CN114544177A - Core machine durability test method for typical use state of complete engine - Google Patents
Core machine durability test method for typical use state of complete engine Download PDFInfo
- Publication number
- CN114544177A CN114544177A CN202210178134.7A CN202210178134A CN114544177A CN 114544177 A CN114544177 A CN 114544177A CN 202210178134 A CN202210178134 A CN 202210178134A CN 114544177 A CN114544177 A CN 114544177A
- Authority
- CN
- China
- Prior art keywords
- point
- working
- machine
- core
- points
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Testing Of Engines (AREA)
Abstract
The application relates to the field of durability tests of core machines, in particular to a core machine durability test method for a typical use state of a complete engine, which comprises the steps of selecting a typical state working point corresponding to a core machine and a complete engine, substituting the typical state working point into a complete machine model, finding out all system data of the complete machine, and calculating inlet and outlet parameters and flow parameters of the core machine by using the system data of the complete machine, so as to establish a corresponding relation between the complete machine and the core machine; and then, the calculated data of the core machine are utilized to evaluate the working life of each structural part of the core machine, weak working conditions are found out to establish test items, then the working points are classified, so that the heating and pressurizing test run times are reduced, different test run program types are designed according to the test items to perform test run, and the durability test result of the core machine is obtained, so that the durability test of the core machine is performed under the condition that no flight task section and task mixing information are input, and the test efficiency is high.
Description
Technical Field
The application belongs to the field of durability tests of core machines, and particularly relates to a core machine durability test method for a complete engine in a typical use state.
Background
The aeroengine works under the harsh conditions of high temperature, high pressure and high rotating speed for a long time, and the working state is frequently changed, so that the aeroengine bears larger alternating load and is easy to have complex mode faults such as cracks and fractures, and the durability/durability test is an important test for checking the indexes such as the service life and the reliability of the aeroengine; the core engine is a key part which has the worst working conditions (high temperature, high pressure and high rotating speed) in the aeroengine and has the greatest influence on the whole performance of the engine, the working principle of the core engine is similar to that of a single-shaft turbojet engine, and the core engine is a single-rotor engine consisting of a core component, an air inlet and exhaust device, a starting system, a control system, a lubricating system and the like; the world aviation strong country generally takes a core machine as a basic platform, derives and develops an aero-engine technical route, can effectively shorten the engine development period, and is vital to engine development. The core machine durability/reliability test is also an important assessment test for indexes such as the service life and the reliability of the core machine, and is a unique method for determining the service life of key parts of the core machine and finding weak links of the core machine.
At present, the durability test of the whole core engine and the whole engine mainly comprises the steps of calculating an engine load spectrum by converting a statistical method such as a rain flow method and the like according to a flight task section and task mixing information of an airplane assembled by the core engine and the whole engine, and designing a durability test program of the engine according to important parameters such as strength, fatigue and service life. The development cycle of the engine is higher than that of an airplane, so that no specific installed object exists when the engine is started for research and development, the development of a core engine is the starting stage of the whole engine, the core engine belongs to the scope of pre-research, the flight task section and task mixing information of the airplane are not input when the durability test of the core engine is carried out, the durability test of the core engine can be effectively carried out under the condition that the flight task section and the task mixing information of a top layer engine are not input, and the problems of setting the service life of key parts of the core engine and finding the weak links of the core engine are urgently needed to be solved.
Disclosure of Invention
The application aims to provide a core machine durability test method in a typical use state of a complete engine, so as to solve the problem that in the prior art, a core machine durability test is difficult to effectively carry out under the condition of no flight mission profile of a top layer machine and no mission mixing information input.
