CN-121993298-A - Method and system for correcting over-temperature protection control parameters of turboshaft engine starting

CN121993298ACN 121993298 ACN121993298 ACN 121993298ACN-121993298-A

Abstract

The invention belongs to the technical field of aero-engines, and discloses a method and a system for correcting a turboshaft engine starting overtemperature protection control parameter, wherein the method comprises the steps of determining a first correction coefficient according to a residual temperature value of a gas turbine outlet before the turboshaft engine is started thermally; the method comprises the steps of carrying out first correction on the lead coefficient and the lag coefficient of the gas turbine outlet temperature signal according to the first correction coefficient, determining a second correction coefficient according to the atmospheric pressure value before the turboshaft engine is started, and carrying out second correction on the lead coefficient and the lag coefficient of the gas turbine outlet temperature signal after the first correction according to the second correction coefficient. According to the invention, the lead and lag coefficients of the gas turbine outlet temperature signal are corrected by the atmospheric pressure value before the turboshaft engine is started and the residual temperature value at the gas turbine outlet, so that the overtemperature protection precision of the turboshaft engine for starting the gas turbine outlet temperature under extreme conditions such as plateau and restarting of the heat engine can be greatly improved, and the damage problem of the turboshaft engine caused by the overtravel of the starting temperature can be avoided.

Inventors

YI SHENG
XIAO XIN
TANG XIAOTIAN
HUANG KAIMING
XUAN JING
CHEN HAOYANG
YANG FANG
DUAN HUI
CHEN SHI
YE PEIXIANG

Assignees

中国航发湖南动力机械研究所

Dates

Publication Date: 20260508
Application Date: 20241101

Claims (11)

1. The method for correcting the over-temperature protection control parameters of the turboshaft engine is characterized by comprising the following steps of: determining a first correction coefficient according to a residual temperature value of an outlet of the gas turbine before the hot start of the turboshaft engine; performing first correction on the lead coefficient and the lag coefficient of the gas turbine outlet temperature signal according to the first correction coefficient; determining a second correction coefficient according to the atmospheric pressure value before the turboshaft engine is started; And carrying out second correction on the lead coefficient and the lag coefficient of the gas turbine outlet temperature signal after the first correction according to the second correction coefficient.
2. The turboshaft engine start overtemperature protection control parameter correction method of claim 1, wherein determining the first correction factor based on the gas turbine outlet residual temperature value prior to the turboshaft engine hot start comprises the steps of: when the outlet surplus Wen Zhixiao of the gas turbine is at a set temperature value before the hot start of the turboshaft engine, determining that the first correction coefficient is 1; when the residual temperature value of the outlet of the gas turbine before the hot start of the turboshaft engine is larger than or equal to a set temperature value, a first correction coefficient is determined according to the residual temperature value of the outlet of the gas turbine before the hot start of the turboshaft engine and an empirical value related to the characteristics of the turboshaft engine.
3. The method for correcting a turboshaft engine start overtemperature protection control parameter of claim 2, wherein the first correction factor is determined based on a gas turbine outlet residual temperature value before the turboshaft engine is hot started, specifically as follows: Where k1 represents a first correction coefficient, tt4.5' represents a residual temperature value at the outlet of the gas turbine before the hot start of the turboshaft engine, f1 represents an empirical value related to the characteristics of the turboshaft engine, and a is a set temperature value.
4. The turboshaft engine start overtemperature protection control parameter correction method of claim 1, wherein the first correction of the gas turbine outlet temperature signal lead coefficient is performed according to a first correction coefficient, comprising the steps of: And multiplying the first correction coefficient by the gas turbine outlet temperature signal lead coefficient to obtain the gas turbine outlet temperature signal lead coefficient after the first correction.
5. The turboshaft engine start overtemperature protection control parameter correction method of claim 1, wherein the first correction of the gas turbine outlet temperature signal lag coefficient is performed according to a first correction coefficient, comprising the steps of: Multiplying the first correction coefficient by the gas turbine outlet temperature signal hysteresis coefficient to obtain the gas turbine outlet temperature signal hysteresis coefficient after the first correction.
6. The method for correcting the over-temperature protection control parameter for the startup of the turboshaft engine according to any one of claims 1 to 5, wherein the second correction coefficient is determined based on the atmospheric pressure value before the startup of the turboshaft engine, specifically comprising: Where k2 represents a second correction coefficient, P 0 represents an atmospheric pressure value before the turboshaft engine is started, f2 represents an empirical value related to the characteristics of the turboshaft engine, and B represents a set pressure value.
7. The turboshaft engine start overtemperature protection control parameter correction method of claim 1, wherein the second correction of the first corrected gas turbine outlet temperature signal lead coefficient is performed according to a second correction coefficient, comprising the steps of: and multiplying the second correction coefficient by the lead coefficient of the gas turbine outlet temperature signal after the first correction to obtain the lead coefficient of the gas turbine outlet temperature signal after the second correction.
8. The turboshaft engine start overtemperature protection control parameter correction method of claim 1, wherein the second correction of the first corrected gas turbine outlet temperature signal lag coefficient is performed according to a second correction coefficient, comprising the steps of: And multiplying the second correction coefficient by the gas turbine outlet temperature signal hysteresis coefficient after the first correction to obtain the gas turbine outlet temperature signal hysteresis coefficient after the second correction.
9. A turboshaft engine start overtemperature protection control parameter correction system, comprising: the first calculation module is used for determining a first correction coefficient according to the residual temperature value of the outlet of the gas turbine before the hot start of the turboshaft engine; a first control module for first correcting the lead coefficient and the lag coefficient of the gas turbine outlet temperature signal according to a first correction coefficient; The second calculation module is used for determining a second correction coefficient according to the atmospheric pressure value before the turboshaft engine is started; And the second control module is used for carrying out second correction on the lead coefficient and the lag coefficient of the gas turbine outlet temperature signal after the first correction according to the second correction coefficient.
10. The turboshaft engine start overtemperature protection control parameter correction system of claim 9, wherein the first control module is specifically configured to: Multiplying the first correction coefficient by the gas turbine outlet temperature signal lead coefficient to obtain a gas turbine outlet temperature signal lead coefficient after the first correction; Multiplying the first correction coefficient by the gas turbine outlet temperature signal hysteresis coefficient to obtain the gas turbine outlet temperature signal hysteresis coefficient after the first correction.
11. The turboshaft engine start overtemperature protection control parameter correction system of claim 9, wherein the second control module is specifically configured to: multiplying the second correction coefficient by the lead coefficient of the gas turbine outlet temperature signal after the first correction to obtain the lead coefficient of the gas turbine outlet temperature signal after the second correction; And multiplying the second correction coefficient by the gas turbine outlet temperature signal hysteresis coefficient after the first correction to obtain the gas turbine outlet temperature signal hysteresis coefficient after the second correction.

