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Aero-engine fan rotor blade bird strike test parameter determination method

A technology for aero-engine and fan rotors, which is used in aircraft component testing, electrical digital data processing, special data processing applications, etc. Validate the state, the parameter range is comprehensive and reasonable, the effect of saving cycle cost and economic cost

Active Publication Date: 2019-10-22
AECC SHENYANG ENGINE RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The airworthiness requirements stipulate 4 evaluation states, and there are many evaluation states, and the evaluation and verification cycle and economic cost are relatively large

Method used

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  • Aero-engine fan rotor blade bird strike test parameter determination method
  • Aero-engine fan rotor blade bird strike test parameter determination method
  • Aero-engine fan rotor blade bird strike test parameter determination method

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Embodiment Construction

[0030] In order to make the objectives, technical solutions and advantages of the implementation of the application clearer, the technical solutions in the implementation modes of the application will be described in more detail below with reference to the drawings in the implementation modes of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the present application. The embodiments described below by referring to the figures are exemplary and are intended to explain the present application, and should not be construed as limiting the present application. Based on the implementation manners in this application, all other implementation manners obtained by persons of ordinary skill in the art without creative efforts fall within the scope of protection of this application. Embodiments of the pr...

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Abstract

The invention belongs to the technical field of aero-engine bird strike tests, and particularly relates to an aero-engine fan rotor blade bird strike test parameter determination method. The method comprises the following steps: firstly, establishing a blade grid cutting model of a fan rotor blade bird strike test; determining a damage pattern of a blade, determining a velocity component VC perpendicular to the tangential direction of the leading edge blade profile; and finally, determining the maximum value of the velocity component VC in different damage modes in each flight stage and corresponding fan rotor blade bird strike test parameters under the maximum value. According to the method, the test process is simplified according to the damage mode of the blade and the maximum value ofthe velocity component VC, and the influence rule curve of the bird strike parameters can be obtained by adopting the method. Therefore, the specific parameters corresponding to each evaluation stateare determined, and the considered parameter range is more comprehensive and reasonable.

Description

technical field [0001] The application belongs to the technical field of aero-engine bird impact tests, and in particular relates to a method for determining parameters of an aero-engine fan rotor blade bird impact test. Background technique [0002] Aviation engine bird strike has always been a major accident that seriously endangers the flight safety of aircraft. After an aeroengine bird strike, the flying bird will first hit the fan rotor blade at the engine inlet, causing the blade to dent, deform, tear, crack, fall off or even break. A series of secondary damages are caused, causing the aerodynamic performance of the blade to decrease, the thrust of the engine to decrease, the engine to be damaged, the engine to stall, the blade to break and even break through the casing to fly out, directly endangering the safety of passengers, causing aircraft crashes and fatalities, and causing huge economic losses . With the improvement of engine development technology, advanced en...

Claims

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Application Information

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IPC IPC(8): G06F17/50B64F5/60
CPCB64F5/60G06F30/15G06F30/20Y02T90/00
Inventor 张海洋王相平杜少辉曹航陈育志
Owner AECC SHENYANG ENGINE RES INST
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