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Open type turbine blade test equipment

A technology for turbine blades and test equipment, applied in the field of aero-engines, can solve problems such as temperature field, thermal deformation, load loading, etc., to avoid excessive rotation speed, ensure work efficiency, and save test costs.

Inactive Publication Date: 2021-06-04
SHENYANG AEROSPACE UNIVERSITY
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0007] The invention provides an open type turbine blade test equipment, and an open improvement scheme is proposed on the basis of a gas heating device to solve the test problems of mechanical load loading, temperature field and thermal deformation of turbine blades

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Embodiment Construction

[0041] The technical solution of the present invention will be further described in detail below in conjunction with the accompanying drawings, but the protection scope of the present invention is not limited to the following description.

[0042] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments It is some embodiments of the present invention, but not all of them. Accordingly, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely represents selected embodiments of the invention.

[0043] The present invention will be further described below in conj...

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Abstract

The invention provides open type turbine blade test equipment. The open type turbine blade test equipment comprises a Laval nozzle, a fuel gas ejector and a workbench, the front end of the Laval nozzle is used for being connected with a gas outlet of a combustion chamber, and the rear end of the Laval nozzle is used for providing a gas testing environment for turbine blades to be tested right behind the Laval nozzle; the fuel gas ejector is used for being installed right behind the Laval nozzle, a turbine blade to be tested is arranged between the fuel gas ejector and the Laval nozzle, and fuel gas ejected by the Laval nozzle passes through the turbine blade to be tested and then enters the fuel gas ejector; a water cooling structure is arranged on the outer wall and / or in the wall of the fuel gas ejector, and a spraying device and an ejection fan are sequentially arranged in the fuel gas ejector from front to back in the fuel gas flowing direction; and a workbench is arranged below the turbine blade to be tested. On the basis of a gas heating device, an open type improvement scheme is provided, the real working environment of the turbine blade is simulated, and the problems of mechanical load loading, temperature field and thermal deformation testing of the turbine blade are solved.

Description

technical field [0001] The invention relates to the field of aero-engines, in particular to an open turbine blade test equipment. An open turbine blade test device. Background technique [0002] The thermomechanical fatigue (TMF) failure of the turbine blades of aero-engines is the most important failure type during the service of aero-engines, which seriously affects the reliability of aero-engines. Turbine blade thermal-mechanical coupling fatigue test is an important demonstration test in engine design and development, and the test results are an important basis for the finalization of turbine blade structure. To test the reliability of turbine blades under heat-mechanical coupling conditions, the test environment of turbine blades needs to be highly similar to the working environment of real engines. [0003] At present, most of the thermal fatigue tests of gas turbine blades use gas heating, the heating device adopts a closed structure, and the shell of the test secti...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M13/00
CPCG01M13/00
Inventor 关鹏艾延廷陈英涛田晶刘玉姚玉东
Owner SHENYANG AEROSPACE UNIVERSITY
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