A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions are formed and disposed on a lateral wall having a plurality of blades such that at least one depression or thickened area is disposed at a blade pressure side and at least one thickened area or depression is disposed at a blade suction side for each blade of the plurality of blades.
B23P 15/02 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
2.
Safety device for a bearing arrangement of a rotor of a turbomachine
A safety device (10) for a bearing arrangement of a rotor of a turbomachine, whereby the safety device (10) includes at least two support structures (12) between which at least one buckling structure (14) is arranged that is configured to collapse when a predetermined buckling load that acts on at least one of the support structures (12) is exceeded, thereby reducing the volume of the safety device (10). A method for the production of a safety device (10) for a bearing arrangement of a rotor of a turbomachine, as well as to a bearing arrangement of a rotor of a turbomachine having such a safety device (10).
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
F01D 25/16 - Arrangement of bearingsSupporting or mounting bearings in casings
F16C 19/52 - Bearings with rolling contact, for exclusively rotary movement with devices affected by abnormal or undesired conditions
A sealing arrangement (100) in an axial turbomachine between, on the one hand, a rotor (1) and, on the other hand, a stator (3) and/or a housing, including a support device (7, 7′) and a sealing element, whereby the support device (7, 7′) extends essentially in the radial direction (r). In the axial direction (u) of the turbomachine, the support device (7, 7′) has an axial contour that effectuates a stiffening effect for the support device (7, 7′).
A device such as a drum for positioning at least one guide blade row from a plurality of guide blade groups in a turbomachine, the device on the outer circumferential side including at least one flange for attachment to a housing section of the turbomachine and on the inner circumferential side including a plurality of uniformly distributed receptacles for accommodating holding elements of the guide blade groups and a plurality of recesses, the device having a depth-reduced inner circumferential section, relative to the accommodating grooves, between at least two adjoining receptacles, which extends in each case from the one receptacle to the other receptacle; a blade-device combination; a method for assembling such a blade-device combination; and a turbomachine.
F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
B23P 15/04 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
A method for arranging a coating, in particular a hardfacing, on a component, in particular a TiAl drive unit component, is disclosed. The coating comprises a metallic coating material. A green body is formed with the coating material, which is arranged in the presence of a solder on the component and is formed into a coating by a combined solder-sintering process and is fixed on the component.
B23K 31/02 - Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by any single one of main groups relating to soldering or welding
B22F 7/04 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite layers with one or more layers not made from powder, e.g. made from solid metal
F01D 5/22 - Blade-to-blade connections, e.g. by shrouding
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
C23C 30/00 - Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
B23K 1/00 - Soldering, e.g. brazing, or unsoldering
B22F 7/06 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite workpieces or articles from parts, e.g. to form tipped tools
C22C 1/04 - Making non-ferrous alloys by powder metallurgy
C23C 28/02 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of metallic material
6.
SMOOTHING METHOD FOR SURFACES OF COMPONENTS PRODUCED BY ADDITIVE MANUFACTURING
The invention relates to a method for altering the surface characteristics, in particular for smoothing the surface of a component, in which method at least one organometallic compound (3) is applied to a surface (2) of the component (1) to be treated and at least part of the organic portion of the organometallic compound is subsequently removed by thermal and/or reactive treatment. The invention also relates to a method for the additive manufacturing of a component, in which said component is built up incrementally in layers from a component material and the surface is smoothed using the method according to one of the preceding claims and/or by applying an enamel coating. The invention further relates to a component produced accordingly.
C23C 18/02 - Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coatingContact plating by thermal decomposition
B05D 5/00 - Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures
C23C 18/08 - Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coatingContact plating by thermal decomposition characterised by the deposition of metallic material
C23C 18/14 - Decomposition by irradiation, e.g. photolysis, particle radiation
A rotor disk for a turbomachine, which is connectable to at least one rotor blade and/or a shaft of the turbomachine, having at least one borehole, which has an elliptical inlet opening having a first passage cross-sectional area and an elliptical outlet opening having a second passage cross-sectional area, so that the second passage cross-sectional area is smaller than the first passage cross-sectional area.
A vane assembly used for controlling a turning gas flow includes multiple vanes, each of which is bowed toward a pressure side of the vane at the root of the vane.
The invention relates to a blade (2) of a turbomachine, in particular a rotor blade of a gas turbine, which has a variable transition radius (Rv1) in the vicinity of at least one platform overhang (16), and to a turbomachine having at least one such blade (2).
A blade for a continuous-flow machine is disclosed, especially an aircraft engine, whereby, starting from the middle section, the cross section of the blade tip is reduced with respect to the middle section, at least over a front partial section in the direction of the leading edge and over at least a rear section in the direction of the trailing edge, and a continuous-flow machine having at least one row of blades including such blades is also disclosed.
A blade cascade for a continuous-flow machine having a non-axisymmetrical side wall contour, whereby the side wall contour has at least one suction-side depression that, in the circumferential direction, is at a distance from a suction-side wall, and having a section located upstream from the leading edges and a section located downstream from the leading edges, it has a pressure-side elevation that makes a transition to a pressure-side wall and that is located in a front blade area, and it has a pressure-side depression that is located upstream from the pressure-side elevation, and also discloses a continuous-flow machine having such a blade cascade.
A damper (2) for damping a blade movement of a turbomachine (1), and to a method for producing the damper (2). The damper (2) has at least one side surface (21, 21′) which can be brought into frictional contact with a friction surface of the turbomachine (1) in order to damp a blade movement. The side surfaces (21, 21′) are asymmetrically convex in shape.
In a moving blade system for a turbomachine, in particular a gas turbine, having at least one moving blade (1), the moving blade system having at least one cavity (3) in which at least one tuning mass (2) is movably situated, the tuning mass and/or the cavity is/are adapted in such a way that the tuning mass rests against an inner wall (3.1) of the cavity in a predefined first operating state of the turbomachine and at least temporarily moves away from the inner wall in a second predefined operating state of the turbomachine.
