Delavan Inc

United States of America

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IPC Class
F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply 13
F02C 7/264 - Ignition 12
F23D 11/38 - NozzlesCleaning devices therefor 6
F02C 7/22 - Fuel supply systems 5
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants 4
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Status
Pending 3
Registered / In Force 27
Found results for  patents

1.

CONTINUOUS IGNITION DEVICE EXHAUST MANIFOLD

      
Application Number 18545506
Status Pending
Filing Date 2023-12-19
First Publication Date 2024-05-16
Owner Delavan Inc. (USA)
Inventor Ryon, Jason

Abstract

A torch ignitor system provides a continuous flame to ignite fuel within a combustor of a gas turbine engine. The torch ignitor system includes a manifold and a plurality of torch nozzles to enable the flame or torch to simultaneously ignite multiple fuel nozzles within the combustor of the gas turbine engine.

IPC Classes  ?

2.

Torch ignitors with gas assist start

      
Application Number 18210139
Grant Number 12031482
Status In Force
Filing Date 2023-06-15
First Publication Date 2023-10-12
Grant Date 2024-07-09
Owner Delavan, Inc. (USA)
Inventor
  • Ryon, Jason A.
  • Williams, Brandon Phillip

Abstract

An embodiment of a torch ignitor system for combustor of a gas turbine engine includes a torch ignitor, the torch ignitor having a combustion chamber oriented about an axis, the combustion chamber having axially upstream and downstream ends defining a flow direction through the combustion chamber, along the axis. The torch ignitor system also includes a cap defining the axially upstream end of the combustion chamber and oriented about the axis, wherein the cap is configured to receive a fuel injector and at least one glow plug, a tip at a downstream end of the combustion chamber, and a passage for pressurized oxygen containing gas passing through the cap from an exterior of the combustion chamber and in fluid communication with the combustion chamber. An embodiment of a method for starting a gas turbine engine is also disclosed.

IPC Classes  ?

  • F02C 7/264 - Ignition
  • F02C 3/00 - Gas-turbine plants characterised by the use of combustion products as the working fluid
  • F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
  • F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel
  • F23R 3/34 - Feeding into different combustion zones

3.

CONNECTING FUEL INJECTORS AND NOZZLES TO MANIFOLDS

      
Application Number 17581358
Status Pending
Filing Date 2022-01-21
First Publication Date 2023-07-27
Owner DELAVAN INC (USA)
Inventor
  • Ryon, Jason
  • Zink, Gregory A.
  • Williams, Brandon Phillip
  • Prociw, Lev A.

Abstract

A method includes joining a fuel plurality of injection components to a fuel manifold, wherein for each fuel injection component in the plurality of fuel injection components, a metallic joint is formed joining and sealing the fuel injection component to the manifold. A system includes a fuel manifold. A plurality of fuel injection components are connected in fluid communication with the fuel manifold with metallic joints sealing between each of the plurality of fuel injection components and the fuel manifold to prevent leakage from between the manifold and the plurality of fuel injection components.

IPC Classes  ?

4.

Continuous ignition device exhaust manifold

      
Application Number 17835525
Grant Number 11891956
Status In Force
Filing Date 2022-06-08
First Publication Date 2022-10-06
Grant Date 2024-02-06
Owner DELAVAN INC. (USA)
Inventor Ryon, Jason

Abstract

A torch ignitor system provides a continuous flame to ignite fuel within a combustor of a gas turbine engine. The torch ignitor system includes a manifold and a plurality of torch nozzles to enable the flame or torch to simultaneously ignite multiple fuel nozzles within the combustor of the gas turbine engine.

IPC Classes  ?

  • F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
  • F02C 7/264 - Ignition

5.

Fuel injector systems for torch igniters

      
Application Number 17533682
Grant Number 11913646
Status In Force
Filing Date 2021-11-23
First Publication Date 2022-08-04
Grant Date 2024-02-27
Owner Delavan Inc. (USA)
Inventor
  • Ryon, Jason
  • Prociw, Lev Alexander

Abstract

A fuel injector system for a torch igniter includes an injector body centered on an axis, a receiving aperture formed in a cap of the torch igniter, an injector aperture, an air channel, a fuel channel, and a purge passage formed in a housing of the torch igniter and fluidly connected to a cooling air source. The injector body includes an axial wall at a first axial end of the injector body, an outer wall connected to the axial wall and extending along the axis transverse to the first wall, and an inner portion connected to the axial wall and extending along the axis transverse to the axial wall. An outer surface of the inner portion is spaced a distance from an inner surface of the outer wall, forming an insulating space between the outer wall and the inner portion.

