A method for assessing power decay for a turboshaft engine

Abstract

The application discloses a kind of turbine shaft engine use power attenuation evaluation method, comprising: obtaining data, the turbine shaft engine use data of multiple flights of helicopter flight is input to controller, the controller identifies and extracts the helicopter sustained level flight section data of each flight;Data calculation, the controller calculates the calibration value P sh_cor And the calibration value M _cor Of engine performance parameter of each flight sustained level flight section data of the helicopter; Determine parameter point, the controller determines the parameter point (P sh_cor , M _cor , t) of each flight; Parameter point check, the controller calculates the evaluation parameter point (M sh_ , t) under the reference shaft output power P _ Of multiple flights; Fitting curve, the controller calculates the fitting curve between the engine performance parameter M _ Under the reference shaft output power and the actual running time t of the turbine shaft engine; Performance evaluation, the controller uses the fitting curve to evaluate turbine shaft engine power attenuation condition.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of flight training, in particular to a method for evaluating power attenuation of a turboshaft engine. BACKGROUND

[0002] The existing power attenuation evaluation technology of turboshaft engine is mainly based on bench test data, selecting parameter indexes that can reflect the power attenuation of the engine, analyzing the performance degradation trend of the engine components, and then combining some model algorithms to evaluate the overall power attenuation of the turboshaft engine.

[0003] The inventors found that the existing technology has at least the following problems: bench test can be carried out according to the rated power dimension to study the power attenuation, while after the turboshaft engine is delivered for use, due to the power loss caused by the turboshaft engine after installation, and the influence of different use environments on the power attenuation of the turboshaft engine, etc., there will be a large error between the power attenuation evaluation of the turboshaft engine based on the bench test data and the actual use result. SUMMARY

[0004] In view of this, the present application provides a method for evaluating power attenuation of a turboshaft engine in use.

[0005] Specifically, the technical scheme comprises the following steps:

[0006] A method for evaluating power attenuation of a turboshaft engine in use comprises:

[0007] Obtaining data, inputting the turboshaft engine use data of multiple flights of a helicopter into a controller, and the controller identifying and extracting the sustained level flight segment data of each flight of the helicopter;

[0008] Data calculation, the controller calculating the calibration value P sh_ of the shaft output power of the sustained level flight segment data of each flight of the helicopter according to the sustained level flight segment data of each flight of the helicopter obtained in the obtaining data step _ ;

[0009] Determining parameter points, the controller determining the parameter points (P sh_ , M _ , t) of each flight according to the calibration value P sh_ of the shaft output power and the calibration value M _ of the engine performance parameter of each flight obtained in the data calculation step, and the actual running time t of the turboshaft engine of each flight;

[0010] Parameter point checking, a reference shaft output power P sh_, the controller calculates the calibration value P sh_ of the shaft output power in the parameter point of the multiple flight stages converted into the reference shaft output power P sh_ ; sh_ ; _ ;

[0011] , the controller calculates the evaluation value M sh_ of the engine performance parameter under the reference shaft output power according to the evaluation parameter point (M _ , t) under the reference shaft output power P _ of the multiple flight stages;

[0012] , the controller evaluates the power attenuation of the turbine shaft engine by using the fitting curve.

[0013] Preferably, the data calculating step includes that the controller calculates the average value P sh of the shaft output power of the helicopter sustained level flight data of each flight stage according to the helicopter sustained level flight data of each flight stage obtained in the data obtaining step, and the controller calculates the calibration value P sh of the shaft output power according to the average value P sh_ ;

[0014] The calculation formula of the calibration value P sh_ of the shaft output power is as follows:

[0015]

[0016] In the formula, P0 is the standard atmospheric pressure, P H is the actual atmospheric pressure, T0 is the standard ambient temperature, and T H is the actual atmospheric temperature.

[0017] Preferably, the engine performance parameter includes the gas turbine speed N g ;

[0018] The data calculating step includes that the controller calculates the average value N g′ of the gas turbine speed of the helicopter sustained level flight data of each flight stage according to the helicopter sustained level flight data of each flight stage obtained in the data obtaining step, and the controller calculates the calibration value N g′ of the gas turbine speed according to the average value N g_cor ;

[0019] the calibrated value N of the gas turbine rotating speed g_cor The calculation formula is as follows:

[0020]

[0021] In the formula, T0 is the standard ambient temperature, T H is the actual atmospheric static temperature.

