CN-122021151-A - Large-state use load analysis method for gas turbine fan engine

CN122021151ACN 122021151 ACN122021151 ACN 122021151ACN-122021151-A

Abstract

The invention relates to the technical field of gas turbine fan engines, in particular to a large-state use load analysis method of a gas turbine fan engine, which obtains large-state use loads with key influences on the service life of key parts of the turbine fan engine, including large-state work time duty ratio, stress working load, other loads with the influence on the service life of the large-state and a large-state use load creep damage equivalent conversion method through deep analysis and research on actual use data of a gas turbine fan engine and the performance and reliability of the engine. The invention provides key technical guidance for the large-state service life determination/extension, test assessment and maintenance support decision of the turbofan engine.

Inventors

FU ZHIZHONG
SUN YANTAO
FAN TIANYU
ZHOU HONGBIN
JI PENGFEI
DONG LIWEI
ZHENG XIAOMEI

Assignees

中国人民解放军93208部队

Dates

Publication Date: 20260512
Application Date: 20260126

Claims (10)

1. A method of analyzing a large-state service load of a gas turbine fan engine, comprising: collecting external field actual use data of a plurality of target engines, wherein the external field actual use data comprises flight parameter data and historical book data; Carrying out statistical analysis based on the actual use data of the external field to determine an average load spectrum for the large state of the engine and a single load value for the large state of the engine; Analyzing the dispersion characteristics of single-machine load by using a probability statistical model based on the engine large-state use load average spectrum and the engine large-state use load single-machine value so as to determine an engine large-state use load high-reliability value; Working parameters of the turbine rotor blade of the engine in a large combat state and a large training state are obtained to calculate creep damage conversion coefficients of different states; Determining an engine large state usage load spectrum based on the engine large state usage load average spectrum, the engine large state usage load single machine value, and the engine large state usage load high reliability value; and forming an engine complete machine test run load spectrum according to the creep damage conversion coefficient so as to provide load input for the engine complete machine test run.
2. The method for analyzing a large-state usage load of a gas turbine fan engine according to claim 1, wherein the flight parameter data includes a high-pressure rotor physical rotational speed, a turbine post-exhaust temperature, an engine throttle lever angle, a combat and training state switching value, and a boost on switching value; The history data comprise total working time, big state working time, boosting working time and boosting switching-on times of an engine; the collected outfield actual usage data covers different latitude areas, different geographical environments and different seasons, and the time range of the data at least comprises a complete natural year.
3. The gas turbine fan engine large state usage load analysis method of claim 2, wherein determining an engine large state usage load average spectrum based on statistical analysis of the flight parameter data comprises: Performing data cleaning on the flight parameter data to remove abnormal data; constructing a flying parameter data analysis model, wherein an engine working state judgment rule defined based on an engine technical specification is preset in the flying parameter data analysis model; And processing the cleaned flying parameter data by using the flying parameter data analysis model, and counting to obtain an engine large-state use load average spectrum, wherein the engine large-state use load average spectrum comprises an engine total working time average value, a combat large-state working time average value, a training large-state working time average value, a stress application turn-on frequency average value and a large-state working time duty ratio average value.
4. The method for analyzing the large-state usage load of the gas turbine fan engine according to claim 2, wherein the history data acquired from the engine is data-selected according to a preset data selection rule on a piece-by-piece basis to perform statistical analysis to determine a single value of the large-state usage load of the engine; the preset data selection rule is to acquire recorded large-state working time corresponding to different time nodes of the engine and total use duration of the engine, and distinguish combat and training states; The engine large-state use load single machine value comprises the total working time of the engine, the working time of the combat large-state, the working time of the training large-state, the stressing working time, the stressing switching-on times and the duty ratio of the large-state working time.
5. The method for analyzing a large-state usage load of a gas turbine fan engine according to claim 4, wherein a three-parameter weibull distribution model is used to analyze the dispersion characteristics of the single load based on the average spectrum of the large-state usage load of the engine and the single-state usage load of the engine, and a characteristic value with reliability greater than a preset reliability threshold is obtained to determine a high-reliability value of the large-state usage load of the engine.
6. The gas turbine fan engine large state usage load analysis method of claim 1, wherein the operating parameters include turbine rotor blade key point temperature and stress; The working parameters are obtained according to the technical specifications of the engine or are obtained through elastoplastic finite element analysis of centrifugal force and temperature load under different states.
7. The gas turbine fan engine large state service load analysis method of claim 6, wherein the temperature and stress based on turbine rotor blade keypoints are calculated using Larson-Miller method to obtain creep life of the keypoints in combat large and training large states.
8. The method for analyzing a large-state load using a gas turbine fan engine according to claim 7, wherein a minimum value among creep life ratios at different key points in a combat large state and a training large state and different flight states is determined as a creep damage conversion coefficient.
9. The method for analyzing engine large state usage load of a gas turbine fan according to claim 8, wherein the data in the engine large state usage load spectrum comprises an engine total operating time, a combat large state operating time, a training large state operating time, a boost on-times, an airport altitude, an engine inlet air temperature, and all load data in the generated engine large state usage load spectrum are scaled to a prescribed length of time.
10. The method for analyzing the load applied to the large state of the gas turbine fan engine according to claim 9, wherein when the residual life of the tested engine is smaller than or equal to the check verification test duration, the durable creep damage conversion coefficient corresponding to the combat and training large state is determined so as to determine the test load spectrum of the whole engine.

