A method and device for determining a sustained test run intake air warming temperature

Abstract

The application belongs to the technical field of engine test, and particularly relates to a method and device for determining the temperature of intake air in a long-duration test run. The method comprises the following steps: S1, determining a first engine inlet temperature for simulating an aircraft at a specified altitude and Mach number; S2, determining a second engine inlet temperature at a corresponding hot day 1% risk extreme value atmospheric temperature at the specified altitude and Mach number; S3, forming a plurality of discrete temperature points between the first engine inlet temperature and the second engine inlet temperature; S4, for each discrete temperature point, determining compressor outlet cross-section parameters and turbine inlet cross-section parameters according to an engine speed and exhaust temperature control plan; S5, determining a turbine base temperature; and S6, taking the discrete temperature point corresponding to the highest turbine base temperature value as the required inlet temperature during the engine long-duration test run. The application can ensure that the hot end components are properly tested, and effectively supports the flight use of the engine in the field.

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