[0022] Preferably, in the parameter point determining step, the controller determines the parameter point (P sh_cor , N g_cor , t) of each flight according to the calibrated value P sh_cor of the shaft output power and the calibrated value N of the gas turbine rotating speed obtained in the data calculating step, and the actual running time t of the turbine shaft engine of each flight. g_cor

[0023] In the parameter point checking step, the controller calculates the evaluation parameter points of multiple flights

[0024] Preferably, the engine performance parameter includes the turbine inter-gas temperature T 45 .

[0025] In the data calculating step, the controller calculates the average value T 45′ of the turbine inter-gas temperature of each flight according to the helicopter sustained level flight data of each flight obtained in the data obtaining step, and calculates the calibrated value T 45′ of the turbine inter-gas temperature according to the average value T 45_cor of the turbine inter-gas temperature.

[0026] The calculation formula of the calibrated value T 45_cor of the turbine inter-gas temperature is as follows:

[0027]

[0028] In the formula, T0 is the standard ambient temperature, T H is the actual atmospheric static temperature.

[0029] Preferably, in the parameter point determining step, the controller determines the parameter point (P sh_cor , T 45_cor , t) of each flight according to the calibrated value P sh_cor of the shaft output power and the calibrated value T 45_cor of the turbine inter-gas temperature obtained in the data calculating step, and the actual running time t of the turbine shaft engine of each flight.​

[0030] In the parameter point verification step, the controller calculates and obtains evaluation parameter points for multiple flights.

[0031] Preferably, in the curve fitting step, the controller outputs power P from the reference axis based on multiple flights. sh_ The evaluation parameter points (M) below _ The evaluation value M of the engine performance parameters under the reference shaft output power is calculated using the linear least squares method. _ The fitting curve between the actual operating time t of the turboshaft engine and the actual operating time t includes:

[0032] The controller is configured with a fitting model of y = a0 + a1x;

[0033] The evaluation parameter point (M) is set in the controller. _ If there are n points (x0, y0), then the controller obtains n points (x1, y1)...(x...t). i y i )…(x n y n ), n≥k;

[0034] The controller calculates the sum of squared deviations:

[0035] The controller takes a partial derivative with respect to the sum of squared deviations, and the sum of squared deviations is minimized when the partial derivative is equal to zero.

[0036] The controller uses stochastic gradient descent or Newton's method to obtain the coefficient matrix [a0, a1] when the sum of squared deviations is minimized. T Then the evaluation value M of the engine performance parameter is obtained. _ The fitted curve between the actual operating time t of the turboshaft engine and the actual operating time t.

[0037] Preferably, in the performance evaluation step, the controller identifies and extracts the engine maturity data for each flight, and the controller uses the fitted curve to evaluate the engine maturity data for each flight to determine whether the power decay of the turbine shaft engine meets the standard.

[0038] Preferably, in the data acquisition step, the controller identifies and extracts multiple segments of the continuous level flight segment data for each helicopter sortie.

[0039] In the data calculation step, the controller calculates the calibration value P of the multiple shaft output power for each flight based on the data from multiple segments of the helicopter's continuous level flight. sh_and calibration values M of a plurality of the engine performance parameters _ ;

[0040] The controller determines a plurality of the parameter points (P sh_ , M _ , t) of each flight according to calibration values P of a plurality of the shaft output powers of each flight sh_ , M _ , t) of each flight

[0041] The controller averages parameters in a plurality of the parameter points (P sh_ , M _ , t) of each flight with the same actual running time t sh_ , M _ , t) of each flight

[0042] The technical solutions provided by the present application have at least the following beneficial effects:

[0043] The present application uses engine use data in various flight training and actual use environment in the method for evaluating power attenuation of turbine shaft engine, thereby reducing the error between the evaluation result and the actual use result. BRIEF DESCRIPTION OF DRAWINGS

[0044] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed in the embodiment description will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative effort on the basis of these drawings.