Description

Method and system for correcting over-temperature protection control parameters of turboshaft engine starting Technical Field The invention belongs to the technical field of aeroengines, and particularly relates to a method and a system for correcting a turboshaft engine starting overtemperature protection control parameter. Background At present, the turboshaft engine has an over-temperature starting automatic protection function, and the over-temperature starting protection function is a protection method that when the aeroengine is started, the fuel gas temperature exceeds the maximum allowable temperature under abnormal conditions, and in order to prevent the engine from being damaged, the engine control system automatically cuts off the fuel supply according to isothermal signals such as the gas turbine outlet temperature Tt 4.5. The existing starting overtemperature automatic protection function generally takes the outlet temperature Tt4.5 of the gas turbine as a starting overtemperature protection control signal, and when the Tt4.5 temperature reaches the maximum allowable temperature of the engine, the control system can automatically cut off oil supply in order to prevent the damage of the turboshaft engine. In order to solve the problem of delay in the rising or falling process of the real signal Tt4.5, the existing control system adopts a lead-lag algorithm to correct the signal Tt4.5 to obtain a correction value Tt4.5cor. When the correction value Tt4.5cor reaches the set temperature protection value, the control system cuts off oil supply in advance, so that the real temperature of Tt4.5 is prevented from exceeding the temperature protection limit value of the turboshaft engine due to response lag of the thermocouple. At present, as shown in fig. 1, the conventional tt4.5 signal lead-lag correction schematic block diagram is obtained by interpolating the lead coefficient tt4.5lead and the lag coefficient tt4.5lag according to the converted rotation speed Ngc of the gas turbine. The existing turboshaft engine starting overtemperature automatic protection function has the following problems: 1. At present, when the lead coefficient and the lag coefficient are designed for the Tt4.5 signal, the influence of the atmospheric pressure P 0 and the thermal starting residual temperature on the temperature change characteristic of the Tt4.5 at the starting time is not considered, and in special cases, the problem of overlarge deviation of the starting overtemperature protection value may exist. 2. The hot start effect of the turboshaft engine is that the turboshaft engine needs to have an emergency restart function, the temperature of a hot end part is high during engine restart, the flow passage area of parts such as turbine blades, a casing and the like is reduced under the characteristic of thermal expansion and contraction, meanwhile, cold air sucked by the engine during start can be heated and expanded, so that the air inflow rate is smaller during engine hot start, the temperature rise rate of Tt4.5 during hot start is obviously higher than that during cold start, and the temperature rise rate of Tt4.5 during restarting is faster when the residual temperature of the engine is higher before start. The existing lead coefficient and lag coefficient cannot ensure that the Tt4.5 overtemperature protection limiting precision under different residual temperature conditions meets the requirement, and the risk of damaging the engine exists. 3. The influence of the atmospheric pressure P 0 is that the air in the plateau is relatively thin, the turboshaft engine has small air when starting in the plateau, and the temperature rising rate of Tt4.5 is obviously higher than that in the plain region. The existing lead coefficient and lag coefficient cannot ensure that the Tt4.5 starting overtemperature protection limiting precision under different altitudes meets the requirement, and the risk of damaging the turboshaft engine exists. In summary, when the existing automatic overtemperature protection function for the turboshaft engine is started under special environmental conditions such as plateau, high temperature, intake distortion and the like, the problems that the accuracy of the overtemperature protection value for starting is not satisfied, surge overtemperature and the like are easy to occur, and the turboshaft engine is damaged are caused. Disclosure of Invention Aiming at the problems, the invention provides a method and a system for correcting the over-temperature protection control parameters of the starting of a turboshaft engine, which adopts the following technical scheme: A method for correcting the over-temperature protection control parameters of the start of a turboshaft engine comprises the following steps: determining a first correction coefficient according to a residual temperature value of an outlet of the gas turbine before the hot start of the turboshaft engine; performing first correcti