IPC Classes  ?

  • F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel
  • F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
  • F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
  • F02C 7/232 - Fuel valvesDraining valves or systems

6.

Internally-mounted torch igniters with removable igniter heads

      
Application Number 17127236
Grant Number 11680528
Status In Force
Filing Date 2020-12-18
First Publication Date 2022-06-23
Grant Date 2023-06-20
Owner Delavan Inc. (USA)
Inventor
  • Ryon, Jason
  • Prociw, Lev Alexander
  • Myers, Steve
  • Tibbs, Andy M.
  • Williams, Brandon P.

Abstract

A torch igniter for a combustor of a gas turbine engine includes an igniter body and an igniter head. The igniter body is disposed within a high-pressure case of a gas turbine engine and extends primarily along a first axis, and includes an annular wall and an outlet wall. The annular wall surrounds the first axis and defines a radial extent of a combustion chamber therewithin. The outlet wall is disposed at a downstream end of the annular wall, defines a downstream extent of the combustion chamber, and includes an outlet fluidly communicating between the combustion chamber and an interior of the combustor. The igniter head is removably attached to the igniter body at an upstream end of the annular wall, wherein the igniter head defines an upstream extent of the combustion chamber, and includes an ignition source and a fuel injector.

IPC Classes  ?

  • F02C 7/264 - Ignition
  • F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
  • F02C 7/22 - Fuel supply systems
  • F02C 7/28 - Arrangement of seals
  • F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply

7.

FUEL FILTER ASSEMBLY

      
Application Number 17554866
Status Pending
Filing Date 2021-12-17
First Publication Date 2022-06-23
Owner Delavan Inc. (USA)
Inventor
  • Jedlinski, Marek
  • Bujewicz, Maciej

Abstract

A fuel filter includes a manifold, a connector element, a filter bowl, a filter element, an inlet shutoff valve, an outlet shutoff valve, an inlet port, an inlet conduit, an outlet port, an outlet conduit and a relief valve. The connector element is fixed to the manifold and the filter bowl is reversibly fixed to the connector element. The connector element engages with the filter element. The filter bowl reversibly receives the filter element and is configured so that when the filter element is located within the filter bowl and the filter bowl is attached to the connection element the filter element divides the space defined by the connector element and filter bowl into an inlet filter chamber and an outlet filter chamber. The inlet port is incorporated in the manifold, and the inlet port and inlet filter chamber are in fluid communication via the inlet conduit.

IPC Classes  ?

  • B01D 35/147 - Bypass or safety valves
  • B01D 35/00 - Filtering devices having features not specifically covered by groups , or for applications not specifically covered by groups Auxiliary devices for filtrationFilter housing constructions
  • B01D 29/11 - Filters with filtering elements stationary during filtration, e.g. pressure or suction filters, not covered by groups Filtering elements therefor with bag, cage, hose, tube, sleeve or like filtering elements
  • G05D 7/01 - Control of flow without auxiliary power
  • B64D 37/02 - Tanks

8.

Axially oriented internally mounted continuous ignition device: removable hot surface igniter

      
Application Number 17125083
Grant Number 11486309
Status In Force
Filing Date 2020-12-17
First Publication Date 2022-06-23
Grant Date 2022-11-01
Owner Delavan Inc. (USA)
Inventor
  • Ryon, Jason
  • Prociw, Lev Alexander
  • Williams, Brandon P.

Abstract

An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle at an upstream end of the combustor liner, a torch igniter at least partially within the combustor case, and a removable surface igniter. The torch igniter includes a combustion chamber, a cap configured to receive a fuel injector, a tip, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, an aperture, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip which fluidly connects the combustion chamber to the combustor. The torch igniter is configured to receive the removable surface igniter through the aperture. An internal end of the removable surface igniter extends through the aperture into the combustion chamber of the torch igniter.