[0045] Figure 1 The flow chart of the method for evaluating power attenuation of turbine shaft engine according to the present application;

[0046] Figure 2 The schematic diagram of engine power attenuation in comprehensive environment according to an embodiment of the present application;

[0047] Figure 3 The schematic diagram of the influence of high temperature environment on engine power attenuation according to an embodiment of the present application;

[0048] Figure 4 The schematic diagram of the influence of high-cold environment on engine power attenuation according to an embodiment of the present application;

[0049] Figure 5Fig. 1 is a schematic diagram of the influence of highland environment on engine power attenuation in an embodiment of the present application.

[0050] The specific embodiments of the present application have been shown through the above-mentioned drawings, and will be described in more detail hereinafter. These drawings and the written description are not intended to limit the scope of the inventive concept in any way, but to illustrate the inventive concept to those skilled in the art by referring to specific embodiments. DETAILED DESCRIPTION

[0051] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of the present application.

[0052] To make the technical solutions and advantages of the present application clearer, the embodiments of the present application will be described in further detail below with reference to the drawings.

[0053] The present embodiment introduces a power attenuation evaluation method for a turboshaft engine, comprising: obtaining data, inputting the turboshaft engine use data of multiple flights of a helicopter into a controller, and the controller identifies and extracts the sustained level flight segment data of each flight of the helicopter; data calculation, the controller calculates the calibration value P of the shaft output power of the sustained level flight segment data of each flight of the helicopter according to the sustained level flight segment data of each flight of the helicopter obtained in the obtaining data step; determining the calibration value M of the engine performance parameter of each flight of the helicopter according to the calibration value P of the shaft output power of each flight of the helicopter obtained in the data calculation step; determining the actual running time t of the turboshaft engine of each flight of the helicopter; and determining the parameter point (P, M, t) of each flight according to the calibration value P of the shaft output power, the calibration value M of the engine performance parameter, and the actual running time t of the turboshaft engine of each flight. sh_ _ sh_ _ sh_ _ sh_ sh_ sh_ sh_ _ sh_ _ The specific embodiments of the present application have been shown through the above-mentioned drawings, and will be described in more detail hereinafter. These drawings and the written description are not intended to limit the scope of the inventive concept in any way, but to illustrate the inventive concept to those skilled in the art by referring to specific embodiments. DETAILED DESCRIPTION

[0051] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of the present application.

[0052] To make the technical solutions and advantages of the present application clearer, the embodiments of the present application will be described in further detail below with reference to the drawings.

[0053] The present embodiment introduces a power attenuation evaluation method for a turboshaft engine, comprising: obtaining data, inputting the turboshaft engine use data of multiple flights of a helicopter into a controller, and the controller identifies and extracts the sustained level flight segment data of each flight of the helicopter; data calculation, the controller calculates the calibration value P of the shaft output power of the sustained level flight segment data of each flight of the helicopter according to the sustained level flight segment data of each flight of the helicopter obtained in the obtaining data step; determining the calibration value M of the engine performance parameter of each flight of the helicopter according to the calibration value P of the shaft output power of each flight of the helicopter obtained in the data calculation step; determining the actual running time t of the turboshaft engine of each flight of the helicopter; and determining the parameter point (P, M, t) of each flight according to the calibration value P of the shaft output power, the calibration value M of the engine performance parameter, and the actual running time t of the turboshaft engine of each flight.​_ Fitted curve between the actual operating time t of the turboshaft engine and the actual operating time t; performance evaluation, the controller uses the fitted curve to evaluate the power decay of the turboshaft engine.

[0054] Furthermore, during the sustained level flight phase of the helicopter, the output shaft power of the turboshaft engine remains basically stable.

[0055] Furthermore, in this embodiment, the actual operating time t refers to the total flight time of the helicopter from the start of delivery and use to the end of the continuous level flight segment recorded for this flight, in hours.

[0056] Furthermore, the controller is equipped with an identification module and a calculation module. The controller receives usage data of the turboshaft engine under various flight training and real-world operating environments. The identification module identifies and extracts data from the helicopter's continuous level flight phase. The calculation module obtains this data and calculates the calibration value P of the shaft output power for each flight's continuous level flight phase based on this data. sh_ And the calibration value M of engine performance parameters _ .