A blade for a turbomachine, in particular a jet engine, including a shroud, having two opposite lateral edges, for delimiting a main flow channel and including a blade which extends away from the shroud, a rounded transition area being provided which encompasses the blade on its root side and is guided beyond the one lateral edge, a section of the transition area protruding beyond the one lateral edge being severed and situated in the area of the other lateral edge as an elevation offset in the transverse direction, a blade arrangement having at least two of such blades as well as a turbomachine having a plurality of such blades.
The invention relates to a method for producing a low-pressure turbine blade from a TiAl material by means of a selective laser melting process, wherein during production in the selective laser melting process the already partially manufactured low-pressure turbine blade is preheated by inductive heating, and wherein the selective laser melting process is carried out under protective gas, wherein the protective gas atmosphere contains contaminants attached to oxygen, nitrogen, and water vapour in each case of less than or equal to 10 ppm, in particular less than or equal to 5 ppm.
The invention relates to a device for the generative production of components (4) by means of selective irradiation of a powder bed (6) having a working space (1) in which at least one powder bed chamber (3) and at least one radiation source are arranged, such that the radiation source is able to irradiate a powder in the powder bed chamber (2), and wherein the device comprises at least one induction coil (3, 13), such that a component that is generated by irradiation (7) of the powder bed can be at least partially inductively heated, and wherein the induction coil (3, 13) is movable relative to one or more powder bed chambers (2). The invention further relates to a method for the generative production of components (4) by means of selective irradiation of a powder bed (6), in which method the component produced (4) is inductively heated at the same time, wherein, on the basis of the geometry of the component to be produced, the position of one or more induction coils (3, 13) for the inductive heating is determined and set.
B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
B23K 26/32 - Bonding taking account of the properties of the material involved
B29C 67/00 - Shaping techniques not covered by groups , or
17.
CR (VI)-FREE ANTI-CORROSION LAYERS OR ADHESIVE LAYERS WHICH CONTAIN A SOLUTION COMPRISING PHOSPHATE IONS AND METAL POWDER, THE METAL POWDER BEING AT LEAST PARTIALLY COATED WITH SI OR SI ALLOYS
The present invention relates to a coating material for the production of an anti-corrosion and/or adhesion promoter layer, which material comprises metal powder and a phosphate-ion-containing solution as the binder, the metal powder being at least partially coated with Si or Si alloys or the binder consisting of phosphoric acid and metal phosphates and being substantially free of chromates. The invention further relates to a method for producing an anti-corrosion and/or adhesion promoter layer, comprising the following steps: Providing a coating material, such as indicated above, applying the coating material to a component surface on which the anti-corrosion and/or adhesion promoter layer is to be created, and drying and/or hardening by way of a heat treatment at a first temperature.
C04B 28/34 - Compositions of mortars, concrete or artificial stone, containing inorganic binders or the reaction product of an inorganic and an organic binder, e.g. polycarboxylate cements containing cold phosphate binders
C09D 5/10 - Anti-corrosive paints containing metal dust
C23C 22/22 - Orthophosphates containing alkaline earth metal cations
C23C 22/74 - Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals characterised by the process for obtaining burned-in conversion coatings
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
C23C 10/18 - Solid state diffusion of only metal elements or silicon into metallic material surfaces using liquids, e.g. salt baths, liquid suspensions
C23C 10/30 - Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes using a layer of powder or paste on the surface
C23C 10/58 - Embedding in a powder mixture, i.e. pack cementation more than one element being diffused in more than one step
18.
SLURRY AND METHOD FOR PRODUCING AN ALUMINUM DIFFUSION LAYER
The present invention relates to a slip for producing an aluminum diffusion layer which comprises an AI-containing powder and an Si-containing powder and a binder, the slurry further comprising an AI-containing powder the powder particles of which are coated with Si. The invention further relates to a method for producing an aluminum diffusion layer, comprising the following steps: Providing a slurry according to any one of the preceding claims, applying the slurry to a component surface on which the aluminum diffusion layer is to be created, drying and/or hardening by way of a heat treatment at a first temperature, and diffusion annealing at a second temperature.
C23C 10/18 - Solid state diffusion of only metal elements or silicon into metallic material surfaces using liquids, e.g. salt baths, liquid suspensions
C23C 10/20 - Solid state diffusion of only metal elements or silicon into metallic material surfaces using liquids, e.g. salt baths, liquid suspensions only one element being diffused
19.
Securing device for axially securing a blade root of a turbomachine blade
A securing device (20) for axially securing a blade root (12) of a blade in a groove (11) of a turbine engine. The outer contour (24) of the securing device (20) that faces a groove wall, in particular a groove base (33), is curved at least in some regions, the outer contour (24) having three different radii (R1, R2, R3) in some regions.
A turbomachine including at least one blade-row group that is arranged in the main flow path and at least two rows of blades that are adjacent to each other in the main flow direction, each row having a plurality of blades, whereby the trailing edges of the blades of the upstream row of blades and the leading edges of the blades of the downstream row of blades are arranged at an axial edge distance that decreases from the center of the main flow path in the direction of at least one main flow limiter.
F01D 1/04 - Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor traversed by the working-fluid substantially axially
F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
A blade group arrangement for a turbomachine in order to form a blade-row group, whereby a front blade and a rear blade each form an overlapping area that has a contraction ratio of at least 1.2, and it also relates to a turbomachine having such a contraction ratio between a front blade and a rear blade.
F01D 1/24 - Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working-fluid stream without intermediate stator blades or the like
A turbomachine is disclosed having at least one blade row group, which is situated in a main flow path and has at least two adjacent blade rows, viewed in the main flow direction, each blade row having a plurality of blades, the rear edges of the blades of the upstream blade row and the front edges of the blades of the downstream blade row in the peripheral direction being situated at an edge distance which varies starting from a main flow path center in the direction of at least one main flow limitation, the periphery-side edge distance increasing or decreasing on both sides.
A turbomachine including at least one blade-row group that is arranged in the main flow path and at least two rows of blades that are adjacent to each other in the main flow direction, each row having a plurality of blades (38, 40), whereby a narrow cross section and a degree of overlap between the blades of the upstream row of blades and the blades of the downstream row of blades vary starting at the center of the main flow path in the direction of at least one main flow limiter.