The technical scheme of the application is as follows: a core machine durability test method for a complete machine typical use state of an engine comprises the steps of establishing a sample set, selecting a typical state working point of the core machine corresponding to the complete machine engine, and using the typical state working point as an initial input point of a core machine durability test; calculating the inlet and outlet parameters and the flow parameters of the core machine by using the selected working points of the whole machine, and establishing the corresponding relation between the whole machine and the core machine; evaluating the working life of each structural part of the core machine according to the performance calculation result of the core machine; performing full-envelope system analysis on a fuel system, a lubricating oil system and an air system, finding out weak working conditions under all working conditions in the full-envelope range of all systems, establishing a test project, and performing working point check by combining with the working points of a core machine corresponding to the whole machine; the method comprises the steps that a core machine overall performance calculation model is utilized, according to a core machine service life evaluation result, a working point with large temperature, pressure and rotating speed span of a core machine is equivalently converted into another working point along different load lines, the working points are classified, and the similar working points are arranged on the same heating and pressurizing test run; designing the types of test run programs, arranging the number of test runs according to the service life evaluation result, determining the working hours of working points, compiling test execution files and carrying out test runs.
Preferably, the classification method of the working points is to classify the working points with the import and export conditions within a certain threshold range into one class; and for the working points with larger temperature, pressure and rotating speed spans of the core machine in the envelope, converting along a temperature line before the turbine, a physical rotating speed line of the core machine and an outlet total pressure line of the isobaric compressor, and then classifying according to the threshold range of the inlet and outlet conditions.
Preferably, the threshold range for the import-export conditions is ± 10%.
Preferably, the selection method of the typical state working point comprises the steps of classifying typical points, and dividing the typical points into a design point class, a maximum load class, a minimum load class, an envelope boundary point class, a typical performance functional point class, a virtual airplane use point class and a component system extreme working annular point class; selecting typical points according to different selection principles by different point classes.
Preferably, the selection principle of the working points is to select the working points with the use frequency of more than 20% when selecting the working points of the design points; selecting a maximum pneumatic load state point, a maximum temperature load state point and a maximum rotating speed load point when the maximum load type working point is selected; selecting a minimum pneumatic load state point, a minimum temperature load state point and a minimum rotating speed load point when selecting a minimum load working point; when the envelope boundary point type working points are selected, at least one working point is selected at the irregular boundary of the envelope; when the typical performance function point type working points are selected, supersonic speed cruise points, subsonic speed cruise points, ground inspection test run points, infrared stealth typical working conditions and power extraction typical points are selected; selecting a takeoff climbing point, a landing point, a hovering point, a high-altitude cruise point, a hollow cruise point and a low-altitude cruise point when the working points of the use points of the hypothetical aircraft are selected; when the extreme working environment point type working points of the component system are selected, the core engine working points under the extreme working conditions in the fuel system, the lubricating oil system and the air system are selected.
Preferably, the time for keeping the rotor dynamic stress and the resonance rotation speed is kept at 10s or less in the design of the test run program.
The core machine durability test method for the whole engine in the typical use state comprises the steps of selecting typical state working points corresponding to a core machine and a whole engine, substituting the typical state working points into a whole engine model, finding out all system data of the whole engine, and calculating inlet and outlet parameters and flow parameters of the core machine by using the system data of the whole engine, so that the corresponding relation between the whole engine and the core machine is established; the method comprises the steps of calculating the data of the core machine, evaluating the working life of each structural component of the core machine, carrying out full-envelope system analysis on a fuel system, a lubricating oil system and an air system, finding out weak working conditions to establish test items, classifying working points to reduce the times of heating and pressurizing test runs, designing different test run program types according to the test items to carry out test runs to obtain the durability test result of the core machine, carrying out the durability test of the core machine under the condition that no flight task profile and task mixing information are input, effectively reducing the test run time by classifying the working points, and having high test efficiency.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic overall flow diagram of the present application;
FIG. 2 is a schematic view of the core machine test heating and pressurizing process of the present application;
FIG. 3 is a schematic diagram of the core machine envelope area division of the present application;
FIG. 4 is a schematic representation of a pre-turbine temperature load operating point transition of the present application;
FIG. 5 is a schematic diagram of the heating and pressurizing test procedure of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
The durability test of the core machine is a pre-research design, flight task profiles and task mixing information input of a top layer machine are not available, accurate core machine inlet parameters, outlet parameters and flow parameters are difficult to obtain, and based on the problem, the method selects a typical state working point of the whole machine, calculates whole machine data by using the typical state working point, then calculates the inlet parameters, the outlet parameters and the flow parameters of the core machine through the whole machine data, and can perform effective durability test through the corresponding relation between the whole machine and the core machine.
