Abrégé

The present invention relates to the technical field of flame holders in turbine engine afterburners. Disclosed are an adjustable combined flame stabilizing device suitable for a turbine engine, which aims to solve the technical problems of thrust losses in the non-afterburning states, poor performance of wide-range combustion operations and the like of high-performance aero-turbine engine afterburners in the prior art. The adjustable combined flame stabilizing device comprises a diffuser, a cavity on-duty flame holder and a radial flame holder. The diffuser comprises an outer wall and an inner cone located in the outer wall, and the cavity on-duty flame holder is connected to the outer wall. A rotation structure is arranged on the outer wall, the rotation structure extends into the cavity on-duty flame holder, and the radial flame holder is arranged at the bottom of the rotation structure. The present invention adjusts the blockage ratio by means of adjusting the inclination angle and the length of a radial flame holder, thereby reducing thrust losses in the non-afterburning states and achieving efficient wide-range combustion operations in afterburning states of turbine engines.

Classes IPC  ?

• F23R 3/00 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux
• F23R 3/22 - Moyens de stabilisation de la flamme, p. ex. accroche-flamme de postcombustion d'ensembles fonctionnels à propulsion par réaction mobiles, p. ex. vers une position inopéranteMoyens de stabilisation de la flamme, p. ex. accroche-flamme de postcombustion d'ensembles fonctionnels à propulsion par réaction réglables, p. ex. autoréglables

Abrégé

The present invention relates to the technical field of aeroengines, and disclosed is an air-bleed mechanism for a turbine engine, which solves the problem that existing air-bleed mechanisms for turbine engines can hardly meet the requirements of aircrafts on the size envelope and weight limit of the turbine engines. The air-bleed mechanism for the turbine engine comprises a static sealing ring integrated on the outer side of an engine casing; the static sealing ring has an inclined surface; a plurality of exhaust holes are formed on the inclined surface; the exhaust holes keep off blades inside the engine casing and are evenly distributed on the inclined surface; a movable sealing ring is attached to the outer side of the static sealing ring; axial end surfaces at the joint between the inclined surfaces of the static sealing ring and the movable sealing ring are connected and locked by means of an axial baffle; an actuating device is connected to the axial baffle; and a sealing structure is connected between the movable sealing ring and the sealing static ring. Under the condition of a same volume of bleed air, compared with conventional air-bleed mechanisms, the air-bleed mechanism of the present application significantly reduces the impact on the envelope radius and overall weight of an engine, and the air-bleed mechanism has a simple structure, high reliability, and low cost.

Classes IPC  ?

• F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
• F01D 25/30 - Têtes d'évacuation, chambres ou parties analogues
• F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages

Abrégé

A high-rotation-speed oil-gas separator for a turbine engine, the oil-gas separator comprising a hollow rotating shaft (77), wherein the upper portion of the rotating shaft (77) is provided with an oil input cavity assembly; the upper middle portion of the rotating shaft (77) is provided with a separation cavity assembly; and the lower portion of the rotating shaft (77) is provided with a driving mechanism. The separation cavity assembly comprises: a separator cavity (12) located on the periphery of the upper middle portion of the rotating shaft (77); a partition layer, which is located in the middle portion of the rotating shaft (77) in the separator cavity (12); a first centrifugal disc (19) located on the upper portion of the partition layer; a second centrifugal disc (20) located on the lower portion of the partition layer; a plurality of first through holes (21) located on the periphery of the first centrifugal disc (19); a plurality of second through holes (22) located on the periphery of the second centrifugal disc (20); an oil guide groove (17) that is located in the separator cavity (12) and is in communication with the plurality of first through holes (21); and an oil outlet (12a) that is located in the separator cavity (12) and is in communication with the oil guide groove (17). A gas outlet (7a) is provided at the bottom portion of the rotating shaft (77). The high-rotation-speed oil-gas separator is self-powered for driving, is not affected by the working condition of an engine, has high separation efficiency and can satisfy the volume and weight of a high-rotation-speed turbine engine.

Classes IPC  ?

• F01D 25/18 - Systèmes de lubrification
• F02C 7/06 - Aménagement des paliersLubrification