F01D 1/04 - Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor traversed by the working-fluid substantially axially
A sealing system and method is disclosed. The sealing system includes a brush sealing element and an accommodating element with an accommodating chamber. The brush sealing element is disposed in the accommodating chamber and a bendable strap is disposed on the accommodating element. The method includes fastening the brush sealing element in the accommodating chamber of the accommodating element. The accommodating element is arranged in a groove of a housing segment and a position of the accommodating element is secured on the housing element by bending the strap of the accommodating element to engage with a side wall of the housing segment.
A blade cascade for a turbomachine having a plurality of blades arranged next to one another in the peripheral direction, at least two blades having a variation for generating an asymmetric outflow in the rear area, as well as a turbomachine having an asymmetric blade cascade, which is connected upstream from another blade cascade, are disclosed.
The invention relates to a method for producing a component from a TiAl alloy, wherein the component is shaped by forging, in particular isothermal forging, and is subsequently subjected to at least one heat treatment, wherein in the first heat treatment the temperature is between 1100 and 1200°C and is maintained for 6 to 10 hours and then the component is cooled.
A housing-side structure of a turbomachine, in particular of a gas turbine, including an in particular segmented jacket ring (16), which carries an abradable lining for radially outer ends of rotor-side moving blades of a moving blade ring, wherein the jacket ring (16) carrying the abradable lining is connected by means of at least one constriction (18) to a stator-side housing part (19), which is radially adjacent to the jacket ring (16) on the outside and the jacket ring is thermally decoupled from said stator-side housing.
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F01D 11/18 - Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
F04D 29/52 - CasingsConnections for working fluid for axial pumps
The invention relates to a method for cleaning a turbo-machine stage (100) consisting of at least one of the following steps: a cleaning nozzle (1) is introduced into an opening of a turbo-machine, in particular into an inspection opening (220); and the blade (100) of the stage is acted upon by solid particles, said particles subliming at the blade temperature, in particular into dry ice particles.
B08B 7/00 - Cleaning by methods not provided for in a single other subclass or a single group in this subclass
B24C 1/00 - Methods for use of abrasive blasting for producing particular effectsUse of auxiliary equipment in connection with such methods
B08B 9/00 - Cleaning hollow articles by methods or apparatus specially adapted thereto
B24C 1/08 - Methods for use of abrasive blasting for producing particular effectsUse of auxiliary equipment in connection with such methods for polishing surfaces, e.g. by making use of liquid-borne abrasives
B24C 3/32 - Abrasive blasting machines or devicesPlants designed for abrasive blasting of particular work, e.g. the internal surfaces of cylinder blocks
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
30.
Method for repair of a component of a turbomachine and a component repaired according to this method
A method is disclosed for the repair of a component of a turbomachine, in particular a rotor of an aircraft gas turbine, with blades taken up in at least one groove and with at least one support region for limiting a blade tilt angle, whereby at least one segment, which has been subjected to wear, of the support region of the component is removed, and a coating that can be introduced in the unit on at least one supporting surface of at least one blade is formed on the component for limiting the blade tilt angle. In addition, a component of a turbomachine, in particular a rotor of an aircraft gas turbine, with at least one such repair site is disclosed.
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
A turbomachine stage includes guide vanes and an airfoil platform forming a guide vane cascade, and rotor blades and an airfoil platform forming a rotor blade cascade. Airfoil platforms have cascade regions extending between circumferentially adjacent airfoils, and gap regions which radially and/or axially bound an axial gap extending axially between the guide vane cascade and the rotor blade cascade. A contour of at least one of these gap regions varies in the radial and/or axial direction around the circumference. A maximum extent of this contour in the radial direction toward the spoke-like pattern is circumferentially spaced from an airfoil edge of this cascade by no more than 50% of the cascade pitch, a maximum variation in the radial direction being no more than 50% of the cascade pitch and/or a maximum extent in the axial direction away from the spoke-like pattern is circumferentially spaced from an airfoil edge of this cascade by no more than 50% of the cascade pitch, a maximum variation in the axial direction being no more than 50% of the cascade pitch.
The present invention relates to a nickel-base superalloy comprising aluminium, cobalt, chromium, molybdenum, tantalum, titanium and tungsten, in addition to nickel, as alloy constituents, wherein rhenium can additionally be contained and the rhenium content is less than or equal to 2 wt.% and wherein the titanium content is greater than or equal to 1.5 wt.%. The invention further relates to components made of the nickel-base superalloy.
A method for depositing material layers on a workpiece made of a material which contains a titanium aluminide includes the steps of: preparing the workpiece; heating the workpiece in a localized region by induction to a predefined preheating temperature; and depositing an additive, preferably in powder form, on the heated surface of the workpiece by build-up welding, in particular laser build-up welding, plasma build-up welding, micro-plasma build-up welding, TIG build-up welding or micro-TIG build-up welding; the additive including a titanium aluminide.
A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions are formed and disposed on a lateral wall having a plurality of blades such that at least one depression or thickened area is disposed at a blade pressure side and at least one thickened area or depression is disposed at a blade suction side for each blade of the plurality of blades.
B23P 15/02 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
The present invention relates to a method for arranging a coating (8, 9), in particular a hardfacing, on a component (1), in particular a TiAl drive unit component, wherein the coating comprises a metallic coating material, and wherein a green body is formed with the coating material, which is arranged in the presence of a solder on the component (1) and is formed into a coating by means of a combined solder-sintering process and is fixed on the component.
F01D 5/22 - Blade-to-blade connections, e.g. by shrouding
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
B23K 1/00 - Soldering, e.g. brazing, or unsoldering
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions formed and disposed on a lateral wall having a plurality of blades such that at least one depression is disposed on a blade pressure side and at least one thickened area is disposed on a blade suction side for each blade of the plurality of blades.
The invention relates to a method for the generative production of a component (3), in particular of a turbo-engine component, wherein material (4) is bonded layer-wise selectively to a layer or to a substrate (6) disposed therebeneath, wherein before, during and/or after the bonding a laser (1A; 1B; 2) additionally acts on the material (4).