IPC Classes  ?

  • F02C 7/264 - Ignition
  • F02C 7/22 - Fuel supply systems
  • F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply

9.

Axially oriented internally mounted continuous ignition device: removable nozzle

      
Application Number 17125114
Grant Number 11754289
Status In Force
Filing Date 2020-12-17
First Publication Date 2022-06-23
Grant Date 2023-09-12
Owner Delavan, Inc. (USA)
Inventor
  • Ryon, Jason
  • Williams, Brandon P.
  • Prociw, Lev Alexander

Abstract

An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle at an upstream end of the combustor liner, a torch igniter within the combustor case, and a removable fuel injector. The torch igniter includes a combustion chamber, a cap configured to receive a removable fuel injector and a surface igniter, a tip, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip which fluidly connects the combustion chamber to the combustor. The removable fuel injector extends through a fuel injector opening of the combustor case. The diameter of the fuel injector opening is wider than a fuel injector diameter of the removable fuel injector.

IPC Classes  ?

  • F23R 3/34 - Feeding into different combustion zones
  • F02C 7/264 - Ignition
  • F02C 7/266 - Electric
  • F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
  • F02C 7/22 - Fuel supply systems
  • F23R 3/42 - Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers

10.

Torch igniter cooling system

      
Application Number 17686911
Grant Number 11719162
Status In Force
Filing Date 2022-03-04
First Publication Date 2022-06-16
Grant Date 2023-08-08
Owner Delavan, Inc. (USA)
Inventor
  • Ryon, Jason
  • Prociw, Lev Alexander

Abstract

An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining the axially upstream end of the combustion chamber and situated on the axis, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, wherein the outlet passage fluidly connects the combustion chamber to the combustor of the gas turbine engine, and a cooling system. The cooling system has an air inlet, a cooling channel, and an aperture. The cooling channel forms a flow path having a first axial section, a second axial section, a radially inward section, and a radially outward section.

IPC Classes  ?

  • F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
  • F02C 7/264 - Ignition
  • F23D 14/78 - Cooling burner parts
  • F23R 3/06 - Arrangement of apertures along the flame tube
  • B33Y 80/00 - Products made by additive manufacturing

11.

Continuous ignition device exhaust manifold

      
Application Number 17123741
Grant Number 11421602
Status In Force
Filing Date 2020-12-16
First Publication Date 2022-06-16
Grant Date 2022-08-23
Owner Delavan Inc. (USA)
Inventor Ryon, Jason

Abstract

A torch ignitor system provides a continuous flame to ignite fuel within a combustor of a gas turbine engine. The torch ignitor system includes a manifold and a plurality of torch nozzles to enable the flame or torch to simultaneously ignite multiple fuel nozzles within the combustor of the gas turbine engine.

IPC Classes  ?

  • F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
  • F02C 7/264 - Ignition

12.

Torch igniter cooling system

      
Application Number 17089250
Grant Number 11473505
Status In Force
Filing Date 2020-11-04
First Publication Date 2022-05-05
Grant Date 2022-10-18
Owner Delavan Inc. (USA)
Inventor
  • Ryon, Jason
  • Prociw, Lev Alexander

Abstract

An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining the axially upstream end of the combustion chamber and situated on the axis, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, wherein the outlet passage fluidly connects the combustion chamber to the combustor of the gas turbine engine, and a cooling system. The cooling system has an air inlet, a cooling channel, and an aperture. The cooling channel forms a flow path having a first axial section, a second axial section, a radially inward section, and a radially outward section.

IPC Classes  ?

  • F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
  • F02C 7/264 - Ignition
  • F23R 3/06 - Arrangement of apertures along the flame tube
  • F23D 14/78 - Cooling burner parts
  • B33Y 80/00 - Products made by additive manufacturing

13.