As shown in fig. 1, the method specifically comprises the following steps:
step S100, establishing a sample set, and selecting a typical state working point of a core machine corresponding to a complete machine engine as an initial input point of a core machine durability test;
establishing a sample set S ═ { S1, S2.. sn }, a clustering dimension k for all engine use state points; the usage states are classified into typical usage states and atypical usage states according to usage spectrum and boundary theory (boundary points are typical points).
Typical state points which are commonly used after classification for typical state use points of the whole aircraft corresponding to the envelope range of the whole aircraft comprise typical states such as a design point class, a maximum load point class, a minimum load point class, a typical performance function point class, a virtual aircraft use point class, a point class considering extreme working environment of a component system and the like, wherein the design point, the maximum load point, the minimum load point and the envelope boundary point are load points which need to be set and are important bases for searching the working boundary of the core engine.
The specific selection rules are shown in table 1:
TABLE 1 typical point selection principle for load in whole envelope range
For each obtained typical state working point, the typical working points can be substituted into a corresponding complete machine model, and corresponding data of a fuel system, a lubricating oil system, an air system and other systems in the complete machine of the engine corresponding to the typical working points can be calculated through the complete machine model so as to prepare for the next use.
S200, calculating corresponding inlet and outlet parameters and flow parameters of a core machine by using the related data of a fuel system, a lubricating oil system, an air system and the like of the whole machine calculated by the selected working point of the whole machine, wherein the flow parameters comprise temperature, pressure, flow data and the like in the core machine, and the inlet and outlet parameters and the flow parameters are obtained by calculating each system of the whole machine, so that the corresponding relation between the whole machine and the core machine is established; and calculating the inlet and outlet parameters and the process parameters of the core machine by using overall performance calculation software according to the operating point of the complete machine state of the aircraft engine selected in the step S100, thereby determining the simulation condition of the durability test of the core machine and determining the durability operating state.
Step S300, evaluating the service life of each structural part of the core machine by utilizing the structural strength professional theory to calculate and analyze according to the performance calculation result of the core machine, and providing an initial basis of durability test time for each system evaluation of the core machine; such as 432 hours from the calculated evaluation, the core machine may be scheduled for 300 hours or 400 hours durability tests, taking into account a certain safety factor.
S400, performing full-envelope system analysis on a fuel system, a lubricating oil system and an air system, finding out weak working conditions under all working conditions in the full-envelope range of each system, establishing a test project, and performing working point assessment by combining with the working points of a core machine corresponding to the whole machine; if the air system works badly under the low working condition of the core machine, the temperature of the lubricating oil system is higher in the throttling state of the core machine in the high-altitude range and the like, the core machine is combined with the working points of the core machine corresponding to the whole machine to be checked together or specially arranged for checking.
As shown in fig. 2-4, in step S500, according to the core engine service life evaluation result, the core engine with large temperature, pressure and speed spans is equivalently converted into another operating point along different load lines by using the core engine overall performance calculation model, the operating points are classified, and the similar operating points are arranged in the same heating and pressurizing test run;
considering the difference between the core machine test and the whole machine test, the core machine test needs to arrange a heating, pressurizing, cooling and depressurizing process, and the heating, pressurizing, cooling and depressurizing process does not belong to the effective load check of the durability test, so the heating, pressurizing, cooling and depressurizing time is compressed as much as possible. As shown by the area divided by the combination of the black dashed line and the solid line in fig. 3, the operating point in the core machine is divided into A, B, C, D, E, F six areas according to the inlet and outlet simulation conditions, and the operating point in each area is arranged in the same heating and pressurizing test run, so that the examination of all the operating points can be completed only by six test runs, and the efficiency is high.