[0057] Furthermore, in the parameter point verification step, the reference axis output power P set in the controller... sh_ Based on the calibration value P of the output power of multiple axes sh_ The determination principle is to select the calibration value P of the output power of most axes. sh_ The calibration value P of the shaft output power within the concentration range of the numerical value. sh_ The value, and the calibration value P of the shaft output power in the aggregation section. sh_ The average value is calculated and used as the reference axis output power P. sh_ The evaluation value M of the engine performance parameter in the evaluation parameter point. _ The calibration value P for the shaft output power sh_ Converted to reference axis output power P sh_ Calibration value M of engine performance parameters _ The converted value.

[0058] Furthermore, in existing technologies, the data source for evaluating turboshaft engine power attenuation is bench test data. However, bench test data differs significantly from the actual conditions after helicopter delivery. Therefore, evaluating turboshaft engine power attenuation using bench test data typically results in a large discrepancy between the current assessment and the actual power attenuation observed in use. This embodiment utilizes turboshaft engine usage data from various flight training and real-world operating environments in its data acquisition step, thereby reducing the error between the evaluation results and actual usage results.

[0059] Preferably, the data calculation step includes the controller calculating the average shaft output power P of each helicopter's continuous level flight segment based on the data acquired in the data acquisition step. sh The controller is based on the average shaft output power P. sh The calibration value P of the shaft output power is calculated. sh_ ;

[0060] Calibration value P of shaft output power sh_ The calculation formula is as follows:

[0061]

[0062] Where: P0 is the standard ambient atmospheric pressure, P H T represents the actual atmospheric pressure, T0 represents the standard ambient temperature, and T represents the actual atmospheric pressure. H This represents the actual atmospheric static temperature.

[0063] Furthermore, in this embodiment, the average gas turbine speed N g′ The average temperature T of the gas combustion gas between the turbines 45′ The average output power P of the shaft sh All of these can be calculated from the helicopter's continuous level flight data identified and extracted during the data acquisition step. For example, the helicopter's continuous level flight data identified and extracted during the data acquisition step includes multiple turbine speeds N. p and multiple engine torque T or The controller controls the speed N of multiple power turbines. p Measured by indicators such as variance, if the calculation requirements are met, the controller controls the speed N of multiple power turbines. p Find the mean N p′ Understandably, the controller controls the torque T of multiple engines. or Measured by metrics such as variance, if the calculation requirements are met, the controller can handle the torque T of multiple engines. or Find the mean T or′ Then, the controller calculates the average shaft output power P. sh The average output power P of the shaft shThe calculation formula of the calibrated value P of the shaft output power is as follows:

[0064]

[0065] The controller can further calculate the calibrated value P of the shaft output power. sh_ .

[0066] Preferably, the engine performance parameter includes the gas turbine speed N g ; the data calculation step includes that the controller calculates the average value N g′ of the gas turbine speed of each flight of the helicopter sustained flat flight section data according to the data obtained in the data acquisition step, and the controller calculates the calibrated value N g′ of the gas turbine speed according to the average value N g_cor of the gas turbine speed.

[0067] The calculation formula of the calibrated value N g_cor of the gas turbine speed is as follows:

[0068]

[0069] In the formula, T0 is the standard ambient temperature, and T H is the actual atmospheric static temperature.

[0070] Further, in the parameter point determination step, the controller determines the parameter point (P sh_ , N g_cor , t) of each flight according to the calibrated value P sh_ of the shaft output power and the calibrated value N g_cor of the gas turbine speed of each flight calculated in the data calculation step, and the actual running time t of the turbine shaft engine of each flight.

[0071] In the parameter point checking step, the controller calculates the evaluation parameter point

[0072] Preferably, the engine performance parameter includes the turbine inter gas temperature T 45 ; the data calculation step includes that the controller calculates the average value T 45′ of the turbine inter gas temperature of each flight of the helicopter sustained flat flight section data according to the data obtained in the data acquisition step, and the controller calculates the calibrated value T 45′ of the turbine inter gas temperature according to the average value T 45_cor of the turbine inter gas temperature.

[0073] The calculation formula of the calibrated value T 45_cor of the turbine inter gas temperature is as follows:

[0074]

[0075] In the formula: T0 is the standard ambient temperature, T H This represents the actual atmospheric static temperature.

