Gas turbine inlet guide vane design method, gas turbine and aeroengine

A technology of imported guide vanes and gas turbines, which is applied in the field of aero-engines, can solve the problems of reducing the available gas volume for cooling and mixing in the combustion chamber, increasing the aerodynamic loss of the inlet guide vanes, and reducing the transmission efficiency of the turbine, so as to achieve reasonable distribution of aerodynamic parameters and aerodynamic The effect of less loss and reducing the amount of air-conditioning
CN113836633BActive Publication Date: 2022-12-02AECC HUNAN AVIATION POWERPLANT RES INST
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
AECC HUNAN AVIATION POWERPLANT RES INST
Publication Date
2022-12-02

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Abstract

The invention discloses a method for designing the inlet guide vane profile of a gas turbine. The isentropic Mach number distribution and characteristic parameters of the inlet guide vane profile surface are acquired through simulation, and the low-load area and inlet attack of the inlet guide vane profile surface are obtained. Angle; cut off the low load area of ​​the leading edge of the inlet guide vane by cutting off the front edge to build a high load inlet guide vane, and increase the inlet angle of attack of the inlet guide vane to increase the inlet guide vane In order to keep the axial installation space of the blade in the aero-engine unchanged, the inlet guide vane profile is enlarged and the parameters are reconstructed, so that the distribution of aerodynamic parameters on the surface of the inlet guide vane is reasonable, the aerodynamic loss is small, and the inlet After the guide vane is enlarged, the blade grid pitch of the turbine is enlarged correspondingly, and the number of blades of the turbine is correspondingly reduced in proportion, thereby reducing the amount of cold air used for the inlet guide vane and reducing the manufacturing cost.
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Description

technical field

[0001] The invention relates to the technical field of design and processing of aero-engine parts, in particular to a design method of a gas turbine inlet guide vane profile. In addition, the present invention also relates to a gas turbine designed, processed and manufactured using the above-mentioned gas turbine inlet guide vane profile design method. In addition, the present invention also relates to an aeroengine comprising the above-mentioned gas turbine. Background technique

[0002] In the existing small and medium-sized aviation gas turbine engines, the turbine is one of the core components of the gas turbine engine power plant. It is a turbomachinery that converts the energy of high-temperature and high-pressure gas into kinetic energy and mechanical energy. When the gas flows from the turbine inlet through the guide vane row, it turns and expands, and then converts the gas pressure potential energy into gas kinetic energy, so that the high-speed gas...

Claims

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