Surface igniter cooling system

      
Application Number 17089254
Grant Number 11608783
Status In Force
Filing Date 2020-11-04
First Publication Date 2022-05-05
Grant Date 2023-03-21
Owner Delavan, Inc. (USA)
Inventor
  • Ryon, Jason
  • Prociw, Lev Alexander

Abstract

An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining an axially upstream end of the combustion chamber, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, a glow plug housing configured to receive a glow plug and allow an innermost end of the glow plug to extend into the combustion chamber, and a cooling system. The cooling system includes an air inlet formed within an exterior of the structural wall, a cooling channel forming a flow path through the structural wall at the glow plug housing, and an air passage.

IPC Classes  ?

14.

Torch igniter cooling system

      
Application Number 17089236
Grant Number 11692488
Status In Force
Filing Date 2020-11-04
First Publication Date 2022-05-05
Grant Date 2023-07-04
Owner Delavan Inc. (USA)
Inventor
  • Ryon, Jason
  • Prociw, Lev Alexander

Abstract

An embodiment of a torch igniter for a combustor of a gas turbine engine comprises a combustion chamber oriented about an axis, a cap defining an axially upstream end of the combustion chamber and oriented about the axis, a tip defining an axially downstream end of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, and a cooling system. The cooling system comprises an air inlet formed within the structural wall, a first flow path disposed between the structural wall and the igniter wall, and an aperture extending through the igniter wall transverse to the flow direction. The aperture directly fluidly connects the first flow path to the combustion chamber.

IPC Classes  ?

  • F02C 7/264 - Ignition
  • F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
  • F23R 3/06 - Arrangement of apertures along the flame tube

15.

Torch injector systems for gas turbine combustors

      
Application Number 17127228
Grant Number 11286862
Status In Force
Filing Date 2020-12-18
First Publication Date 2022-03-29
Grant Date 2022-03-29
Owner Delavan Inc. (USA)
Inventor
  • Ryon, Jason
  • Prociw, Lev Alexander
  • Williams, Brandon P.

Abstract

A combustor system for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case and defining a main combustion chamber, a dome defining an upstream end of the main combustion chamber, and at least one torch injector attached to the dome of the main combustion chamber configured to inject combustion gases into the main combustion chamber. Each torch injector includes a torch injector housing defining and surrounding a torch combustion chamber configured to house a combustion reaction, an outlet passage defined by the torch injector housing, an electrothermal ignition source extending at least partially into the torch combustion chamber, and a fuel injector configured to inject fuel into the torch combustion chamber to at least partially impinge on the electrothermal ignition source and generate the combustion gases. The outlet passage directly fluidly connects the torch combustion chamber to the main combustion chamber.

IPC Classes  ?

  • F02C 7/266 - Electric
  • F23R 3/34 - Feeding into different combustion zones
  • F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
  • F02C 7/22 - Fuel supply systems

16.

High-pressure continuous ignition device

      
Application Number 17123778
Grant Number 11226103
Status In Force
Filing Date 2020-12-16
First Publication Date 2022-01-18
Grant Date 2022-01-18
Owner Delavan Inc. (USA)
Inventor
  • Ryon, Jason
  • Prociw, Lev Alexander
  • Williams, Brandon P.

Abstract

A torch ignitor system provides a continuous flame to ignite fuel within a combustor of a gas turbine engine. The torch ignitor system includes a torch ignitor, a housing, a flow channel, and an outlet nozzle. The torch ignitor system is configured to receive high-pressure air from the high-pressure compressor region of a gas turbine engine to increase operational characteristics of the torch ignitor system, including fuel atomization, cooling of the torch ignitor system, and circulation of combustion air within the torch ignitor system.

IPC Classes  ?

  • F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel
  • F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
  • F02C 3/04 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
  • F02C 7/264 - Ignition

17.

Fuel injector systems for torch igniters

      
Application Number 17127250
Grant Number 11209164
Status In Force
Filing Date 2020-12-18
First Publication Date 2021-12-28
Grant Date 2021-12-28
Owner Delavan Inc. (USA)
Inventor
  • Ryon, Jason
  • Prociw, Lev Alexander

Abstract

A fuel injector system for a torch igniter includes an injector body centered on an axis, a receiving aperture formed in a cap of the torch igniter, an injector aperture, an air channel, a fuel channel, and a purge passage formed in a housing of the torch igniter and fluidly connected to a cooling air source. The injector body includes an axial wall at a first axial end of the injector body, an outer wall connected to the axial wall and extending along the axis transverse to the first wall, and an inner portion connected to the axial wall and extending along the axis transverse to the axial wall. An outer surface of the inner portion is spaced a distance from an inner surface of the outer wall, forming an insulating space between the outer wall and the inner portion.