For example, in a core machine high-altitude test project, working points with different Mach numbers can be placed in the same heating and pressurizing test car for examination.
The method can be used for checking the working points which are relatively close to each other among the working points, and the working points with large temperature, pressure and rotating speed span of the core machine in the envelope can be converted along the equal turbine front temperature line, the equal core machine physical rotating speed line and the equal compressor outlet total pressure line, so that the checking can be intensively arranged in different regions after the originally dispersed working points are converted, the core machine heating and pressurizing test run efficiency is greatly improved, and the core machine can be verified under the same load condition. For example, in an overhead test project and a low-altitude test project of the core machine, working points under two different projects under the total pressure of the same compressor outlet can be put into the same test car for testing.
As shown in fig. 4, the specific method of the equivalent conversion of the working point is as follows: by utilizing a core machine overall performance calculation model, an equal turbine front temperature line, an equal inlet pressure line, an equal inlet temperature line and the like are calculated in a flight envelope, a working point 1 with one high Mach number can be converted to a working point 2 with the other high Mach number on the equal temperature line for examination, a working point can be converted to the other working point on the equal inlet pressure line for examination, and by analogy, the comprehensive load working point is set through conversion along different load lines, and the alternating load simulation of the core machine durability test is completed.
In the same test run, it is required to ensure that the test life of each structural component in the test is within the range of the initial life evaluation in step S300, and the minimum life of each structural component is taken as the test time of the same test run.
As shown in fig. 5, in step S600, the type of the test run program is designed, the number of test runs is arranged according to the life evaluation result, the working hours of the working point is determined, and the test execution file is written for test runs.
Finally determining the durability test working point of the core machine according to the steps, designing a specific test run program, generally dividing the type of the test run program designed by a user according to an envelope, and then finishing compiling test execution files such as test run technical requirements, measurement requirements and the like according to the type of the test run program, the number of test runs and the working hours. Because the core machine is generally in a pre-research stage, the part tests of the core machine are not sufficiently developed in the pre-research stage, when a durability test program of the core machine is compiled, the core machine rotating speed stopping step is comprehensively designed by mainly considering the factors of the dynamic stress, resonance and the like of the rotor and the stator of the core machine, the situation that the test cannot be developed due to the damage of the hardware of the core machine is avoided, the core machine is strictly forbidden to stop for more than 10s at the dynamic stress and the resonance rotating speed of the rotor and the stator, and the service life of the hardware can be ensured. As exemplified by the core testing program in table 2.
TABLE 2 example of the programming of the durability test run of a certain core machine
This application has following advantage:
1. the method has small relevance with the top layer machine test, so that the core machine durability test can be carried out under the condition that the flight task profile and the task mixing information input of the top layer machine are not needed;
2. the test run efficiency is high, the invalid time of heating, pressurizing, cooling, depressurizing and the like is greatly shortened, and the test run efficiency of the core engine is greatly improved;
3. the service life of hardware is long, the hardware can work under a proper working condition by avoiding the factors of dynamic stress, resonance and the like of the rotor and the stator of the core engine to stay on the step, and the service life of the hardware can be ensured.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. A core machine durability test method for a typical use state of a complete engine is characterized by comprising the following steps: comprises that
Establishing a sample set, selecting a typical state working point of a core machine corresponding to a complete machine engine as an initial input point of a core machine durability test, substituting the typical state working point into a complete machine model, and acquiring data of each system in the complete machine model;
calculating the inlet and outlet parameters and the flow parameters of the core machine by using the selected working points of the whole machine, and establishing the corresponding relation between the whole machine and the core machine;
evaluating the working life of each structural part of the core machine according to the performance calculation result of the core machine;
performing full-envelope system analysis on a fuel system, a lubricating oil system and an air system, finding out weak working conditions under all working conditions in the full-envelope range of all systems, establishing a test project, and performing working point check by combining with the working points of a core machine corresponding to the whole machine;
the method comprises the steps that a core machine overall performance calculation model is utilized, according to a core machine service life evaluation result, a working point with large temperature, pressure and rotating speed span of a core machine is equivalently converted into another working point along different load lines, the working points are classified, and the similar working points are arranged on the same heating and pressurizing test run;
designing different test run program types according to different test projects, arranging the number of test runs according to the service life evaluation result, determining the working hours of working points, compiling a test execution file and carrying out test runs.
