Blade hole type prewhirl nozzle for prewhirl cooling system

A pre-rotating nozzle and cooling system technology, which is applied to the cooling of the engine, the cooling of the turbine/propulsion device, engine components, etc., can solve the problems of difficult processing and installation, and poor applicability of nozzle engineering, so as to achieve easy design and Machining, guarantee of acceleration and deflection performance, effect of small flow loss

Inactive Publication Date: 2015-12-02
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to improve the performance of the pre-swirling nozzle and overcome the problems of poor engineering applicability and difficult proces

Method used

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  • Blade hole type prewhirl nozzle for prewhirl cooling system
  • Blade hole type prewhirl nozzle for prewhirl cooling system
  • Blade hole type prewhirl nozzle for prewhirl cooling system

Examples

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Embodiment Construction

[0020] This embodiment is a leaf hole type pre-swirl nozzle used in a pre-swirl cooling system. The leaf-hole pre-swirl nozzle is a kind of oblique holes distributed on the nozzle ring at equal intervals, and its inclination angle is the pre-swirl angle.

[0021] refer to Figure 1 ~ Figure 3 , the leaf-hole pre-swirl nozzle of the pre-swirl cooling system is composed of blade pressure surface 1, blade suction surface 2, nozzle flow channel 3, pre-swirl nozzle outlet 4, and blade-shaped solid block 5; the blade pressure surface 1 and blade suction surface 2. Form oblique orifice flow passages deflected along the circumferential direction at equal intervals on the nozzle ring. The deflection surface of the nozzle flow passage 3 becomes tapered, and the minimum throat area is reached at the outlet 4 of the pre-rotation nozzle. The pre-rotation angle is 10-30°. Blade-shaped solid blocks 5 are arranged between adjacent flow channels of the leaf-hole pre-swirling nozzle, and the ...

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Abstract

The invention discloses a blade hole type prewhirl nozzle for a prewhirl cooling system, and belongs to the field of application of aero-engine prewhirl cooling systems. The blade hole type prewhirl nozzle is characterized in that a blade pressure face and a blade suction face are adopted for forming inclined hole runners deflecting in the circumferential direction of a nozzle ring at equal intervals, deflecting molded faces of the nozzle runners are in a gradually-contracted shape, a minimum laryngeal area is achieved at an outlet of the prewhirl nozzle, the accelerating performance and the deflecting performance of the prewhirl nozzle are effectively guaranteed, and the flowing loss of a main flow is small. Blade type solid blocks are distributed between adjacent runners of the prewhirl nozzle, under the condition that the laryngeal area of the nozzle is definite, the ratio of the blade height to the pitch of the prewhirl nozzle can be flexibly adjusted by additionally arranging the blade type solid blocks, and the long and narrow performance of the sections of the runners is effectively improved, so that the secondary flow loss of the end walls in the runners is reduced, the flow coefficient and the prewhirl efficiency of the prewhirl nozzle are improved, and the system temperature drop effect is further improved.

Description

technical field [0001] The invention relates to the application field of an aero-engine pre-swirl cooling system, in particular to a leaf-hole type pre-swirl nozzle used for the pre-swirl cooling system. Background technique [0002] In recent years, the technology of aero-engine is changing with each passing day, and the performance of the engine has been greatly developed. The main way to improve engine performance is to increase the temperature before the turbine and the boost ratio, but the increase in the temperature before the turbine seriously deteriorates the working environment of high-temperature components such as the turbine in the engine, resulting in poor reliability and shortened life of the engine. The current cooling technologies for turbine blades include film cooling, internal impingement cooling, spoiler column enhanced heat transfer, rib enhanced heat transfer, and combinations thereof. Although the blade cooling technology has made great progress, the ...

Claims

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Application Information

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IPC IPC(8): F02C7/14
Inventor 刘高文刘育心孔晓治冯青吴衡
Owner NORTHWESTERN POLYTECHNICAL UNIV
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