IPC Classes  ?

  • F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel
  • F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
  • F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
  • F02C 7/232 - Fuel valvesDraining valves or systems

18.

Tube joints, brazed tube joint assemblies, and methods of making tube joints

      
Application Number 15949737
Grant Number 11015745
Status In Force
Filing Date 2018-04-10
First Publication Date 2019-10-10
Grant Date 2021-05-25
Owner Delavan Inc. (USA)
Inventor
  • Clausen, Derrick
  • Myers, Steven J.
  • Heffernan, David

Abstract

A tube joint includes a first member and a second member. The first member has a bore defining an inner diameter. The second member has a first outer surface defining a first outer diameter with two or more helical protrusions extending radially from the first outer diameter. The two or more helical protrusions collectively define a second outer diameter. The second outer diameter of the second member is larger than the inner diameter of the first member by an amount sufficient to center and retain the second member within the bore of the first member. Brazed tube joint assemblies and methods of making brazed tube joints are also described.

IPC Classes  ?

19.

Hydraulic plug

      
Application Number 15887035
Grant Number 10746340
Status In Force
Filing Date 2018-02-02
First Publication Date 2018-08-23
Grant Date 2020-08-18
Owner DELAVAN INC. (USA)
Inventor
  • Cis, Marcin
  • Kiełbowicz, Dariusz

Abstract

A method of manufacturing a hydraulic plug. A shell with a circumferential wall, a sealed end, an open end and an axially extending cavity within is provided in which the cavity is defined by an internal surface with an inner diameter which narrows towards the open end. A head of an expander is inserted into the cavity, the expander further comprising a stem extending from the cavity for applying a tensile force (T) to the head. A sleeve is provided on a stem side of the head extending into the cavity, an end of the sleeve adjacent the head having an inner diameter which is less than a maximum outer diameter of the head. The sleeve is formed by expanding the sleeve by forcing the head into the end of the sleeve through urging the sleeve and/or expander towards the other in an axial direction.

IPC Classes  ?

  • F16L 55/132 - Means for stopping flow in pipes or hoses by introducing into the pipe a member expandable in situ introduced axially into the pipe or hose the closure device being a plug fixed by radially deforming the packing
  • F16L 55/13 - Means for stopping flow in pipes or hoses by introducing into the pipe a member expandable in situ introduced axially into the pipe or hose the closure device being a plug fixed by plastic deformation
  • F16J 13/14 - Detachable closure membersMeans for tightening closures attached exclusively by spring action or elastic action
  • F16J 13/12 - Detachable closure membersMeans for tightening closures attached by wedging action by means of screw-thread, interrupted screw-thread, bayonet closure, or the like
  • F16B 7/02 - Connections of rods or tubes, e.g. of non-circular section, mutually, including resilient connections with conical parts
  • F16B 19/10 - Hollow rivetsMulti-part rivets fastened by expanding mechanically

20.

Hydraulic plug

      
Application Number 15789201
Grant Number 10400932
Status In Force
Filing Date 2017-10-20
First Publication Date 2018-04-26
Grant Date 2019-09-03
Owner DELAVAN INC. (USA)
Inventor
  • Cis, Marcin
  • Sawicki, Piotr

Abstract

A method of manufacturing a hydraulic plug includes providing a shell comprising a circumferential wall, a sealed end, an open end and a cylindrical cavity opening to the open end is provided. The open end of the shell is wider externally than the sealed end. A head of an expander is inserted into the cavity. The head of the expander has a convex contact surface which is rounded in an axial direction (A) of the cavity. A region of the shell adjacent its open end is plastically deformed causing material from the circumferential wall of the shell to be displaced radially inward around the head of the expander to form a constricted opening retaining the expander within the cavity. The deforming reshapes an internal surface of the cavity from a cylindrical to a non-linear shaped ramp leading up to a constricted opening.

