FIELD: engine building.
SUBSTANCE: invention relates to gas turbine engines with a free power turbine for aviation and ground applications. Free power turbine includes a roller bearing, the inner ring of which is fixed in an axial position by a nut, and an air labyrinth seal with a labyrinth ring and a stator flange of the labyrinth. Between the inner ring and the cylindrical surface of the shaft there is an intermediate roller bearing bushing with a radial shaft, directed to the nut, annular rib whose inner surface is an alternation of planar and cylindrical surfaces with the contact of flat surfaces of the sleeve along the flat outer surfaces of the shaft, outer surface of the annular rib is cylindrical, with the axial rib of the locking sleeve placed on it, which is made with an edge directed to the axis of the shaft, which is also made with an inner surface of alternating planar and cylindrical surfaces with the contact of the flat surfaces of the locking bush on the flat outer surfaces of the shaft, on the intermediate sleeve between the inner ring of the roller bearing and the locking bushing there is a labyrinth ring, forming with the stator flange a labyrinth seal with a central air annular cavity connected at the inlet to the inner air cavity of the shaft, and at the output – through a multitude of labyrinth scallops with the air cavity of the gas turbine engine and through a single labyrinth scallop and through a C-shaped slotted air cavity formed by the cylindrical part of the stator flange and covering it with the front part of the labyrinth ring with conical internal surfaces – with the oil cavity of the turbine.
EFFECT: thanks to the present invention, the reliability of a gas turbine engine is improved by eliminating stress raisers on the motor shaft when fixing the roller bearing nut in the circumferential direction, and also the leakage of oil from the oil cavity of the engine to the air in all modes of engine operation is excluded.
1 cl, 5 dwg
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| POWER TURBINE | 2016 |
|
RU2654156C1 |
| GAS-TURBINE ENGINE BEARING SUPPORT | 2001 |
|
RU2215886C2 |
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|
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| TURBOJET ENGINE ROTOR SHAFT SUPPORT (VERSIONS), TURBOJET ENGINE ROTOR SHAFT SUPPORT BODY, JET TURBINE ENGINE ROTOR SHAFT SUPPORT ROLLER BEARING HOUSING, TURBOJET ENGINE ROTOR SHAFT SUPPORT SEALING STAGES | 2015 |
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| LOW-PRESSURE COMPRESSOR OF GAS TURBINE ENGINE OF AVIATION TYPE | 2016 |
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|
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| ROTOR SHAFT BEARING OF LOW-PRESSURE COMPRESSOR OF TURBOJET ENGINE (VERSIONS), SEALING SPOOL OF ROTOR SHAFT BEARING, ROTOR SHAFT BEARING BLOCK, CONTACT HUB OF ROTOR SHAFT BRACELET SEALING, OIL-CONTROL RING OF ROTOR SHAFT | 2016 |
|
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| ROTOR SHAFT BEARING OF LOW-PRESSURE COMPRESSOR OF TURBOJET ENGINE (VERSIONS), CYLINDER CONSTITUENT OF ROTOR SHAFT, EXTERNAL TIGHTENING COMPONENT OF ROTOR SHAFT | 2016 |
|
RU2614018C1 |