2. The method for testing the durability of the core engine in the overall typical use state of the engine as claimed in claim 1, is characterized in that: the classification method of the working points is that,
classifying the working points with the import and export conditions within a certain threshold range into one class;
and for the working points with larger temperature, pressure and rotating speed spans of the core machine in the envelope, converting along a temperature line before the turbine, a physical rotating speed line of the core machine and an outlet total pressure line of the isobaric compressor, and then classifying according to the threshold range of the inlet and outlet conditions.
3. The method for testing the durability of the core engine in the overall typical use state of the engine as claimed in claim 2, is characterized in that: the threshold range of the import-export conditions is ± 10%.
4. The method for testing the durability of the core engine in the overall typical use state of the engine as claimed in claim 1, is characterized in that: the selection method of the typical state working point comprises the following steps
Classifying typical points into a design point class, a maximum load class, a minimum load class, an envelope boundary point class, a typical performance function point class, a virtual airplane use point class and a component system extreme working annular point class;
and selecting typical points according to different selection principles by different point classes.
5. The core machine durability test method for the whole engine typical use state according to claim 4, characterized in that: the selection principle of the working point is
When selecting the working points of the design point class, selecting the working points with the use frequency of more than 20 percent;
selecting a maximum pneumatic load state point, a maximum temperature load state point and a maximum rotating speed load point when the maximum load type working point is selected;
selecting a minimum pneumatic load state point, a minimum temperature load state point and a minimum rotating speed load point when selecting a minimum load working point;
when the envelope boundary point type working points are selected, at least one working point is selected at the irregular boundary of the envelope;
when the typical performance function point type working points are selected, supersonic speed cruise points, subsonic speed cruise points, ground inspection test run points, infrared stealth typical working conditions and power extraction typical points are selected;
selecting a takeoff climbing point, a landing point, a hovering point, a high-altitude cruise point, a hollow cruise point and a low-altitude cruise point when the working points of the use points of the hypothetical aircraft are selected;
when the extreme working environment point type working points of the component system are selected, the core engine working points under the extreme working conditions in the fuel system, the lubricating oil system and the air system are selected.
