Two-stage turbocharger for aviation piston engine

A technology of turbocharger and piston engine, applied in the direction of internal combustion piston engine, engine components, combustion engine, etc., can solve the problems of limited flying height of aircraft, increase the mass of the engine, occupy a large volume, etc., and achieve light weight and reduce stiffness. , good sealing effect

Inactive Publication Date: 2012-10-24
BEIHANG UNIV
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AI Technical Summary

Problems solved by technology

[0003] General aviation turbochargers usually use a single-stage supercharging form (1T1C) in which a turbine drives a compressor or a two-stage parallel connection form (1T1C+1T1C) in which two turbines drive two compressors respectively. The improvement is very limited, and the latter will significantly increase the mass of the engine while occupying a large volume, which is not conducive to high-altitude flight

Method used

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  • Two-stage turbocharger for aviation piston engine
  • Two-stage turbocharger for aviation piston engine
  • Two-stage turbocharger for aviation piston engine

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Embodiment Construction

[0028] The present invention will be further described in detail below in conjunction with the accompanying drawings.

[0029] Such as figure 1 Shown, a kind of 1T2C two-stage turbocharging device for aviation piston engine described in the present invention. Including rotor assembly 13, front support assembly 11, rear support assembly 9, turbine volute assembly 8, compressor casing 10,12.

[0030] Such as figure 2 As shown, the rotor assembly includes turbine shaft welded 1, high-pressure compressor impeller 4, low-pressure compressor impeller 6, and compression nut 7, each part is locked by the compression nut, and the turbine shaft is welded to the design of the turbocharger and assembly benchmarks. In order to increase the rigidity of the shaft, reduce vibration, and improve the dynamic characteristics of the rotor, the support scheme adopts the method of inner support. The main support is located between the turbine 1 and the impeller 4 of the high-pressure compressor...

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Abstract

The invention discloses a two-stage turbocharger for an aviation piston engine. The two-stage turbocharger comprises a rotor assembly, a front support assembly, a rear support assembly, a turbine volute, a high-pressure compressor casing, a low-pressure compressor casing and the like, wherein each part in the rotor assembly is locked through a compression nut, and respectively connected with the turbine volute and the compressor casings through bolts; the rear support assembly is of a thin-walled stainless steel soldering structure, and bearings are distributed in a back to back mode; and the compressor casings are of a combined mode, the low-pressure compressor casing is connected with the high-pressure compressor casing through a bolt, and is connected with a regulator assembly through a bolt. The two-stage turbocharger has the advantages that: the turbocharger has simple structure and light weight, and a structure that one turbine drives two compressors is adopted, so that the requirement of an aircraft for high-altitude flight is fulfilled, and the weight of the engine is effectively reduced. The two-stage turbocharger has the characteristics of high reliability and good sealing property, and fulfills the requirement of high-altitude sealing.

Description

technical field [0001] The invention relates to the technical field of turbocharging of aviation piston engines, in particular to a two-stage turbocharger for aviation piston engines. Background technique [0002] As the altitude increases, the atmospheric pressure decreases, the air density decreases, the oxygen content in the air decreases, and the average temperature decreases. As a result, the amount of air entering the engine decreases, and the power of the engine decreases. Turbochargers are installed on the aircraft to meet the requirements of high altitude, long endurance and flight reliability of the aircraft. [0003] General aviation turbochargers usually use a single-stage supercharging form (1T1C) in which a turbine drives a compressor or a two-stage parallel connection form (1T1C+1T1C) in which two turbines drive two compressors respectively. The improvement of the engine is very limited, and the latter will significantly increase the mass of the engine while ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02B37/00F02B39/00F02B39/14F01D25/12F01D25/16F04D25/04
CPCY02T10/144Y02T10/12
Inventor 杜发荣周煜丁水汀韩树军王昊尘
Owner BEIHANG UNIV
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