A method for monitoring the power state of a turboshaft engine

Abstract

The invention relates to the field of helicopter engine safety, in particular to a turboshaft engine power state monitoring method. The turboshaft engine power state monitoring method comprises the following steps that 1, all data of parameters including engine torque, power turbine rotation speed, power turbine front temperature, gas compressor rotation speed, atmosphere temperature and pressurealtitude which are within the preset time interval range, and the difference value between the maximum value and the minimum value are measured, and all the data serve as a quasi-steady-state data segment; 2, the quasi-steady-state data segment is subjected to value assessment; 3, the engine power, the power turbine front temperature and the gas compressor rotation speed in the standard state arecalculated; 4, the difference between the actual power and the expected power of an engine in the standard state is obtained through calculation; and 5, when the difference value in the step 4 is smaller than the preset value, and a warning indicating that the power of the engine is abnormal is given. According to the turboshaft engine power state monitoring method, the difference between the actual power and the expected power of the engine is displayed in real time, and if the difference value is smaller than a certain preset value, the warning indicating that the power of the engine is abnormal is given.

Description

technical field [0001] The invention relates to the field of helicopter engine safety, and relates to a method for monitoring the power state of a turboshaft engine. Background technique [0002] The actual output power of the engine is very important to ensure the flight performance of the helicopter. With the accumulation of use time, the actual output power of the engine will be attenuated. At present, in order to monitor the engine power attenuation trend of various models at home and abroad, to ensure the safety of the engine, and to provide a basis for engine maintenance, it is necessary to perform a power guarantee inspection test on the engine every certain flight time. [0003] However, the current engine power guarantee inspection test cannot monitor the decay trend of the engine power at any time. Contents of the invention [0004] The purpose of the present invention is to provide a turboshaft engine power state monitoring method to at least solve the problem ...

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to provide a turboshaft engine power state monitoring method to at least solve the problem that the current engine power guarantee inspection test cannot monitor the decay trend of engine power at any time

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