[0076] Furthermore, in the parameter point determination step, the controller calculates the calibration value P of the shaft output power for each flight based on the data calculation step. sh_ The calibration value T of the gas temperature between the turbine and the turbine 45_ And the actual operating time t of the turboshaft engine for each sortie, to determine the parameter point (P) for each sortie. sh_ T 45_ ,t);

[0077] In the parameter point verification step, the controller calculates and obtains evaluation parameter points (P) for multiple flights. sh_ T 45_ ,t).

[0078] Furthermore, it can be understood that, for example, in this embodiment, if the parameter points (P1, T1, t1) for the first sortie, the parameter points (P2, T2, t2) for the second sortie, and the parameter points (P3, T3, t3) for the third sortie are obtained, then the reference axis output power P is determined. sh_ The average of the parameter points from the first and second sorties is selected. The shaft output power calibration value P1 at the first parameter point is converted to the value using an empirical formula. The turbine inter-gas temperature calibration value T1 is simultaneously converted, and the shaft output power calibration value P2 at the second parameter point is converted to the correct value using an empirical formula. The turbine inter-gas temperature calibration value T2 is simultaneously converted, while the actual usage time t at the parameter point remains unchanged. Therefore, the output power P can be obtained with the actual usage time t as the x-axis and the reference axis as the y-axis. sh_ Turbocharger inter-gas temperature assessment value T 45_ Power decay assessment plot for turboshaft engines with the vertical axis as the ordinate (e.g.) Figure 2 (As shown). Based on the converted reference axis output power P sh_ Evaluation parameter points (M) _ ,t) Calculate and obtain the evaluation value M of the engine performance parameters under the reference shaft output power. _ Fitted curve between the actual operating time t of the turboshaft engine and the actual operating time t; performance evaluation, the controller uses the fitted curve to evaluate the power decay of the turboshaft engine.

[0079] Furthermore, in this embodiment, based on the characteristics of turboshaft engines, a key indicator reflecting the performance of turboshaft engines is selected: gas turbine speed N. g and turbine gas temperature T 45, establish a turbo-shaft engine performance comprehensive evaluation index system, create an evaluation method for key indicators to obtain the actual turbo-shaft engine performance comprehensive evaluation results, evaluate its support for flight training and tasks, and the evaluation results have high accuracy.

[0080] Preferably, in the fitting curve step, the controller obtains the evaluation value M sh_ of the engine performance parameter under the reference shaft output power according to the evaluation parameter point (M _ , t) under the condition of the plurality of flight cycles by using a linear least square method. _ The fitting curve between the evaluation value M _ and the actual running time t of the turbo-shaft engine specifically includes the following steps.

[0081] The fitting model is set as y = a0 + a1x in the controller.

[0082] The evaluation parameter point (M i , t) has n, and the controller obtains n points (x0, y0), (x1, y1)…(x i , y n )…(x n , y T ), n ≥ k.

[0083] The controller calculates the sum of squared deviations.

[0084] The controller takes the partial derivative of the sum of squared deviations, and when the partial derivative is equal to zero, the sum of squared deviations is minimum.

[0085] The controller uses a stochastic gradient descent or Newton method to obtain the coefficient matrix [a0, a1] when the sum of squared deviations is minimum. _ Then the fitting curve between the evaluation value M sh_ and the actual running time t of the turbo-shaft engine is obtained.

[0086] Preferably, in the performance evaluation step, the controller identifies and extracts the engine maturation period data of each flight cycle, and the controller evaluates the engine maturation period data of each flight cycle by using the fitting curve to determine whether the turbo-shaft engine power attenuation meets the standard.

[0087] Preferably, in the data acquisition step, the controller identifies and extracts the helicopter sustained level flight segment data of each flight cycle, and the data calculation step includes the following steps. _ In the data calculation step, the controller calculates the calibration value P sh_ of the shaft output power and the calibration value M _ of the engine performance parameter of each flight cycle according to the multi-segment helicopter sustained level flight segment data of each flight cycle. sh_and calibration values M of a plurality of engine performance parameters _ , and the actual running time t of the turbine shaft engine of each flight, a plurality of parameter points (P sh_ , M _ , t) of each flight are determined; the controller averages the parameters in the plurality of parameter points (P sh_ , M _ , t) of each flight with the same actual running time t, and the controller performs parameter point checking on the parameter points (P sh_ , M _ , t) after averaging the parameters.

