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Turbine stator top sealing limit structure with vane type wire groove

A turbine stator and blade profile technology, applied in the direction of machines/engines, leakage prevention, mechanical equipment, etc., can solve problems such as insufficient sealing ability and blade tip leakage loss, to control leakage loss, reduce clearance leakage, The effect of improving structural reliability

Active Publication Date: 2021-10-19
XIAN AEROSPACE PROPULSION INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The technical problem of the present invention is: in order to overcome the shortcomings of existing stator limiting rings, such as blade top leakage loss and insufficient sealing ability, provide a turbine stator blade top sealing and limiting structure with blade-shaped wire slots, which is simple in production and processing, easy assembly

Method used

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  • Turbine stator top sealing limit structure with vane type wire groove
  • Turbine stator top sealing limit structure with vane type wire groove
  • Turbine stator top sealing limit structure with vane type wire groove

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Embodiment Construction

[0021] The invention proposes a sealing and position-limiting structure at the top of a turbine stator with blade-shaped wire slots, which is a new scheme for improving the sealing and position-limiting capability of the top of the turbine stator. Such as figure 1 As shown, the sealing and limiting structure at the top of the turbine stator includes a casing 1 , a sealing and limiting ring 2 and a turbine stator 3 .

[0022] The casing 1 is a hollow structure, and the inner wall is provided with annular steps. The trailing edge and leading edge of the turbine stator 3 blades are processed with steps of the same height. The turbine stator 3 is loaded from the entrance of the casing 1. The ring-shaped step fit in the body 1 limits the movement of the turbine stator 3 to the outlet. The shell 1 and the top of the turbine stator 3 are radially matched with a small gap, and the fit gap is less than 0.03mm; then push the sealing limit ring 2, The sealing limit ring 2 has a groove c...

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Abstract

The invention discloses a sealing and limiting structure at the top of a turbine stator with blade-shaped wire grooves, which comprises a casing, a turbine stator arranged in the casing, and a sealing and limiting ring with a sealing function; the turbine stator is connected with the casing, The step on the housing cooperates with the step on the trailing edge of the turbine stator blade, which restricts the movement of the turbine stator to the outlet side; the sealing limit ring is processed with a groove consistent with the shape of the turbine stator blade, and is pushed into the casing from the inlet side. And cooperate with the front edge step of the blade to limit the movement of the turbine stator to the inlet side; the sealing limit ring limits the circumferential movement of the turbine stator under the action of the air flow force; due to the sealing limit ring groove and the turbine stator blade surface It is a very small clearance fit with consistent profiles, which can effectively reduce the leakage of the top clearance of the blade and improve the performance of the turbine.

Description

technical field [0001] The invention relates to a sealing and position-limiting structure at the top of a turbine stator with blade-shaped wire slots, which can be applied to combined engines of aviation, spaceflight and near space. Background technique [0002] Multi-stage turbines are widely used in the fields of aviation, aerospace and near-space combined engines. Under the requirements of large thrust-to-weight ratio design indicators and high-performance and high-efficiency requirements of the engine, it can meet the assembly requirements of turbine parts and reduce the gap between turbine assembly parts. Interstitial flow leakage is of great significance to the development of high-performance engines. In order to realize the production and assembly of multi-stage turbines, a split structure is often used to realize the assembly of the shell and the stator. The production and processing are complicated and the assembly is difficult. Another solution is to use a limit r...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D25/24F01D25/28F01D11/00
Inventor 张鹏飞许开富朱东华贾少锋任众严俊峰王文廷
Owner XIAN AEROSPACE PROPULSION INST
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