Description

Large-state use load analysis method for gas turbine fan engine Technical Field The invention relates to the technical field of gas turbine fan engines, in particular to a large-state use load analysis method of a gas turbine fan engine. Background In the development process of a gas turbine fan engine, the gas turbine fan engine is usually designed in a targeted manner according to required life indexes, wherein the life indexes mainly comprise the total life of the engine, maintenance interval time, total accumulated cycle number (TAC), middle and large-state working time proportion and the like. The big state mainly refers to the middle and above states, including combat and training states. In various life indexes of the engine, the large-state working time duty ratio is very important, and particularly for military fighter engines, the engine is required to work in a large state under various working conditions such as taking off, maneuvering in the air, fighting, escaping and the like of the aircraft so as to provide enough thrust to support the aircraft to complete the task. The length of the large-state working time influences the maintenance interval of the engine to a certain extent, and under certain conditions, the total working time of the engine is still abundant, but the large-state working time is consumed, so that the engine is forced to return to a factory for maintenance in advance, and the use economic benefit of the engine can be greatly reduced. Therefore, the large-state working time duty ratio is reasonably determined according to the large-state load actually used by the engine, and is important to improving the operational efficiency and economic benefit of the engine. Chinese patent publication No. CN119358291a. The invention discloses an analysis method for designing load spectrum compiling reference objects of aero turbine shaft engines, which comprises the steps of counting high-power states of the engines and high-power state using time of the engines corresponding to air typical task sections of various helicopters according to information of each typical task section, calculating the accumulated time proportion of the high-power states of the engines in the typical task sections related to each helicopter, calculating the folded time proportion of the high-power states of the engines in all typical task sections of various helicopters based on the accumulated time proportion of the high-power states of the engines, selecting helicopters serving as the reference objects for compiling load spectrum according to the folded time proportion of the high-power states of the engines, and compiling the load spectrum based on the helicopters. It follows that the prior art has the following problems: The real and changeable external field use data can not be fully acquired and utilized, the problem of carrying out the correlation analysis on the load and the creep damage of the key parts of the engine is avoided, and the problem that the residual life in the engine life extension test is insufficient to complete all the examination is avoided. . Disclosure of Invention Therefore, the invention provides a large-state use load analysis method of a gas turbine fan engine, which is used for solving the problems that the prior art cannot fully acquire and utilize real and changeable external field use data, the load and creep damage of key parts of the engine are not subjected to correlation analysis, and the residual life in an engine life extension test is insufficient to complete all the assessment. In order to achieve the above object, the present invention provides a method for analyzing a large-state usage load of a gas turbine fan engine, comprising: collecting external field actual use data of a plurality of target engines, wherein the external field actual use data comprises flight parameter data and historical book data; Carrying out statistical analysis based on the actual use data of the external field to determine an average load spectrum for the large state of the engine and a single load value for the large state of the engine; Analyzing the dispersion characteristics of single-machine load by using a probability statistical model based on the engine large-state use load average spectrum and the engine large-state use load single-machine value so as to determine an engine large-state use load high-reliability value; Working parameters of the turbine rotor blade of the engine in a large combat state and a large training state are obtained to calculate creep damage conversion coefficients of different states; Determining an engine large state usage load spectrum based on the engine large state usage load average spectrum, the engine large state usage load single machine value, and the engine large state usage load high reliability value; and forming an engine complete machine test run load spectrum according to the creep damage conversion coefficient so as to provide load input