[0088] Further, it can be understood that the helicopter sustained level flight segment data of each flight in the embodiment includes multiple segments, and the multiple segments of helicopter sustained level flight segment data correspond to obtain a plurality of parameter points (P sh_ , M _ , t). For example, the time of the first level flight segment is t1 hours t 11 minutes to t1 hours t 12 minutes, and the parameter point corresponding to the first level flight segment is (P1, T1, t1); the time of the second level flight segment is t1 hours t 13 minutes to t1 hours t 14 minutes, and the parameter point corresponding to the second level flight segment is (P2, T2, t1), the time in the parameter point corresponding to the first level flight segment is the same as the time in the parameter point corresponding to the second level flight segment, and the parameters in the parameter point corresponding to the first level flight segment and the parameters in the parameter point corresponding to the second level flight segment can be averaged to obtain a parameter point parameter point which enters the subsequent parameter point checking step.

[0089] Further, the turbine shaft engine usage power decay evaluation method in the embodiment can be used to evaluate the turbine shaft engine usage power decay in special environments.

[0090] In the implementation process, it is necessary to evaluate the turbine shaft engine usage power decay in different environments.

[0091] 1) Power decay evaluation in comprehensive environment

[0092] The controller obtains the effective data segment by identifying the helicopter sustained level flight segment from the multi-flight parameter data input into the controller, and obtains the effective parameter point by calculation. The shaft output power calibration value P sh_ is converted to the reference shaft output power P sh_ (the power value is the average of the shaft output power calibration values in the helicopter sustained level flight segment), and the reference shaft output power P sh_The evaluation value M of the engine performance parameter corresponding to the actual working time t _ The evaluation value M of the engine performance parameter corresponding to the actual working time t _ is fitted by using the linear least square method, so as to obtain the evaluation value M of the engine performance parameter corresponding to the actual working time t _ The curve of the evaluation value M of the engine performance parameter corresponding to the actual working time t is shown in FIG. 4. Figure 2

[0093] 2) Power attenuation evaluation in high-temperature environment

[0094] The effective data segments are intercepted from the sustained flight segments of the helicopters by identifying the sustained flight segments of the helicopters from the multi-flight parameter data, the parameter points in the non-special environment and the parameter points in the high-temperature environment are obtained by calculation, and the calibrated value P of the shaft output power in the parameter points is obtained. sh_ The calibrated value P of the shaft output power in the parameter points is converted to the reference shaft output power P sh_ by using the empirical formula (the power value is the average value of the calibrated values of the shaft output power in the sustained flight segments of the helicopters), so as to obtain the reference shaft output power P sh_ The evaluation value M of the engine performance parameter corresponding to the actual working time t _ The evaluation value M of the engine performance parameter corresponding to the actual working time t _ is fitted by using the linear least square method, so as to obtain the evaluation value M of the engine performance parameter corresponding to the actual working time t _ The curve of the evaluation value M of the engine performance parameter corresponding to the actual working time t is shown in FIG. 4. Figure 3

[0095] 3) Power attenuation evaluation in high-cold environment

[0096] The effective data segments are intercepted from the sustained flight segments of the helicopters by identifying the sustained flight segments of the helicopters from the multi-flight parameter data, the parameter points in the non-special environment and the parameter points in the high-cold environment are obtained by calculation, and the calibrated value P of the shaft output power in the parameter points is obtained. sh_ The calibrated value P of the shaft output power in the parameter points is converted to the reference shaft output power P sh_ by using the empirical formula (the power value is the average value of the calibrated values of the shaft output power in the sustained flight segments of the helicopters), so as to obtain the reference shaft output power P sh_ The evaluation value M of the engine performance parameter corresponding to the actual working time t _ The evaluation value M of the engine performance parameter corresponding to the actual working time t _ is fitted by using the linear least square method, so as to obtain the evaluation value M of the engine performance parameter corresponding to the actual working time t _ The curve of the evaluation value M of the engine performance parameter corresponding to the actual working time t is shown in FIG. 4. Figure 4

