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Method for measuring and calculating influence of angle change of variable stator blade of gas compressor on flow

A technology of angle change and air compressor, which is applied to components of pumping devices for elastic fluids, mechanical equipment, non-variable pumps, etc., can solve problems such as high risk, high cost, and limited test data, and achieve optimization Corresponding relationship curve, improving the effect of high cost

Active Publication Date: 2021-01-22
AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD +1
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Problems solved by technology

[0005] The purpose of the present invention is to provide a method for calculating the influence of the change of the adjustable vane angle of the compressor on the flow rate, so as to improve the high cost, long period and risk of testing the flow rate of the compressor under different vane angles through experiments in the related art. Large, limited experimental data problem

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  • Method for measuring and calculating influence of angle change of variable stator blade of gas compressor on flow
  • Method for measuring and calculating influence of angle change of variable stator blade of gas compressor on flow
  • Method for measuring and calculating influence of angle change of variable stator blade of gas compressor on flow

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Embodiment Construction

[0027] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. The following description of at least one exemplary embodiment is merely illustrative in nature and in no way taken as limiting the invention, its application or uses. 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.

[0028] figure 1 A schematic diagram of the local structure of the compressor of the aeroengine of the present embodiment is shown, figure 2 Shows the schematic structural diagram of the adjustable vane of the compressor of this embodiment, combined below figure 1 and figure 2 The parameters desi...

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Abstract

The invention relates to a method for measuring and calculating the influence of angle change of a variable stator blade of a gas compressor on the flow. The method comprises the step A: measuring andcalculating the change of the air flow in the gas compressor according to the change of the projected area on the cross section of the gas compressor before and after the adjustment angle change of asingle-stage variable stator blade. The problems of high cost, long cycle, high risk, and limited test data that exist in the related technology by testing the flow of the gas compressor under different stator vane angles are improved.

Description

technical field [0001] The invention relates to the field of aero-engines, in particular to a method for measuring and calculating the influence of the angle change of the adjustable vane of a compressor on the flow. Background technique [0002] In aero-engines or gas turbines, one or more stages of stator blades in front of the compressor are generally designed to have adjustable installation angles (called VSV adjustable blades) to improve the performance of the compressor at non-design speeds. When the engine speed changes, the VSV blade installation angle (rotating along the blade stacking axis) is adjusted in real time through the VSV actuator to make the aero-engine have optimal performance. Therefore, each stage of VSV has a certain adjustment angle at each speed, thus forming a VSV regulation law at all speeds. [0003] The VSV regulation law is very important to the performance of the engine. Therefore, in the process of designing the aerodynamic performance of th...

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Application Information

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IPC IPC(8): F04D29/56F04D27/00
CPCF04D27/001F04D29/563
Inventor 姜逸轩曹传军尹泽勇李继保翟志龙吴帆李游
Owner AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD
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