B23K 26/34 - Laser welding for purposes other than joining
B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
B28B 1/00 - Producing shaped articles from the material
B23P 15/04 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
The present invention relates to a method for coating a component, in particular a component of a gas turbine or an aircraft engine, in which the coating is applied to the component by means of cold gas spraying and wherein the surface of the component (1) to be coated is pretreated with cold plasma (11) before the coating. The present invention further relates to a cold gas spraying device (4) for performing the method.
The invention relates to a method for armoring TiAl vanes of turbomachines. A TiAl vane is provided onto which a mixture of at least one hard material and at least one braze material is applied so that subsequently the mixture can be brazed on the TiAl vane by means of an inductive heating process. The invention further relates to a TiAl vane for a turbomachine, in particular for an aircraft engine, comprising a TiAl main part and an armor which consists of a mixture of hard materials and braze material.
F01D 5/22 - Blade-to-blade connections, e.g. by shrouding
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
B23K 1/00 - Soldering, e.g. brazing, or unsoldering
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
A blade row for a turbomachine, in particular a gas turbine, is disclosed. The blade row has a number of first blade arrangements each having at least one first blade and a first shroud with a first extension in the circumferential and/or axial direction and at least a number of additional blade arrangements each having at least one additional blade and one additional shroud with an additional extension in the same direction, which is different from the first extension.
A component, in particular for a gas turbine, is disclosed. The component has at least two component segments which are arranged relative to one another leaving a gap and are sealed against each other by a sealing device. The sealing device includes at least one brush seal. Also disclosed is a gas turbine, in particular an aircraft engine, having such a component.
The invention relates to a method and device for generatively producing components, said device comprising a radiation device for selectively radiating a powder bed, and an induction device for inductively heating the component produced by radiating the powder bed. Said induction device comprises at least one voltage source which can simultaneously produce alternating voltages with at least two different frequencies.
A method for generative production of a component (4) by means of a device (2.1), wherein a cycle, with the steps: - application (S 10) of a layer with solidifiable material (5) and - local solidification (S20) of material in this layer, is repeated many times and a physical parameter of the device (2.1) and/or the component being created is detected and compared in an at least partially automated manner to a reference parameter in at least one cycle.
The invention relates to a method for the generative production of a component (2) and to a device for carrying out such a method, having the following steps: applying a material layer with a constant layer thickness; hardening a region of the material layer according to a component cross-section; generating an eddy current scan of the hardened region, a scan depth corresponding to a multiple of the layer thickness; ascertaining a material characterization of the hardened region taking into consideration a previous eddy current scan of hardened regions of lower-lying material layers; and repeating the steps until the component (2) is assembled. An electric material characterization of each individual layer is determined using a recursive algorithm of individual measurements (monolayer by monolayer), and thus the entire component is checked step by step in a complete and highly resolve manner.
B23K 31/12 - Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by any single one of main groups relating to investigating the properties, e.g. the weldability, of materials
B23K 26/34 - Laser welding for purposes other than joining
B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
B29C 67/00 - Shaping techniques not covered by groups , or
G01N 27/90 - Investigating or analysing materials by the use of electric, electrochemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws using eddy currents
B23K 26/08 - Devices involving relative movement between laser beam and workpiece
B23K 37/02 - Carriages for supporting the welding or cutting element
B23Q 1/48 - Movable or adjustable work or tool supports using particular mechanisms with sliding pairs and rotating pairs
45.
METHOD FOR MANUFACTURING, REPAIRING AND/OR EXCHANGING A ROTOR/STATOR COMBINATION SYSTEM, AND A ROTOR/STATOR COMBINATION SYSTEM MANUFACTURED IN ACCORDANCE WIH THE METHOD
A rotor/stator combination system and a method for manufacturing, repairing and/or exchanging a rotor/stator combination system, in particular a compressor or a turbine of an engine, having a rotor which has at least one blade element and having a stator, wherein the method has the following step: layered build-up of the rotor with the at least one blade element together with the stator by means of a generative production process.
A method for electrochemically processing a workpiece surface using an electrode, which has at least one effective surface for processing the workpiece surface, and using an electrolyte, wherein the electrolyte is suctioned away from the effective surface. The invention further relates to an electrode, which has at least one electrolyte feed for supplying the electrolyte to the effective area and an electrolyte suctioning system for suctioning the electrolyte away from the effective area.
The invention discloses a component (1), in particular a ring or rod element, having a main body (2) which comprises at least one end section (4) which is connectible to an additional end section (6), wherein a first end section (4) comprises a locking system (16) having a guide surface (18) which can be moved, with respect to a guide plane (20), to contact a guide surface (22) of a guide section (24) of the second end section (6), and the second end section (6) comprises a locking protrusion (26) having a support surface (28) which, with respect to the guide plane (20), can be moved to contact a support surface (30) of a guide section (32) of the first end section (4), wherein the locking protrusions (16, 26) latch onto each other in a locking position.
The invention relates to a method for producing forged components made of a TiAl alloy, in particular turbine blades. The components are forged and undergo a two-stage heat treatment after the forging process. The first stage of the heat treatment comprises a recrystallization annealing process for 50 to 100 minutes at a temperature below the γ/α transition temperature, and the second stage of the heat treatment comprises a stabilization annealing process in the temperature range of between 800 °C to 950 °C for 5 to 7 hrs. The cooling rate during the first heat treatment stage is greater than or equal to 3 °C/sec, in the temperature range between 1300 °C to 900 °C.
The invention relates to a method for producing, repairing and/or exchanging a housing, in particular an engine housing of an aircraft engine, comprising at least two shells, between which a structural part is formed, wherein the method comprises the following step: layer-by-layer construction of the at least two shells jointly with the structural part by means of a generative manufacturing system, wherein the structural part comprises at least one porous structure and/or honeycomb structure. The invention relates furthermore to such a housing.
