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Micro engine impeller disc with centrifugal compressor and turbine blades integrated

A technology of turbine blades and compressors, which is applied in the direction of machines/engines, liquid fuel engines, engine components, etc., can solve the problems of reducing the size of the turbine engine and the overall size limit of the turbojet engine, and achieve the improvement of rotor rotation accuracy and vibration stability , the axial length is reduced, and the effect of increasing the service life

Pending Publication Date: 2020-06-26
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In microturbine engines, centrifugal compressors and centripetal turbines are often used to obtain greater working capacity and reduce the size of the turbine engine. However, due to the inherent limitations of its own structure, the overall size of the turbojet engine is still limited.

Method used

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  • Micro engine impeller disc with centrifugal compressor and turbine blades integrated
  • Micro engine impeller disc with centrifugal compressor and turbine blades integrated
  • Micro engine impeller disc with centrifugal compressor and turbine blades integrated

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Embodiment Construction

[0017] The present invention will be further described now in conjunction with accompanying drawing:

[0018] combine figure 1 , figure 2 , image 3 , The invention provides a micro-engine impeller disc structure in which a centrifugal compressor and turbine blades are integrated. figure 1 It is an overall schematic diagram of a micro-engine impeller disc integrating a centrifugal compressor and a turbine blade, figure 2 Side view of a micro-engine wheel disc integrated with centrifugal compressor and turbine blades, Figure three A cutaway view of a turbine blade.

[0019] After the engine is started by the front starter motor, the air flows through the intake duct and is figure 1 (2) The centrifugal compressor compresses from figure 2 (3) The flow channel in the turbine blade flows out, and the compressed air passes through the annular return combustion chamber to form high-temperature and high-pressure gas, and at the same time, part of the air flow is figure 1 (5...

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Abstract

The invention provides a micro engine impeller disc with a centrifugal compressor and turbine blades integrated. The centrifugal compressor and an axial flow type turbine are adopted for obtaining thelarger compressor pressure ratio and the higher gas expansion work doing capacity, meanwhile, the aim of reducing the size of a turbine engine is achieved, the air flow entering the centrifugal compressor from an air inlet way is compressed through the centrifugal compressor to enter a backflow type combustion chamber, gas combusted through the backflow type combustion chamber does work for axialturbine blades, a spindle between the compressor and the turbine is omitted, the axial size of the engine is reduced, the mass of the engine is reduced, rotor imbalance torque borne by the engine iseliminated, and stability of the engine is greatly improved.

Description

technical field [0001] The invention belongs to the field of micro gas turbine engines, and relates to a micro engine impeller disk integrated with a centrifugal compressor and turbine blades. Background technique [0002] With the recent rapid development of the aerospace field, various micro-aircraft have been widely used and developed rapidly in the modern military field, and they will continue to play an important role in electronic air warfare, precise concealed reconnaissance, ground precision strikes, and environmental monitoring. important role. Its power unit micro-turbine has the characteristics of large thrust-to-weight ratio, small volume, compact structure, short development cycle, and low cost. In order to ensure more advanced technology in this field, more and more attention has been paid to the research and development of micro-turbine engines at home and abroad, and it has gradually developed into a new field of aero-engines. [0003] In microturbine engin...

Claims

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Application Information

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IPC IPC(8): F02C3/05F04D17/10F04D29/28F04D29/30F01D5/04F01D5/18F01D5/14
CPCF02C3/05F04D17/10F04D29/284F04D29/30F01D5/048F01D5/186F01D5/147
Inventor 张群程祥旺胡凡李小龙
Owner NORTHWESTERN POLYTECHNICAL UNIV