6. The method for testing the durability of the core engine in the overall typical use state of the engine as claimed in claim 1, is characterized in that: during the design of the test run program, the rotor dynamic stress and the resonance rotation speed are kept for 10s or less.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210178134.7A CN114544177B (en) | 2022-02-25 | 2022-02-25 | Core machine durability test method for typical use state of engine complete machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210178134.7A CN114544177B (en) | 2022-02-25 | 2022-02-25 | Core machine durability test method for typical use state of engine complete machine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114544177A true CN114544177A (en) | 2022-05-27 |
| CN114544177B CN114544177B (en) | 2023-05-05 |
Family
ID=81680336
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210178134.7A Active CN114544177B (en) | 2022-02-25 | 2022-02-25 | Core machine durability test method for typical use state of engine complete machine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114544177B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115168990A (en) * | 2022-06-28 | 2022-10-11 | 中国航发沈阳发动机研究所 | Typical transient history spectrum of aircraft engine and determination method thereof |
| CN115586013A (en) * | 2022-12-09 | 2023-01-10 | 中国航发沈阳发动机研究所 | Durability test system for core machine of aircraft engine |
| CN115586006A (en) * | 2022-12-09 | 2023-01-10 | 中国航发沈阳发动机研究所 | Technical verification method for core engine of aircraft engine |
| CN115597881A (en) * | 2022-12-09 | 2023-01-13 | 中国航发沈阳发动机研究所（Cn） | Method for verifying starting and slow running of core engine of aircraft engine |
| CN115711747A (en) * | 2022-12-09 | 2023-02-24 | 中国航发沈阳发动机研究所 | Aircraft engine core performance calibration verification method |
| CN115753131A (en) * | 2022-12-09 | 2023-03-07 | 中国航发沈阳发动机研究所 | Verification method for high-temperature and high-pressure environment of core engine of aircraft engine |
| CN115753121A (en) * | 2022-12-09 | 2023-03-07 | 中国航发沈阳发动机研究所 | Durability verification method for engine core machine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102749196A (en) * | 2011-10-17 | 2012-10-24 | 成都发动机（集团）有限公司 | Service life examining accelerating test run method for long-service-life aircraft engine |
| CN107247002A (en) * | 2017-04-20 | 2017-10-13 | 北京航空航天大学 | Consider the turbine rotor blade accelerated life test load design method of flight damage |
| CN107941481A (en) * | 2017-09-30 | 2018-04-20 | 中国北方发动机研究所(天津) | A kind of high-temperature duration life assessment method of vehicle supercharger turbine |
| CN111198100A (en) * | 2020-01-09 | 2020-05-26 | 中国航发沈阳发动机研究所 | Method for monitoring service life of key part of aircraft engine |
| CN113848064A (en) * | 2021-08-17 | 2021-12-28 | 蓝箭航天技术有限公司 | Core machine test verification method and device |
| CN114013685A (en) * | 2021-11-15 | 2022-02-08 | 中国航发沈阳发动机研究所 | Heating and pressurizing program design method for test of aircraft engine core |
-
2022
- 2022-02-25 CN CN202210178134.7A patent/CN114544177B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102749196A (en) * | 2011-10-17 | 2012-10-24 | 成都发动机（集团）有限公司 | Service life examining accelerating test run method for long-service-life aircraft engine |
| CN107247002A (en) * | 2017-04-20 | 2017-10-13 | 北京航空航天大学 | Consider the turbine rotor blade accelerated life test load design method of flight damage |
| CN107941481A (en) * | 2017-09-30 | 2018-04-20 | 中国北方发动机研究所(天津) | A kind of high-temperature duration life assessment method of vehicle supercharger turbine |
| CN111198100A (en) * | 2020-01-09 | 2020-05-26 | 中国航发沈阳发动机研究所 | Method for monitoring service life of key part of aircraft engine |
| CN113848064A (en) * | 2021-08-17 | 2021-12-28 | 蓝箭航天技术有限公司 | Core machine test verification method and device |
| CN114013685A (en) * | 2021-11-15 | 2022-02-08 | 中国航发沈阳发动机研究所 | Heating and pressurizing program design method for test of aircraft engine core |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115168990A (en) * | 2022-06-28 | 2022-10-11 | 中国航发沈阳发动机研究所 | Typical transient history spectrum of aircraft engine and determination method thereof |
| CN115168990B (en) * | 2022-06-28 | 2023-08-18 | 中国航发沈阳发动机研究所 | Method for determining typical transient course spectrum of aero-engine |