F01D 5/00 - BladesBlade-carrying membersHeating, heat-insulating, cooling, or antivibration means on the blades or the members
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F01D 25/26 - Double casingsMeasures against temperature strain in casings
The invention relates to a splash protection device (2) for receiving welding spatter or melt spatter (22) that occurs during the construction of a component (3) by means of a generative manufacturing process upon the selective solidification of a power layer (12) by energy radiation (9), wherein the splash protection device (2) comprises a receptacle (14) having a support (15) that is provided with at least one layer of an adhesive or adhering material (16) for receiving welding or melt spatter (22).
A guide blade of a turbomachine, in particular of a compressor, a blade of the guide blade without an inner shroud having a flow inlet edge, a flow outlet edge, a suction side, and a pressure side. The blade is formed by a plurality of blade sections stacked one on top of the other in the radial direction, and the centers of gravity of the blade sections extend along a stacking axis. The blade sections are stacked one on top of the other in the radial direction in such a way that, in a radially inner section of the blade adjacent to a radially outer section of the blade, the stacking axis has its single inflection point in its radial curvature, namely, between a first, radially inner subsection of the radially inner section in which the stacking axis has a concave curvature toward the pressure side, and a second, radially outer subsection of the radially inner section in which the stacking axis has a concave curvature toward the suction side.
The invention relates to a method for producing an inlet lining for a turbomachine for slowing down a rotor in the event of a shaft fracture, wherein the inlet lining is formed as an integral generative blade section when a blade is produced generatively. The invention further relates to an inlet system, comprising an inlet ring that is arranged circumferentially on a series of blades and has a chamber-like material structure, to a turbomachine having such an inlet system, and to a guide blade having such an inlet lining.
F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
53.
COLD GAS SPRAY METHOD WITH IMPROVED ADHESION AND REDUCED LAYER POROSITY
The present invention relates to a method for coating a component, in which the coating material is applied to the component that is to be coated in powder form by means of cold gas spraying, following which a surface heat treatment is carried out, during which the deposited material is melted. The invention also relates to a corresponding coating on a component, said coating being produced using said method.
C23C 24/10 - Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
54.
ROTOR BLADE FOR A COMPRESSOR OF A TURBOMACHINE, COMPRESSOR, AND TURBOMACHINE
The invention relates to a rotor blade for a compressor of a turbomachine, comprising a blade that has a front edge, a rear edge, and a blade tip, between which a pressure side and a suction side extend, wherein a pressure-side profile variation that extends into the rear edge and the blade tip is provided. The invention further relates to a compressor and to a turbomachine.
The invention relates to a method for checking a blade contour of a turbomachine, in particular a gas turbine, wherein an actual contour (1; 1') of a blade is detected, wherein a target contour of the blade is scaled and the actual contour is compared with said scaled target contour (2).
G05B 19/401 - Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by control arrangements for measuring, e.g. calibration and initialisation, measuring workpiece for machining purposes
56.
METHOD FOR THE PRODUCTION, REPARATION OR REPLACEMENT OF A COMPONENT, INCLUDING A COMPACTING STEP USING PRESSURE
The invention relates to a method for producing, repairing and/or replacing a component, in particular a blade element of a gas turbine in an aircraft engine. Said method includes the following steps: applying a layer of material, powder being fused using energy radiation; compacting a selected region by applying pressure thereto.
An inner ring for forming a guide blade ring for a turbomachine is disclosed, composed of at least two one-part ring segments having a plurality of openings, closed on the peripheral side, for accommodating journal bearings on the blade side, the outer diameter of the inner ring being at least 12 times larger than its height. Also disclosed are a guide blade ring having this type of inner ring and a turbomachine having this type of guide blade ring.
The invention relates to a cover device (46) for an integrally bladed main rotor body (1) of a turbomachine for preventing or reducing a cooling air flow from a high pressure side to a low pressure side through channels formed between adjacent rotor blades, wherein a plurality of cover elements (48) are provided that can be inserted individually into the channels and have at least one peripheral sealing surface(58, 72). The invention further relates to an integrally bladed main rotor body with such a cover device, to a method for producing such an integrally bladed main rotor body and to a turbomachine having such an integrally bladed main rotor body.
An inner ring for forming a guide blade ring for a turbomachine is disclosed, composed of at least two one-part ring segments having a plurality of openings, closed on the peripheral side, for accommodating journal bearings on the blade side, the outer diameter of the inner ring being at least 12 times larger than its height. Also disclosed are a guide blade ring having this type of inner ring and a turbomachine having this type of guide blade ring.
The present invention relates to a blade arrangement for a turbo engine, in particular a gas turbine, with a rotor and several blades fastened thereto, which are configured to be systematically different, wherein at least two adjacent blades have systematically different cover bands (12, 22) and/or inner blade platforms (11, 21).
The present invention provides a bearing arrangement (1), in particular for a turbomachine (2), having a first and/or second bearing housing part (3, 4) with at least one coolant duct (7, 7') for cooling the first and/or second bearing housing part (3, 4) and with at least one lubricant duct (8) for supplying lubricant to a bearing (12), wherein the coolant duct (7, 7') and the lubricant duct (8) are provided so as to be fluidically separate from one another.
The invention relates to a method for generatively producing or repairing a component (1), in particular a turbomachine, comprising a layered material structure, which can be produced directly or indirectly on a construction platform (6) and/or on a component to be repaired, wherein a first material structure (8) having a first construction direction (10) and a second material structure (16) having a second construction direction (18) different from the first construction direction (10) are produced in order to form a load-optimized structure. The invention further relates to a component (1), in particular for a turbomachine, comprising at least one generatively produced first material structure (8) having a first construction direction (10) and at least one second generatively produced material structure (16) having a second construction direction (18) different from the first construction direction.
A device (2) having at least one connecting element (24, 26) for fastening a component (4) to, respectively for detaching it from a component carrier (6) using adhesive bonds; a mechanical peeling device (8) being provided for breaking the adhesive bonds. Also a method for fastening a component (4) to, respectively for detaching it from a component carrier (6).
