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Control method of titanium alloy compressor tip clearance

A technology of blade tip clearance and control method, applied in mechanical equipment, engine components, machines/engines, etc., can solve problems such as burning out aircraft equipment, aircraft crashes, etc., to reduce gas leakage rate, improve efficiency, and coating thickness distribution. low impact effect

Inactive Publication Date: 2020-03-24
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Abstract
  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

If the flame continues to spread out, it will burn through the outer titanium alloy casing and engine nacelle, burn out other systems of the aircraft, and eventually lead to a plane crash

Method used

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  • Control method of titanium alloy compressor tip clearance
  • Control method of titanium alloy compressor tip clearance
  • Control method of titanium alloy compressor tip clearance

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Experimental program
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Effect test

Embodiment Construction

[0026] Such as figure 1 , 2 As shown, the abradable sealing coating NiCrFeAl-BN is prepared by plasma spraying method on the inner wall of the casing, and the specific preparation process is as follows:

[0027] 1) Parts cleaning: Use absorbent cotton or a brush dipped in acetone to carefully wipe and clean the sprayed area and adjacent areas of the parts to completely remove the oil on the surface of the parts.

[0028] 2) Protection: Use protective tooling and high-temperature protective tape to shield and protect the non-sprayed areas of the parts. After the protection is completed, a second confirmation is required to ensure that there is no leakage or over-protection.

[0029] 3) Sand blowing: put the parts into the sand blowing machine, and ensure that the clamping position of the parts is correct and firm. After stabilization, perform sand blowing on the spraying area; after the sand blowing is completed, use compressed air to blow off the floating dust on the surface...

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Abstract

The invention aims to provide a control method of a titanium alloy compressor tip clearance. The control method is characterized in that an abradable sealing coating is sprayed on the inner wall of acasing; tips of rotor blades are compositely electroplated with a Ni / c-BN coating; and the abradable sealing coating and the Ni / c-BN coating are used as a pair of abradable sealing friction pair, thereby forming a novel gas circuit sealing coating structure. In the operation process of an engine, the tips of the rotor blades can cut into the abradable sealing coating on the inner wall of the casing, thus grooves capable of improving the sealing effect are reserved, ideal radial airflow gaps are formed, and the maximum pressure difference is obtained, so that the power of the engine is remarkably improved, the consumption of aviation kerosene is reduced, and the one-time test run percent of pass of the whole engine is improved.

Description

technical field [0001] The invention belongs to the gas path sealing technology of an aero-engine compressor, in particular to a method for controlling blade tip clearance of a titanium alloy compressor. Background technique [0002] Aeroengine compressor tip clearance refers to the radial clearance between the rotor blade tip of an axial flow engine and the casing. Under the action of the pressure difference between the pressure surface and the suction surface of the blade, the high-pressure gas will leak through the radial gap, thereby reducing the working efficiency and stability of the engine, and increasing the fuel consumption rate and exhaust temperature. In addition, the running clearance of the compressor is too large, its aerodynamic characteristics may be damaged when the engine accelerates, and cause surge. These surges mostly occur during takeoff and climb, especially within 40 to 60 seconds after reaching the takeoff thrust, which affects the stability and rel...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D11/12
CPCF01D11/122
Inventor 艾鹏刘礼祥李晓罡苏宝情潘帅
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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