[0097] 4) Power attenuation evaluation in high-temperature environment

[0098] ​​​The valid data segment is intercepted from multiple flight data by identifying the helicopter sustained flat flying segment, and the parameter point in non-special environment and the parameter point in plateau environment are obtained by calculation, and the shaft output power calibration value P in the parameter point is calibrated sh_ The shaft output power P is converted to the reference shaft output power P by an empirical formula sh_ (the power value is the average value of the shaft output power calibration value in the helicopter sustained flat flying segment), and the reference shaft output power P is obtained sh_ The corresponding engine performance parameter evaluation value M _ The relationship between the engine performance parameter evaluation value M _ and the actual working time t is fitted by using the linear least square method, so that the variation curve of the engine performance parameter evaluation value M _ with the actual working time t is obtained, as shown in Figure 5 .

[0099] The present embodiment also includes comparative analysis of the power attenuation of the turbine shaft engine and the performance attenuation of the bench test engine. Specifically, the attenuation of the corresponding performance parameters is calculated by investigating the engine power and engine performance parameters during the engine bench test when the engine is shipped and during the first overhaul period and returned to the factory. The attenuation of the corresponding performance parameters and the engine power attenuation are compared and analyzed, and it is found through practice that the attenuation trends and attenuation values of the two are basically consistent, and the difference is consistent with the actual situation, such as the engine performance is improved after cleaning during the first overhaul period and bench test, etc.

[0100] In the present application, the terms "first" and "second" are used only for descriptive purposes and should not be construed as indicating or implying relative importance. The term "a plurality of" refers to two or more, unless otherwise explicitly limited.

[0101] Other embodiments of the present application will be apparent to those skilled in the art from consideration of the specification and practice of the application disclosed herein. The present application is intended to cover any variations, uses or adaptive changes of the present application following the general principles of the present application and including known or customary technical methods not disclosed in the present application. The specification and examples are only considered as exemplary.

[0102] The above is only the preferred embodiment of the present application, and is not intended to limit the present application, and any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application should be included in the protection scope of the present application.

Claims

1. A method of assessing power decay for use in a turboshaft engine, characterized by, The method comprises: acquiring data, inputting the turbine engine usage data of multiple flight missions of a helicopter into a controller, the controller identifying and extracting the sustained level flight segment data of each flight mission; data computation, the controller computes a calibration value P of the shaft output power of the helicopter sustained level flight segment data of each mission from the helicopter sustained level flight segment data of each mission acquired in the acquisition data step sh_cor and the calibration value M of the engine performance parameter _cor ; determining a parameter point (P sh_cor , M _cor , t) for each flight, based on the calibration value P sh_cor of the shaft output power of each flight calculated in the data calculation step, the calibration value M _cor of the engine performance parameter, and the actual operating time t of the turbine shaft engine of each flight. Parameter point verification, the controller is provided with a reference shaft output power P sh_ , the controller converts the calibrated value P sh_cor of the shaft output power in the parameter point of the multiple cycles determined in the parameter point determination step to the reference shaft output power P sh_ , and calculates to obtain the evaluation parameter point (M sh_ , t) under the reference shaft output power P _ of multiple cycles. a fitting curve of the evaluation parameter point (M sh_ , t) with respect to the reference axis output power P _ , t) with respect to the reference axis output power P _ and the actual operating time t of the turboshaft engine. performance evaluation, the controller evaluating the turbine shaft engine power decay condition using the fitting curve.

2. The method of claim 1, wherein The data calculating step comprises that the controller calculates the average value P of the shaft output power of the helicopter sustained level flight segment data of each flight according to the helicopter sustained level flight segment data of each flight obtained in the data obtaining step sh The controller calculates the calibration value P of the shaft output power according to the average value P of the shaft output power sh sh_cor ;​ The calibrated value P of the shaft output power sh_cor The calculation formula is as follows: wherein: P0 is standard ambient atmospheric pressure, P H is actual atmospheric pressure, T0 is standard ambient temperature, T H is actual atmospheric temperature.