A blade channel having a not-axially-symmetric end wall contour in a turbomachine is disclosed, the end wall contour having at least one individual contour in the form of an elevation, on the pressure side, and at least three individual contours in the form of two recesses and one elevation, on the suction side, the elevation being situated between the recesses in the flow direction; a turbomachine having a plurality of blade channels of this type is also disclosed.
The invention relates to a method for monitoring a generative production process in real time, wherein an element is at least optically detected and the installation space is thermally detected when applying a layer. The invention also relates to a device for carrying out said method.
The invention relates to a heat exchanger (20), in particular for a jet engine, said engine being designed as a structure-mechanical and/or fluid-mechanical element or having an integral element of this type and being at least partially produced by rapid manufacturing.
The invention relates to a process for testing the generative production of a component, the process comprising the following steps: at least one ultrasonic transducer device having a transmitter device for emitting ultrasonic signals is provided; at least one receiver device for receiving ultrasonic signals and determining at least one parameter of the ultrasonic signals is provided; an evaluation device for evaluating the at least one parameter is provided; at least one powder layer consisting of a powder which can be solidified by energy radiation is applied to a building platform and a selected region of the powder layer is solidified by energy radiation to form a component region; at least one partial region of the solidified component region is acted upon by ultrasonic signals by means of the transmitter device; the reflected ultrasonic signals are received; at least one parameter of the reflected ultrasonic signals is determined; and the at least one parameter is evaluated by the evaluation device.
The invention relates to a method for producing gas turbine components, in particular aircraft turbine components, preferably low-pressure turbine blades made of a powder sintered selectively in layers by locally limited introduction of radiant energy, wherein the sintering is carried out in a closed first housing (2), so that a defined atmosphere can be set, wherein the powder or at least one part of the powder is generated in the same first housing (2) or in a second housing connected to the first housing in a gas-tight manner. The invention further relates to a corresponding device and to a gas turbine blade produced thereby.
B22F 3/00 - Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sinteringApparatus specially adapted therefor
B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
B22F 9/04 - Making metallic powder or suspensions thereofApparatus or devices specially adapted therefor using physical processes starting from solid material, e.g. by crushing, grinding or milling
B22F 9/10 - Making metallic powder or suspensions thereofApparatus or devices specially adapted therefor using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying using centrifugal force
69.
INTERMEDIATE HOUSING OF A GAS TURBINE WITH AN OUTER BOUNDING WALL, HAVING UPSTREAM OF A SUPPORTING RIB A CONTOUR THAT CHANGES IN THE CIRCUMFERENTIAL DIRECTION, FOR REDUCING SECONDARY FLOW LOSSES
Intermediate housing (14), in particular of turbines (11, 13) of a gas engine, having a radially inner bounding wall (23) and having a radially outer bounding wall (24, 24'), having a crossflow channel (33) which is formed by the bounding walls (23, 24, 24') and in which at least one supporting rib (15) is positioned which has a front edge (16), a rear edge (17) and side walls (18) which extend between the front edge (16) and the rear edge (17) and guide a gas flow which flows through the crossflow channel (33), wherein the radially outer bounding wall (24) has a contour which changes in the circumferential direction, at least in a section upstream of the supporting rib (15).
F01D 11/04 - Preventing or minimising internal leakage of working fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
F01D 25/16 - Arrangement of bearingsSupporting or mounting bearings in casings
F02C 7/20 - Mounting or supporting of plantAccommodating heat expansion or creep
F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
The invention relates to a turbomachine blade (1) with a tuning element (2; 2'; 20) which is provided for impact contact with the blade, with a tuning element guide (3; 3'), in particular a cavity, by which an individual tuning element (2; 2') is movably guided; and/or with a resilient support structure (10) for oscillating storage of the tuning element (20), and wherein the tuning element guide (3; 3') or support structure (10) is fastened to a blade root (1.10), in particular a blade neck (1.12) of the blade.
F01D 5/16 - Form or construction for counteracting blade vibration
71.
METHOD FOR THE GENERATIVE PRODUCTION OF A COMPONENT WITH AN INTEGRATED DAMPING ELEMENT FOR A TURBOMACHINE, AND A COMPONENT PRODUCED IN A GENERATIVE MANNER WITH AN INTEGRATED DAMPING ELEMENT FOR A TURBOMACHINE
The invention relates to a method for the generative production of a component (1) with an integrated damping element for a turbomachine, in particular a gas turbine, having the following method steps: assembling the component (1) in a generative manner, and introducing a damping material (2) into the component (1) during the method step of the generative assembly of the component (1). The invention further relates to a component (1) with an integrated damping element for a turbomachine, in particular a gas turbine, wherein the component (1) is assembled in a generative manner, and the component (1) has a damping material (2) which is introduced into the component (1) during the generative assembly of the component (1). The invention further relates to a turbomachine, in particular a gas turbine, comprising such a component (1).
A joining device for arranging a component on a component carrier is disclosed. The joining device includes an application system for positioning the component in the joining device and a receptacle for clamping the component carrier in the joining device. The component is arranged on the component carrier by an adapter. A method for arranging the component on the component carrier is also disclosed.
What is disclosed is a process for electrochemically individually coating a component, in particular a turbine blade or vane, wherein, to treat a component face, i.e. reduce a layer thickness of a coating of the component in the region of the component face right up to setting a layer thickness of 0 mm and thus avoiding a coating of the component face, a shaping face of a shaping panel with a near-net shape in relation to the component face is applied to the component face (spacing = 0 mm) or is spaced apart from the component face (spacing > 0 mm), and also an apparatus for carrying out such a process.
An anti-wear coating, in particular an anti-erosion coating, which is applied to a surface of a component that is stressed under fluid technology and is to be protected, in particular a gas turbine part, is disclosed. The anti-wear coating includes one or more multilayer systems applied in a repeating order to the surface to be coated, and the/each multilayer system includes at least one relatively soft metallic layer and at least one relatively hard ceramic layer. All the layers of the/each multilayer system are based on chromium, and a diffusion barrier layer is applied between the surface to be protected and the multilayer system(s).
B32B 15/04 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance
76.
