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Centripetal impeller for gas turbine engine

A gas turbine and engine technology, applied in liquid fuel engines, engine components, machines/engines, etc., can solve the problems of short life, centripetal impeller centrifugal and high thermal load, high stress, etc., to extend life, reduce stress, Processing simple effects

Active Publication Date: 2013-09-18
CHINA AVIATION POWER MACHINE INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to provide a centripetal impeller of a gas turbine engine to solve the technical problems of the centripetal impeller, such as high centrifugal and thermal loads, high stress, and short service life.

Method used

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  • Centripetal impeller for gas turbine engine
  • Centripetal impeller for gas turbine engine
  • Centripetal impeller for gas turbine engine

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Embodiment Construction

[0033] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in many different ways defined and covered by the claims.

[0034] figure 1 It is one of the structural schematic diagrams of the centripetal impeller of the gas turbine engine in the preferred embodiment of the present invention; figure 2 It is the second structural diagram of the centripetal impeller of the gas turbine engine in the preferred embodiment of the present invention, as figure 1 , 2 As shown, the gas turbine engine centripetal impeller includes a disc 1 and blades 2, the blades 2 are arranged on the surface of the disc 1, and the blades 2 extend to the rim 3 outside the disc 1, and the feature is that the wheel on the back of the blade 2 The disc 1 is provided with a weight-reducing groove 4, and the weight-reducing groove 4 includes at least two arc surfaces. The weight-reducing groove 4 i...

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Abstract

The invention discloses a centripetal impeller for a gas turbine engine, which comprises an impeller disk (1) and blades (2). The blades (2) are arranged on the surface of the impeller disk (1), and extend to a rim (3) outside the impeller disk (1); the impeller disk (1) at the backs of the blades (2) is provided with a pocket (4); at least two circular arc surfaces are formed in the pocket (4). The pocket is processed at the position at the back of the impeller to reduce a centrifugal load borne by an impeller center so as to reduce stress. Due to the structural characteristics of the centripetal impeller, the pocket cannot be excessively deep dug and the fillet radius also cannot be excessively large; the adoption of a multi-section circular arc structure of the pocket can effectively solve the problem of limitation of the fillet radius; aiming at the pocket, the multi-section circular arc structure is adopted, a large circular arc radius is adopted in a region with a large stress and a small circular arc radius is adopted in a region with a small stress. According to the novel structure, the stress can be greatly reduced in a small space range and service life is prolonged.

Description

technical field [0001] The invention relates to the technical field of gas turbine engines, in particular, to a centripetal impeller of a gas turbine engine. Background technique [0002] The centripetal impeller has the advantages of high falling pressure ratio, strong working ability, high performance under small flow rate, few parts, and low manufacturing cost. At present, it has been widely used in small and medium-sized aviation power auxiliary devices and turbo pumps for rockets. and automotive turbochargers. [0003] The working speed of the centripetal impeller is relatively high, generally above 50,000r / min, and the radius of the flow channel is relatively large, and the centrifugal load is large; in addition, as the hot end part of the turbine, its working temperature is relatively high, and the working temperature of the current advanced centripetal impeller is generally at 700 ° C or above. Based on the above two reasons, the centrifugal and thermal loads of t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/02F01D5/14F01D5/30F04D29/26
Inventor 米栋钱正明张志佾
Owner CHINA AVIATION POWER MACHINE INST
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