3. The method of claim 1, wherein The engine performance parameter includes a gas turbine rotation speed N g ; The data calculation step includes the controller calculating the average gas turbine speed N of each helicopter's continuous level flight segment data for each flight based on the data acquisition step. g′ The controller is based on the average speed N of the gas turbine. g′ The calibration value N of the gas turbine speed was calculated. g_cor ; The calibration value N of the gas turbine rotation speed g_cor The calculation formula is as follows: where: T0 is the standard ambient temperature, T H is the actual atmospheric static temperature.

4. The method of claim 3, wherein said controller calculates the calibration value P of the shaft output power of each flight according to the data obtained in the data calculation step sh_cor and the calibration value N of the gas turbine rotation speed g_cor , and the actual operation time t of the turbine shaft engine of each flight, determines the parameter point (P sh_cor , N g_cor , t) of each flight. The controller calculates a plurality of evaluation parameter points of the plurality of times in the parameter point checking step 5. The method of claim 1, wherein The engine performance parameter includes turbine inter-stage gas temperature T 45 ; The data calculating step comprises that the controller calculates the average value T of the turbine inter-stage gas temperature of each flight according to the helicopter sustained straight flight segment data of each flight obtained in the data obtaining step 45′ The controller calculates the calibration value T of the turbine inter-stage gas temperature according to the average value T of the turbine inter-stage gas temperature 45′ 45_cor ;​ The calibrated value T of the turbine intermediate gas temperature 45_cor The calculation formula is as follows: where: T0 is the standard ambient temperature, T H is the actual atmospheric static temperature.

6. The method of claim 5, wherein said controller calculates the calibration value P of the shaft output power of each flight according to the data obtained in said data calculating step sh_cor and the calibration value T of the turbine inter-stage gas temperature 45_cor , and the actual running time t of the turbine shaft engine of each flight, determines the parameter point (P sh_cor , T 45_cor , t) of each flight. The parameter point checking step, wherein the controller calculates and obtains a plurality of evaluation parameter points of the plurality of times 7. The method of claim 1, wherein The controller in the fitting curve step obtains the evaluation value M of the engine performance parameter under the reference axis output power P according to the evaluation parameter point (M, t) under the reference axis output power P of multiple times sh_ The evaluation parameter point (M, t) is calculated by linear least squares method _ The evaluation value M of the engine performance parameter under the reference axis output power P is obtained _ The fitting curve between the actual running time t of the turbine shaft engine, specifically includes: the fitting model in the controller is set as y=a0+a1x; The controller sets the evaluation parameter point (M _ , t) to have n, and the controller obtains n points (x0, y0), (x1, y1)…(x i , y i )…(x n , y n ), n≥k. The controller calculates a sum of squares of deviations: the controller takes the partial derivative of the sum of squared deviations, and when the partial derivative is equal to zero, the sum of squared deviations is minimum; The controller uses a stochastic gradient descent or Newton method to find the coefficient matrix [a0, a1] that minimizes the sum of the squared deviations T The evaluation parameter point (M _ , t) is obtained from the evaluation value M _ of the engine performance parameter in the evaluation parameter point (M _ , t) and the actual operating time t of the turboshaft engine.

8. The method of claim 1, wherein in the performance evaluation step, the controller identifies and extracts the engine maturation period data of each flight mission, and the controller evaluates the engine maturation period data of each flight mission using the fitting curve to determine whether the turbine shaft engine power decay condition meets the standard.

9. The method of claim 1, wherein in the data acquisition step, the controller identifies and extracts the sustained level flight segment data of each flight mission, which includes multiple segments. The controller calculates the calibration value P of the multiple shaft output powers of each flight according to the helicopter sustained straight flight segment data of multiple segments of each flight in the data calculation step sh_cor and the calibration value M of the multiple engine performance parameters _cor ; The controller determines the parameter point of each flight according to the calibration value P of the output power of each shaft of the engine sh_cor and the calibration value M of the engine performance parameter _cor , and the actual running time t of the turbine shaft engine of each flight, determines the parameter point (P sh_cor , M _cor , t) of each flight. The controller averages the parameters in the parameter points (P sh_cor , M _cor , t) for which the actual run times t in each flight are the same, and the controller performs the parameter point check on the parameter points (P sh_cor , M _cor , t) after averaging the parameters.

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