DAMPING MEANS FOR DAMPING A BLADE MOVEMENT OF A TURBOMACHINE
The invention relates to a damping means (2) for damping a blade movement of a turbomachine (1) and to a method for producing the damping means (2). The damping means (2) has at least one side surface (21, 21') which can be brought into frictional contact with a friction surface of the turbomachine (1) in order to damp a blade movement. The side surfaces (21, 21') are of asymmetrically convex configuration.
The invention relates to a method for the layered manufacturing of a structural component from powder, comprising the following steps: establishing at least one parameter (t) of a depression (1) in a produced layer (2) of the structural component; smoothing out the depression (1) if the at least one parameter (t) exceeds a predetermined value; and filling the smoothed-out depression (1) with powder (13).
According to the invention, a process for applying layers (22) of material to a workpiece (10) made of a material which comprises or consists of a titanium aluminide comprises the following steps: the workpiece is prepared; the workpiece is heated to a predefined preheating temperature in a locally delimited region (24) by means of induction (20); and a, preferably pulverulent, additive is applied to the heated surface of the workpiece by means of build-up welding, in particular laser build-up welding, plasma build-up welding, micro-plasma build-up welding, TIG build-up welding or micro-TIG build-up welding, wherein the additive comprises a titanium aluminide.
The present invention relates to a solder alloy based on nickel and composed of a mixture comprising a first solder material, a second solder material and a base material, wherein the base material is a nickel-based material which corresponds to the material to be soldered and is present in a proportion of from 45 to 70% by weight in the mixture, the first solder material is a nickel-based material comprising chromium, cobalt, tantalum, aluminium and boron and is present in a proportion of from 15 to 30% by weight in the mixture and the second soldered material is a nickel-based material which comprises chromium, cobalt, molybdenum, tungsten, boron and hafnium and is present in a proportion of from 15 to 25% by weight in the mixture, and also a process for producing a corresponding solder alloy and the use of the solder alloy for the repair of gas turbine components.
According to the invention, in a rotor blade arrangement for a turbo machine, in particular a gas turbine, having at least one rotor blade (1), wherein the rotor blade arrangement has at least one cavity (3) in which at least one tuning mass (2) is arranged in a movable manner, the tuning mass and/or the cavity are/is adapted such that the tuning mass bears against an inner wall (3.1) of the cavity in a predefined first operating state of the turbo machine, and moves away from the inner wall at least intermittently in a second predefined operating state of the turbo machine.
The invention relates to a securing means (20) for axially securing a blade root (12) of a blade in a groove (11) of a turbomachine. The outer contour (24) of the securing means (20) facing a groove wall, in particular a groove base (33), is curved at least in some areas, wherein the outer contour (24) has different radii (R1, R2, R3) in some areas.
The present invention relates to a blade of a turbomachine, in particular an adjustable guide blade or vane of a gas turbine, having at least one thickened area (18) on a pressure side (D) of the blade profile (P), wherein the thickened area (18) is disposed in a radially outer-lying, housing-side region of the blade (10), wherein the thickened area (18) is designed at a distance from a front edge (12) and a rear edge (14) of the blade (10).
A method for repairing a component of a gas turbine and a solder alloy are disclosed. In an embodiment, the method includes applying the solder alloy to the component in an area of the component having a punctiform damage or a linear imperfection, where the solder alloy is a mixture of a NiCoCrAlY alloy and a Ni-based solder. A molded repair part made of the solder alloy is applied to the component in an area of the component having a planar defect. The component is heat treated to solder the molded repair part on the component and to solder the solder alloy applied to the component in the area of the component having the punctiform damage or the linear imperfection. The component is cooled after the heat treating and, following the cooling, the component is further heat treated.
B23K 31/02 - Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by any single one of main groups relating to soldering or welding
DEVICE FOR PRODUCING, REPAIRING, AND/OR REPLACING A COMPONENT BY MEANS OF A POWDER THAT CAN BE SOLIDIFIED BY ENERGY RADIATION, AND A METHOD AND A COMPONENT PRODUCED ACCORDING TO THE METHOD
The invention relates to a device for producing, repairing, and/or replacing a component, in particular an aircraft component, by means of a powder that can be solidified by energy radiation of an energy radiation source, characterized in that the device has a supporting platform, which is arranged at a predetermined angle greater than 0° from a horizontal plane and to which the powder that can be solidified by the energy radiation source can be applied.
A shroud segment to be arranged on a gas turbine blade is disclosed. The shroud segment includes a shroud segment surface and a stiffening structure that is raised relative to the shroud segment surface. The stiffening structure is cross-shaped at least in some areas.
For machining robot-guided components, in particular turbine blades (1), with a tool (2), which is fastened in an articulated manner (3, 23, 34) to a tool holder (4), according to the invention a deflection (α, β) of the tool (2) with respect to the tool holder (4) from a desired position (2') is detected and, on the basis of this deflection, a pose of a robot (IR) that is guiding a component is changed.
The invention relates to an anti-wear coating, specifically for components which are subject to erosion under mechanical loading, in particular for gas turbine components, said coating comprising at least two different individual layers which preferably alternate with one another multiply and are applied to a surface of a component which is to be coated. The individual layers comprise a ceramic main layer (45, 46, 47, 48) and a quasi-ductile, non-metallic intermediate layer (41, 42, 43, 44).
C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material
C23C 14/22 - Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
88.
COMPONENT, AND METHOD FOR DEVELOPING, REPAIRING AND/OR CONSTRUCTING SUCH A COMPONENT
The invention relates to a method for developing, repairing and/or constructing a component, especially a vane element of a gas turbine, said method comprising the following steps: a component is provided; and at least part of the component is constructed by means of kinetic cold gas compacting.
F01D 5/00 - BladesBlade-carrying membersHeating, heat-insulating, cooling, or antivibration means on the blades or the members
C23C 24/04 - Impact or kinetic deposition of particles
89.