| CN115753131A (en) * | 2022-12-09 | 2023-03-07 | 中国航发沈阳发动机研究所 | Verification method for high-temperature and high-pressure environment of core engine of aircraft engine |
| CN115597881A (en) * | 2022-12-09 | 2023-01-13 | 中国航发沈阳发动机研究所（Cn） | Method for verifying starting and slow running of core engine of aircraft engine |
| CN115711747A (en) * | 2022-12-09 | 2023-02-24 | 中国航发沈阳发动机研究所 | Aircraft engine core performance calibration verification method |
| CN115586006B (en) * | 2022-12-09 | 2023-02-28 | 中国航发沈阳发动机研究所 | Technical verification method for core engine of aircraft engine |
| CN115586006A (en) * | 2022-12-09 | 2023-01-10 | 中国航发沈阳发动机研究所 | Technical verification method for core engine of aircraft engine |
| CN115753121A (en) * | 2022-12-09 | 2023-03-07 | 中国航发沈阳发动机研究所 | Durability verification method for engine core machine |
| CN115597881B (en) * | 2022-12-09 | 2023-03-10 | 中国航发沈阳发动机研究所 | Method for verifying starting and slow running of core engine of aircraft engine |
| CN115586013B (en) * | 2022-12-09 | 2023-03-14 | 中国航发沈阳发动机研究所 | Durability test system for core machine of aircraft engine |
| CN115586013A (en) * | 2022-12-09 | 2023-01-10 | 中国航发沈阳发动机研究所 | Durability test system for core machine of aircraft engine |
| CN115711747B (en) * | 2022-12-09 | 2023-09-05 | 中国航发沈阳发动机研究所 | Method for calibrating and verifying performance of aircraft engine core engine |
| CN115753131B (en) * | 2022-12-09 | 2023-09-22 | 中国航发沈阳发动机研究所 | High-temperature high-pressure environment verification method for aircraft engine core engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114544177B (en) | 2023-05-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114544177B (en) | Core machine durability test method for typical use state of engine complete machine | |
| CN111198100A (en) | Method for monitoring service life of key part of aircraft engine | |
| CN115640666B (en) | Aero-engine acceleration task test chart compiling method based on damage equivalence | |
| CN115795744B (en) | Method for compiling aviation turbofan engine component level low-cycle fatigue life load spectrum | |
| El-Aini et al. | High cycle fatigue of turbomachinery components-Industry perspective | |
| Seemann et al. | Modeling the life cycle cost of jet engine maintenance | |
| CN107667280B (en) | Scheduled inspection and predicted end-of-life of machine components | |
| CN115356121A (en) | Method for evaluating damage of service life and residual service life of turbine blade in service environment | |
| CN117634220A (en) | Aviation fuel gear pump equivalent acceleration life test method | |
| CN115345439B (en) | Aeroengine comprehensive task spectrum compiling method based on task segments related to operation and frequency mixing of task segments | |
| CN110955932A (en) | Airplane part reliability test method | |
| CN114171139B (en) | Material selecting method for compressor blade | |
| CN115406664A (en) | Method and system for compiling turbo-propeller engine acceleration task trial spectrum | |
| CN115587499A (en) | Typical transient process compilation method for aircraft engine | |
| CN114139276A (en) | Fatigue life analysis method for disk-shaft integrated blisk structure | |
| Chang | Performance diagnosis for turbojet engines based on flight data | |
| CN116244879A (en) | Turbofan engine inclusion evaluation integrated platform | |
| CN112052523B (en) | Helicopter rotor moving part strength design method based on load characteristic comparison | |
| Bazmi et al. | New Thermodynamic Model and Mathematical Analytical in T400 Turboshaft Power Assurance Test Process | |
| CN115031970A (en) | Method for making stand endurance test program of aero-engine and test method | |
| CN114048633B (en) | Airplane high and cold test matrix design method | |
| JOHNSON et al. | The system testability and maintenance program (STAMP)-A testability assessment tool for aerospace systems | |
| CN115935523B (en) | Method for compiling cyclic fatigue life load spectrum of shaft components of aviation turbofan engine | |
| WULF | CF6 jet engine performance deterioration | |
| CN117150253A (en) | Engine health state assessment method based on multitask learning |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |