Device to transmit torque from compressor shaft to gas turbine engine auxiliaries

FIELD: aircraft engineering; gas turbine engines.

SUBSTANCE: invention relates to units of drives of gas-turbine engines of aircraft and ground application. Proposed device to transmit torque from compressor shaft to box of auxiliaries of gas-turbine engine includes spur gear wheel and bevel gear spaced and connected by seat surfaces and splines. Bevel gear is mounted on separate bearing support. Inductor is fitted in inner space of spur gear.

EFFECT: improved reliability of engine by provision of accurate signal from device checking frequency of rotation of compressor rotor.

1 dwg

 

The invention relates to drive units of gas turbine engines for aircraft and ground application.

A known design of aircraft gas turbine engine with the transmission of torque from the compressor shaft is a bevel gear to the bevel gear wheel center drive, transmitting torque to the pair of conical gears box drive units (WO 99/47799).

A disadvantage of the known construction is that the quality of the signal from the gauge of frequency of rotation of the rotor of the compressor affects the totality of all side joints in the kinematic chain in the area from gears associated with the sensor, to the rotor of the compressor, which in turn affects the operation of the fuel automation. This ultimately leads to unplanned changes in the operation of the engine.

Closest to the claimed design is the design of the Central drive of aircraft gas turbine engine, comprising an Assembly unit consisting of a cylindrical wheel and bevel gears, which are collected on landing surfaces, constricted between the nut and pass each other torque through the slots. ("Domestic aviation and rocket-space technology", Engine, aerospace, marine, industrial. 1944-2000, Moscow, AKS-Conversant", 2000, the section 3VR< "Progress", str - prototype).

A disadvantage of the known designs adopted for the prototype, is the lack of precision of the signal from the gauge of frequency of rotation of the rotor of the compressor. Actuator sensor is located in the tidal separation of body and affected by the combination of lateral joints in the kinematic chain from the gears, resulting in a rotation of the sensor to the rotor of the compressor.

The technical problem on which the invention is directed, is to increase the reliability of the gas turbine engine by providing a high precision signal from the device control rotor speed.

The essence of the technical solution lies in the fact that the device transmit torque from a shaft of the compressor to the box drive units gas turbine engine, comprising a cylindrical spur wheel and bevel gear, according to the invention the cylindrical wheel and bevel gear spaced apart, connected by planting surfaces and slots, with bevel gear is located on a separate bearing support, and the inner cavity of the cylindrical wheel mounted inductor.

The location of the bevel gear on a separate bearing support in the front centre drive, connecting with her on the landing surfaces of the slotted cylindrical wheel allows you to set the inner cavity of the wheel inducer. Work inductor located in the Central drive, eliminates the influence of backlash between the teeth of gear wheels box Central drive, spline gears and drive shafts on the quality of the signal from the speed sensors, which generally increases the reliability of the engine.

The drawing shows a device for torque transmission.

On the front part of the rotor shaft of the compressor 1 through the slots installed spur gear 2. In case 3 Central drive is spur gear wheel 4 on the bearing support 5 connected by landing surfaces 6 and slots 7 with a bevel gear 8 that is located on the bearing support 9. The wheel 4 and the gear 8 is tightened by a nut 10. Into the internal cavity 11 of the wheel 4 has a coil 12, which represents a gear wheel with straight-toothed profile. The inductor 12 is fixed on the toothed wheel 4 bolt 13 and nut 14. At some distance from the outer diameter of the ring gear of the gearbox are the sensors of the speed control 15.

The device operates as follows. The rotor of the compressor 1 through the gear 2 rotates the gear wheel 4 with the inductor 12. During the rotation of the inductor 12, the teeth of the inductor to induce the sensors control the frequency of rotation 15 of the inductive signal, which is then registered motor and then the on-Board systems of the aircraft. the case of load fluctuation in the kinematic chain from the gear wheels of the box to the intermediate wheel 4 with the inductor 12 of the Central drive of the inductor does not feel the County fluctuations and the quality of the signal from the sensor 15 provides reliable operation of the engine.

Device transmit torque from a shaft of the compressor to the box drive units gas turbine engine, comprising a cylindrical spur wheel and bevel gear, wherein the cylindrical wheel and bevel gear spaced apart and connected by planting surfaces and slots, with bevel gear is located on a separate bearing support, and the inner cavity of the cylindrical wheel mounted inductor.



 

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