Aviation gas turbine transition state performance similarity method and device

Abstract

The invention provides an aviation gas turbine transition state performance similarity method and device. The method comprises the steps of obtaining a high-temperature working condition characteristic curve of a gas turbine, taking any moment in the high-temperature working condition characteristic curve as a high-temperature working condition datum point, and determining high-temperature working condition parameters of the high-temperature working condition datum point; determining a target moment corresponding to the low-temperature working condition reference point according to the consistency of the high-low temperature working condition dimensionless moments, and determining low-temperature working condition parameters of the low-temperature working condition reference point according to the basic reference quantity corresponding to the actual physical condition; according to the reference temperature of the high-temperature working condition datum point and the reference temperature of the low-temperature working condition datum point, determining the corresponding relation of the high-temperature working condition characteristic curve and the low-temperature working condition characteristic curve on the time scale; on the basis of the corresponding relation and the high-temperature working condition characteristic curve, determining the change rate of the parameters at all moments along with time under the low-temperature working condition; and generating the working condition parameters of the low-temperature working condition at each moment according to the low-temperature working condition parameters and the change rate of the low-temperature working condition datum point.

Description

technical field [0001] The present application relates to the field of research and testing of turbine transition state performance, in particular to a method and device for similar transition state performance of aviation gas turbines. Background technique [0002] Turbines are widely used in aerospace, vehicle and ship power, power stations and other fields, and their aerodynamic performance is a key factor affecting the working state of the engine and energy conversion efficiency. Usually, the analysis and design system of turbine aerodynamic performance is established based on steady-state conditions, and the related research on the transient characteristics of turbines in the transition state process is still in its infancy, and it is urgent to carry out relevant experiments on the typical transition state process of turbines. To fully and comprehensively grasp the turbine performance in the transition state process. [0003] In related fields, Imperial College of Tech...

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Problems solved by technology

However, the common transition state process of aircraft turbines usually does not have a clear periodicity, and this similar method based on the St number is not applicable

[0004] At present, the research on transition state similarity worldwide is still in its infancy, and it is difficult to find theories and results that can be referred to. This is precisely the pain point of the turbine transition state test, and it is urgent to refine the transition state similarity applicable to engineering. method

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