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radial multistage turbine engine

A turbine engine and turbine technology, which is applied in the direction of machines/engines, gas turbine devices, mechanical equipment, etc., can solve the problems of difficult manufacturing, poor low-speed performance, and slender structure, and achieve good high-low speed performance, large jet torque, and reduced pressure. The effect of small manufacturing difficulty

Active Publication Date: 2017-04-12
张耀明
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  • Application Information

AI Technical Summary

Problems solved by technology

Due to its slender structure and high speed, the axial multi-stage turbine engine is very suitable for use on aviation machinery, but not suitable for general large-scale machinery and transportation vehicles. In addition, because the blades must have a certain twist from the blade root to the blade tip, It has the disadvantages of high manufacturing difficulty, high cost, and poor low-speed performance

Method used

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Embodiment Construction

[0012] Describe embodiment in detail in conjunction with accompanying drawing, the present invention is on a main shaft 12 near the output end and is fixed with a compressor motor disk 7 with key, is provided with air intake passage 13 around main shaft on this disk, on the two disk surfaces of this disk Along the radial direction from inside to outside, there are multi-stage moving blades 6 installed step by step. On the main shaft, an outer static disk 10 of the compressor is installed in cooperation with the output end of the moving disk, and on the other side of the compressor moving disk. A compressor inner static disk 14, on the two compressor static disks are respectively provided with compressor static vanes 9 which are matched with the gaps between the compressor motor blades, and on the compressor outer static disk at the output end of the main shaft is provided with a ring diameter larger than the intake passage The air inlet 11 of the air inlet 11 is installed with ...

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Abstract

The invention discloses a radial multistage turbine engine which is characterized in that an air compressor moving disc is fixed on a main shaft; an air inlet passage is formed in the air compressor moving disc and surrounds the main shaft; multistage moving blades are mounted on two disc surfaces in the radial direction from inside to outside in a step-by-step shortened manner; an air compressor outer stator disc is arranged on the main shaft and is in sealing normal running fit with the air compressor moving disc; an air compressor inner stator disc is rotationally mounted on the other side of the air compressor moving disc; air compressor stator blades in clearance fit with the air compressor moving blades are arranged on the two stator discs respectively; an air inlet is formed in the air compressor outer stator disc; a turbine inner stator disc is rotationally mounted on the main shaft behind the air compressor inner stator disc; a turbine outer stator disc is rotationally mounted at the rear end of the main shaft; a turbine is internally provided with a combustion chamber; a circle of arc sealing wall is connected between the turbine inner stator disc and the circumference wall of the air compressor outer stator disc; a high-pressure air inlet passage is formed in a turbine moving disc and surrounds the main shaft; and moving blades and stator blades are mounted among the turbine moving disc, the turbine outer stator disc and the turbine inner stator disc. The manufacturing cost is reduced.

Description

[0001] Technical field: [0002] The invention relates to an engine, in particular to a radial multi-stage turbine engine suitable for installation and use on various machines. [0003] Background technique: [0004] Most of the existing turbine engines are axial multi-stage structures, and those with radial structures are also radial single-stage structures. Due to its slender structure and high speed, the axial multi-stage turbine engine is very suitable for use on aviation machinery, but not suitable for general large-scale machinery and transportation vehicles. In addition, because the blades must have a certain twist from the blade root to the blade tip, It has the disadvantages of high manufacturing difficulty, high cost and poor low-speed performance. [0005] Invention content: [0006] The purpose of the present invention is to provide a radial multi-stage turbine engine with simple structure, low cost and suitable for use on various machines. [0007] The technical...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C3/055
Inventor 张耀明
Owner 张耀明
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