RU26327U1 - BIOTATIVE TURBINE - Google Patents

Description

2602lT4799

2 no 2 I

MKI: FOlDl / 26

BIOTATIVE TURBINE

The proposed birobotative turbine relates to aircraft engine manufacturing and can be used to directly drive double-row rotational fans of opposite rotation in promising turbofan engines (TVVD).

An analogue of the proposed utility model is the GE36 biotational turbine of the demonstration fuel-injection engine manufactured by General Electric, USA (AIAA Paper No. 85-1190). The twin-rotor analog turbine - internal and external rotors provide retention and drive, respectively, of the rear and front rotor fans located directly above the turbine. Each rotor has 6 blade crowns with working blades, and each blade crown of one rotor acts as a nozzle apparatus for the crown of the other rotor located behind it. The direct drive of the fan fans eliminates the gearbox, which simplifies the design and removes restrictions on the maximum power of a high pressure fuel pump. However, the location of the fan fans in the rear of the GE36 engine nacelle may not be acceptable under the engine layout conditions. by plane.

The closest technical solution of the claimed useful mode.ga1 is a biotic turbine according to US patent No. 2318990 according to CL 415-64 from 1943. The turbine is designed for direct drive of an electric current generator. Torque from the external rotor is transmitted to the shaft through the last crown of the working blades. This is due to the fact that the temperature of the gas stream decreases in the turbine from inlet to outlet, and the blades

the last crown are subject to heating to the least degree, which is important from the point of view of strength. However, this design has a low stiffness of the external rotor, which can lead to unacceptable vibrations in some engine operating modes.

The proposed design of the birotational turbine differs from that described by the presence of an additional support in the front of the external rotor, designed to increase its rigidity. An increase in the stiffness of the rotor increases its own vibrational frequencies and moves them beyond the frequency limits of the exciting vibrations acting in the engine.

The device of the proposed birotative turbine is shown schematically in the figure. The turbine in the figure includes the internal rotor 1, the blades

2 of internal rotor 1, shaft 10 and disk 11 of internal rotor 1, main support 12 of internal rotor 1, external rotor 3, rotor blades 4 of external rotor 3, shaft 5 and disk 6 of external rotor 3, main support 13 of external rotor 3, additional bearing support 7, additional support disk 8, housing 9.

The operation of the turbine shown in the figure is as follows. Under the action of gas-dynamic forces acting in the circumferential direction on the working blades 2 of the inner rotor 1 and the working blades 4 of the outer rotor 3, both rotors rotate in opposite directions. The torque and axial force from the rotor blades 2 of the internal rotor 1 are transmitted through the disk And to the shaft 10 installed in the main support 12. The torque and axial force from the rotor blades 4 of the external rotor 3 are transmitted to the shaft 5 through the last crown of the blades 4 and installed in the main support 13. Supports 12 and 13 are installed in the housing 9. The front crown of the working blades 4 of the external rotor 3 is connected via an additional disk 8 to the additional support 7 installed in the housing 9. The external rotor

3 with an additional support 7 and a disk 8 has a higher rigidity compared with the rotor of the prototype.

The technical solution proposed in this utility model, which allows avoiding the occurrence of low-frequency vibrations of the external rotor of the biotational turbine, opens up the prospect of creating powerful high-pressure fuel assemblies with a front-mounted fan heater.

Claims (1)

Birobative turbine, mainly for a gas turbine engine, comprising a housing, internal and external rotors with their working blades, disks and shafts, characterized in that the front row of working blades of the external rotor is connected through an additional supporting disk to an additional bearing support installed in the housing.