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Aeroengine Turbine Blade Cooling Test Sealing Structure

A technology for aero-engines and turbine blades, which is applied to the sealing of engines, engine components, mechanical equipment, etc., can solve the problems that the sealing structure of the bleed air tube cannot achieve zero leakage, and the bleed air tube cannot achieve sealing, so as to ensure the elastic sealing characteristics, Improve efficiency and ensure effectiveness

Active Publication Date: 2019-12-20
AECC SHENYANG ENGINE RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0017] 1. The sealing structure of the existing bleed pipe cannot achieve zero leakage
[0019] 2. The sealing structure of the existing bleed pipe cannot realize the sealing problem at high temperature

Method used

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  • Aeroengine Turbine Blade Cooling Test Sealing Structure
  • Aeroengine Turbine Blade Cooling Test Sealing Structure
  • Aeroengine Turbine Blade Cooling Test Sealing Structure

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Embodiment Construction

[0095] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention.

[0096] It should be noted that: in the drawings, the same or similar symbols represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of the present invention, but not all of the embodiments. In the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0097] In describing the present invention, it is to be understood that...

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Abstract

The invention relates to the technical field of turbine blade tests, and particularly provides a cooling test sealing structure for aero-engine turbine blades. Three circular sealing sheets are adopted to divide sealing gum to be in two-stage sealing, and bolts and nuts are used for fixing and compressing the circular sealing sheets. In this way, a gas guide pipe and a testing guide line can be sealed completely, and the safety coefficients of the sealing structure are increased. In order to prevent the sealing gum from losing efficacy at a high temperature, active thermal insulation and effective cooling measures are taken for the sealing gum, the effect that the sealing gum is within a specified operating temperature range is guaranteed, the sealing gum can achieve the characteristic ofelastic sealing, and thus the gas guide pipe and the testing guide line can be sealed completely at different gas temperatures (the swelling amounts of the blades are different).

Description

technical field [0001] The invention relates to the technical field of turbine blade testing, in particular to a sealing structure for the cooling test of an aeroengine turbine blade. Background technique [0002] The cooling effect test of aero-engine turbine blades is an indispensable verification test in the development of aero-engines at home and abroad. At present, the cooling effect test of turbine blades is generally carried out on the ground test bench. The cooling effect test of the turbine blade is carried out on a specially designed cooling effect test device. Generally, 5 to 7 blades are selected to form a fan-shaped channel for the test cascade, of which the middle one is the main test blade, and the rest are foil blades. During the test, the cooling air is passed through. . Due to the high temperature of the gas, the inlet and exhaust sections of the test adopt a double-layer water-cooled structure. In order to facilitate disassembly and assembly and realize...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F16J15/06
CPCF16J15/06
Inventor 谢建文张树林张健姣吕颂张涛
Owner AECC SHENYANG ENGINE RES INST