DEVICE FOR PRODUCING, REPAIRING AND/OR REPLACING A COMPONENT BY MEANS OF A POWDER THAT CAN BE SOLIDIFIED BY ENERGY RADIATION, METHOD AND COMPONENT PRODUCED ACCORDING TO SAID METHOD
The invention relates to a device and method for producing, repairing and/or replacing a component (10), especially an aircraft component, by means of a powder that can be solidified by energy radiation of an energy radiation source, the device comprising an application unit (24) that is designed such that the powder can be applied onto an uneven surface (22) by means of the application unit.
B29C 73/00 - Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass
B29C 67/00 - Shaping techniques not covered by groups , or
B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
B28B 1/00 - Producing shaped articles from the material
90.
COMPONENT, IN PARTICULAR ENGINE COMPONENT, WITH AN ALLOCATION CHARACTERISTIC AND METHOD
The invention relates to a component (1), in particular an engine component, comprising an allocation characteristic (6, 7) for allocating the component (1) a defined place of manufacture. Said allocation characteristic (6, 7) is located inside the component (1) which is inaccessible from the outside.
The invention relates to a method for generatively producing or for repairing at least one area of a component, wherein a zone arranged downstream of a molten bath is post-heated to a post-heating temperature and the component is set to a base temperature. The invention further relates to a device for carrying out such a method.
The invention relates to a generative production method for producing a component by selectively melting and/or sintering a powder several times consecutively by introducing an amount of heat by means of beam energy, such that the powder particles melt and/or sinter in layers, wherein the powder particles (1) are made of a first material (2) and the powder particles are surrounded by a second material (3) partially or over the entire surface thereof, wherein the second material has a lower melting point than the first material and/or lowers the melting point of the first material when mixed with the first material. The invention further relates to a corresponding powder and to a prototype produced from said powder.
B22F 1/02 - Special treatment of metallic powder, e.g. to facilitate working, to improve properties; Metallic powders per se, e.g. mixtures of particles of different composition comprising coating of the powder
B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
A method and device for producing a hole in an object is disclosed. The method includes the generation of a beam for removing material such that a bottom of a borehole is placed in a focus position of the beam, and a removal of material by impingement of the beam on the bottom of the borehole. A repeated placing of the bottom of the borehole in a focus position of the beam in order to compensate for the increased depth of the hole as a result of the removal of material is combined with a step of changing a radiation characteristic of the beam when the bottom of the borehole is repeatedly placed in a focus position.
The invention relates to a heat-resistant TiAl alloy (and the production thereof), which in addition to unavoidable impurities comprises titanium, al, niobium, molybdenum, and carbon as alloying elements. The composition is selected in such a way that the carbon is dissolved into the mixed crystals of the alloy so as to substantially avoid carbide precipitations and the alloy is solidified from the melt exclusively by means of the β-phase and/or ϒ-phase.
Turbomachine housing (10) and method for setting a distance (30) between the turbomachine housing (10) and at least one rotor blade (21) located inside the turbomachine housing (10). At least one control channel (11) is provided in the turbomachine housing (10), wherein a fluid is guided through said control channel in order to heat or cool the turbomachine housing (10), whereby the distance (30) between the turbomachine housing (10) and the rotor blade (21) is set.
The invention relates to a method for the open-loop and/or closed-loop control of a laser device, wherein the method comprises the following steps: determining a laser characteristic curve by setting a predetermined laser variable and detecting the total laser power or total laser energy of the laser beam of the laser device which is established in the case of the laser variable; and open-loop and/or closed-loop control of the laser device on the basis of the laser characteristic curve.
d) of the casing (18) is coupled to at least three adjusting devices (20) of the clearance control system. The invention also relates to a turbomachine (14), especially a gas turbine, as well as to a method for adjusting a running clearance (L).
F01D 11/22 - Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
98.
DESTRUCTION-FREE AND CONTACTLESS INSPECTION METHOD AND INSPECTION APPARATUS FOR SURFACES OF COMPONENTS WITH ULTRASOUND WAVES
FRAUNHOFER-GESELLSCHAFT ZUR FÖRDERUNG DER ANGEWANDTEN FORSCHUNG E.V. (Germany)
MTU AERO ENGINES GMBH (Germany)
Inventor
Köhler, Bernd
Barth, Martin
Bamberg, Joachim
Baron, Hans-Uwe
Abstract
The invention relates to a method for the destruction-free and contactless inspection of components (3), in which ultrasound waves (6) are transmitted in a non-vertical, pre-specifiable incidence angle (9) onto the surface of the component (3) using an ultrasound transmission transducer (1) arranged at a distance from the surface of the component (3) and the intensity of the ultrasound waves (7), which are reflected by the surface of the component (3), is captured in a time-resolved and/or frequency-resolved manner by the group antenna elements (2n) of an ultrasound group antenna (2), which is configured to detect ultrasound waves (7), and, on this basis, the phase shift of the ultrasound waves, which are guided on the surface of the inspection body, is determined in relation to the ultrasound waves (7), which are reflected directly at the surface of the component (3).
G01N 29/07 - Analysing solids by measuring propagation velocity or propagation time of acoustic waves
G01N 29/11 - Analysing solids by measuring attenuation of acoustic waves
G01N 29/22 - Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic wavesVisualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object Details
G01N 29/26 - Arrangements for orientation or scanning
The invention relates to a housing-side structure of a turbomachine, in particular of a gas turbine, comprising an in particular segmented jacket ring (16), which carries an abradable coating for radially outer ends of rotor-side rotor blades of a rotor blade ring, wherein the jacket ring (16) carrying the abradable coating is connected by means of at least one narrow part (18) to a stator-side housing part (19), which is radially outwardly adjacent to the jacket ring (16), and the jacket ring is thermally decoupled from said stator-side housing part.
F01D 11/18 - Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
F04D 29/52 - CasingsConnections for working fluid for axial pumps
The invention relates to a method for cleaning a turbo-machine stage (100) consisting of at least one of the following steps: a cleaning nozzle (1) is introduced into an opening of a turbo-machine, in particular into an inspection opening (220); and the blade (100) of the stage is acted upon by solid particles, said particles subliming at the blade temperature, in particular into dry ice particles.
patents