IPC Classes  ?

  • F16L 55/10 - Means for stopping flow in pipes or hoses
  • F16L 55/13 - Means for stopping flow in pipes or hoses by introducing into the pipe a member expandable in situ introduced axially into the pipe or hose the closure device being a plug fixed by plastic deformation
  • B65D 39/12 - Closures arranged within necks or pouring openings or in discharge apertures, e.g. stoppers expansible, e.g. inflatable

21.

Compensating for thermal expansion via controlled tube buckling

      
Application Number 15452345
Grant Number 10001280
Status In Force
Filing Date 2017-03-07
First Publication Date 2017-06-22
Grant Date 2018-06-19
Owner Delavan Inc. (USA)
Inventor Caples, Mark

Abstract

One embodiment includes a fuel injector for a gas turbine engine. The fuel injector has an inlet fitting for receiving fuel. The fuel injector also has an outlet fitting for delivering fuel through a nozzle to a combustor of the gas turbine engine. An injector support extends between the inlet fitting and the outlet fitting and has an internal bore therethrough. A fuel tube extends from the inlet fitting through the internal bore of the injector support to the outlet fitting. The injector support has a greater coefficient of thermal expansion than the fuel tube. At room temperature the fuel tube is under compressive stress such that the fuel tube is buckled. As a result of differential thermal expansion of the fuel tube and the injector support during engine operation the fuel tube is relieved of compressive stress.

IPC Classes  ?

  • F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply

22.

Retention feature for fuel injector nozzle

      
Application Number 14523587
Grant Number 09581121
Status In Force
Filing Date 2014-10-24
First Publication Date 2016-04-28
Grant Date 2017-02-28
Owner Delavan Inc. (USA)
Inventor
  • Ryon, Jason
  • Caples, Mark
  • Canny, John David
  • Nelson, Nicole L.

Abstract

A nozzle for a fuel injector can include an outer air swirler having an inner surface with the outer air swirler having a groove on the inner surface and a prefilmer located concentrically within the outer air swirler with the prefilmer having at least one detent finger to engage the groove on the inner surface of the outer air swirler. The nozzle can also include a fuel swirler located concentrically within the prefilmer and configured to convey fuel to a forward end of the nozzle with the fuel swirler having at least one tab extending axially at an aft end, and an inner air swirler having a cylindrical forward end located concentrically within the fuel swirler and an aft support extending radially outward to contact the outer air swirler with the cylindrical forward end contacting at least one tab of the fuel swirler to hold the fuel swirler in place.

IPC Classes  ?

  • F02M 61/18 - Injection nozzles, e.g. having valve-seats
  • F23D 11/24 - Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
  • F23D 11/38 - NozzlesCleaning devices therefor
  • F02M 61/16 - Details not provided for in, or of interest apart from, the apparatus of groups

23.

Swirl slot relief in a liquid swirler

      
Application Number 14329507
Grant Number 09625146
Status In Force
Filing Date 2014-07-11
First Publication Date 2016-01-14
Grant Date 2017-04-18
Owner DELAVAN INC. (USA)
Inventor
  • Myers, Steve
  • Ryon, Jason
  • Fogarty, Robert

Abstract

A swirler for inducing swirl on a liquid flow includes a swirler body defining a downstream end and an upstream end; a plurality of axial slots on an external surface of the swirler body, each of the plurality of axial slots having a slot entrance and a slot exit; and a slot relief at the slot exit. Each of the plurality of axial slots are helical and configured to impart swirl on the liquid flow as the liquid flow traverses through each of the slots.

IPC Classes  ?

  • B05B 7/10 - Spray pistolsApparatus for discharge producing a swirling discharge
  • F23D 11/38 - NozzlesCleaning devices therefor
  • B05B 1/34 - Nozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means designed to influence the nature of flow of the liquid or other fluent material, e.g. to produce swirl
  • F23D 11/10 - Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
  • F23D 11/24 - Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
  • F23R 3/30 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices

24.

Additive manufacture from machined surface

      
Application Number 14305522
Grant Number 10207325
Status In Force
Filing Date 2014-06-16
First Publication Date 2015-12-17
Grant Date 2019-02-19
Owner Delavan Inc. (USA)
Inventor
  • Zink, Gregory
  • Pack, Spencer
  • Donovan, Matt

Abstract

A method of additive manufacturing includes building a component having a top surface, attaching the component to a powder bed fusion plate that receives the component, filling the powder bed fusion chamber so the powder is flush with the top surface of the component, and adding a first layer of powdered metal level with the top surface of the component. The method of additive manufacturing also includes fusing the first layer of powdered metal to the top surface of the component to create a fusion joint, and building up an additively manufactured body from the top surface of the component in subsequent layers.

IPC Classes  ?

  • B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
  • B22F 3/24 - After-treatment of workpieces or articles
  • B22F 7/08 - 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 with one or more parts not made from powder
  • F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
  • F23D 11/38 - NozzlesCleaning devices therefor
  • B33Y 10/00 - Processes of additive manufacturing
  • B33Y 30/00 - Apparatus for additive manufacturingDetails thereof or accessories therefor

25.

Offset stem fuel distributor

      
Application Number 14158348
Grant Number 09689571
Status In Force
Filing Date 2014-01-17
First Publication Date 2015-07-16
Grant Date 2017-06-27
Owner DELAVAN INC. (USA)
Inventor
  • Ryon, Jason
  • Buelow, Philip

Abstract

A nozzle is provided including a fuel swirler having an outer wall, an interior wall, and a fuel flow path configured to receive a fuel flow. The fuel flow path extends from adjacent and inlet end of the nozzle to a discharge end of the nozzle and is arranged between the outer wall and the interior wall. The fuel flow path includes a first inlet portion and a volute. The first inlet portion is generally offset from a center of the fuel swirler.

IPC Classes  ?

  • F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
  • F23R 3/14 - Air inlet arrangements for primary air inducing a vortex by using swirl vanes
  • F23D 11/10 - Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour

26.

Compensating for thermal expansion via controlled tube buckling

      
Application Number 14147240
Grant Number 09625155
Status In Force
Filing Date 2014-01-03
First Publication Date 2015-07-09
Grant Date 2017-04-18
Owner Delavan Inc. (USA)
Inventor Caples, Mark

Abstract

One embodiment includes a fuel injector for a gas turbine engine. The fuel injector has an inlet fitting for receiving fuel. The fuel injector also has an outlet fitting for delivering fuel through a nozzle to a combustor of the gas turbine engine. An injector support extends between the inlet fitting and the outlet fitting and has an internal bore therethrough. A fuel tube extends from the inlet fitting through the internal bore of the injector support to the outlet fitting. The injector support has a greater coefficient of thermal expansion than the fuel tube. At room temperature the fuel tube is under compressive stress such that the fuel tube is buckled. As a result of differential thermal expansion of the fuel tube and the injector support during engine operation the fuel tube is relieved of compressive stress.

IPC Classes  ?

  • F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply

27.

Three-piece airblast fuel injector

      
Application Number 14191038
Grant Number 09574776
Status In Force
Filing Date 2014-02-26
First Publication Date 2015-04-23
Grant Date 2017-02-21
Owner Delavan Inc. (USA)
Inventor
  • Buelow, Philip
  • Nelson, Nicole L.

Abstract

A fuel system includes an external cool air source, and a fuel injector. The fuel injector includes a fuel circuit, an outer air circuit, an inner air circuit, and an outlet. The fuel circuit receives liquid fuel from a fuel inlet. The outer air circuit receives cool air from the cool air source and substantially surrounds the fuel circuit. The inner air circuit is in fluid communication with the outer air circuit and a portion of the fuel circuit substantially surrounds the inner air circuit. The outlet provides atomized fuel from the fuel circuit, outer air circuit and inner air circuit to a combustor.

IPC Classes  ?

  • F02M 53/08 - Injectors with heating, cooling, or thermally-insulating means with air cooling
  • F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
  • F01N 3/025 - Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust for cooling, or for removing solid constituents of, exhaust by means of filters using means for regenerating the filters, e.g. by burning trapped particles using fuel burner or by adding fuel to exhaust
  • F23D 11/10 - Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
  • F23D 11/38 - NozzlesCleaning devices therefor

28.

Active pattern factor control for gas turbine engines

      
Application Number 13477626
Grant Number 08483931
Status In Force
Filing Date 2012-05-22
First Publication Date 2012-10-04
Grant Date 2013-07-09
Owner Delavan Inc. (USA)
Inventor
  • Williams, Brandon Phillip
  • Goeke, Jerry Lee

Abstract

A method of actively controlling pattern factor in a gas turbine engine includes the steps of issuing fuel into a combustion chamber of a gas turbine engine through one or more circumferentially disposed fuel injectors, determining an initial circumferential pattern factor in the combustion chamber, and adjusting fuel flow through one or more selected fuel injectors based on the initial circumferential pattern factor, to yield a modified circumferential pattern factor in the combustion chamber. The step of determining the circumferential pattern factor can include the steps of detecting a chemiluminescent signature within the combustor, correlating the chemiluminescent signature to an equivalence ratio, and computing the initial circumferential pattern factor based on the equivalence ratio. Alternatively, the step of determining the circumferential pattern factor can include the steps of measuring temperatures at a plurality of circumferential positions at the combustor exit and computing the initial circumferential pattern factor based on the measured temperatures.

IPC Classes  ?

  • G06F 19/00 - Digital computing or data processing equipment or methods, specially adapted for specific applications (specially adapted for specific functions G06F 17/00;data processing systems or methods specially adapted for administrative, commercial, financial, managerial, supervisory or forecasting purposes G06Q;healthcare informatics G16H)

29.

Active pattern factor control for gas turbine engines

      
Application Number 13477509
Grant Number 08417434
Status In Force
Filing Date 2012-05-22
First Publication Date 2012-09-13
Grant Date 2013-04-09
Owner Delavan Inc (USA)
Inventor
  • Williams, Brandon Phillip
  • Goeke, Jerry Lee

Abstract

A method of actively controlling pattern factor in a gas turbine engine includes the steps of issuing fuel into a combustion chamber of a gas turbine engine through one or more circumferentially disposed fuel injectors, determining an initial circumferential pattern factor in the combustion chamber, and adjusting fuel flow through one or more selected fuel injectors based on the initial circumferential pattern factor, to yield a modified circumferential pattern factor in the combustion chamber. The step of determining the circumferential pattern factor can include the steps of detecting a chemiluminescent signature within the combustor, correlating the chemiluminescent signature to an equivalence ratio, and computing the initial circumferential pattern factor based on the equivalence ratio. Alternatively, the step of determining the circumferential pattern factor can include the steps of measuring temperatures at a plurality of circumferential positions at the combustor exit and computing the initial circumferential pattern factor based on the measured temperatures.

IPC Classes  ?

  • G06F 19/00 - Digital computing or data processing equipment or methods, specially adapted for specific applications (specially adapted for specific functions G06F 17/00;data processing systems or methods specially adapted for administrative, commercial, financial, managerial, supervisory or forecasting purposes G06Q;healthcare informatics G16H)

30.

FLEXURE SEAL FOR FUEL INJECTION NOZZLE

      
Application Number US2008076610
Publication Number 2009/039142
Status In Force
Filing Date 2008-09-17
Publication Date 2009-03-26
Owner DELAVAN INC (USA)
Inventor
  • Thomson, Neal, A.
  • Hall, Troy
  • Haggerty, Daniel
  • Caples, Mark

Abstract

A nozzle (40) includes an inlet at an upstream end of the nozzle, a discharge outlet at a downstream end of the nozzle, and a fluid delivery passage extending between the inlet and the discharge outlet. Exterior (210) and interior (208) walls of the nozzle (40) have downstream tip ends that are relatively longitudinally movable at one or more interfaces. An internal insulating gap (206b) is interposed between the interior and exterior walls to insulate fuel from ambient temperature conditions exterior to the nozzle. One or more flexible (222) seal structures internal to the nozzle isolate a portion of the insulating gap (206b) from any ambient fluid entering into the gap through the one or more interfaces while providing relative movement between interior and exterior walls of the nozzle.

IPC Classes  ?

  • F23D 11/38 - NozzlesCleaning devices therefor
  • F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply