CN102749196A - Service life examining accelerating test run method for long-service-life aircraft engine - Google Patents
Service life examining accelerating test run method for long-service-life aircraft engine Download PDFInfo
- Publication number
- CN102749196A CN102749196A CN201110314410XA CN201110314410A CN102749196A CN 102749196 A CN102749196 A CN 102749196A CN 201110314410X A CN201110314410X A CN 201110314410XA CN 201110314410 A CN201110314410 A CN 201110314410A CN 102749196 A CN102749196 A CN 102749196A
- Authority
- CN
- China
- Prior art keywords
- engine
- life
- time
- test run
- state
- 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.)
- Pending
Links
Images
Landscapes
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses a service life examining accelerating test run method for a long-service-life aircraft engine. The method mainly comprises: collecting data on using conditions of the engine; calculating working conditions of the engine within a certain time; determining time required by the engine for work each time and distributed time in different working states according to service life requirements, starting times, shut-down times and average single flight time of the engine; carrying out data fusion to form a typical using state curve of the engine according to conventional using operating instructions of the engine; adopting a rainflow counting method to extract major and minor using stats of engine load; adopting a durable-service-life damage equivalence principle to convert minor state time of the engine load into major state time of high load or delete the minor state time of the engine load, and forming an engine high load state using curve; and working out test run procedures to determine actual testing time of the engine. The service life examining accelerating test run method for the engine greatly shortens time and reduces expenses for service life examining test run of the long-service-life aircraft engine.
Description
Technical field
The invention belongs to the experimental technique field of aeromotor; Specifically; The test run method is quickened in the life-span examination that relates to a kind of long-life aeromotor, especially based on the exemplary operation state status of its use and the life-span examination test run technology of life consumption equivalent method.
Background technology
Early stage aeromotor is shorter serviceable life, mainly is employed in interior life-span management form to engine place under repair preset time, so traditional life-span wire examination method is according to carrying out the test run examination actual life of engine.This test run method is simple; Under long situation of given life-span of engine, implement easily, such as certain model aeromotor, be 200 hours serviceable life; Per hour fuel consumption is 1 ton; In one month, just can accomplish the examination to engine life, the examination funds are about 2,000,000, from the time with all can accept economically.But constantly prolong, serviceable life increasingly sophisticated along with the aeromotor structure, and the regulation of cancelling preventive overhaul that has is just safeguarded according to actual conditions.At this moment, if carry out examining actual life test run just to exist problems such as expensive many, that the cycle is long, the actual operating position difference of test run program and outfield is big according to original mode.Such as, present civilian engine life is generally more than 10,000 hours, and per hour fuel consumption is by 5 tons of calculating, and test run just needed at least two years, and only the fuel oil funds just reach Renminbi more than 500,000,000.Test period is long, and funds consumption is big, and the people can't be accepted.
The main aerial mission of fighter plane has several kinds of situation such as aerial fistfight, air to surface, low-latitude flying, and is as shown in Figure 2.The user mode (load condition) of aeromotor in the various aerial missions of aircraft mainly contains parking, slow train, centre and maximum several kinds of load conditions, and engine is in different load conditions, and its throttle lever is in different gear positions.Engine is in different load conditions has different influences to life-span of engine, and dead ship condition can be ignored the influence of engine life, increases gradually successively, and the effect on service life to engine when load is maximum is maximum.The test run examination of Traditional engine life-span; Not distinguishing the different user modes of engine influences engine life, carries out the test run examination actual life by engine without exception, so test run wire examination method science not very; Brought the engine life test run examination time long thus, expense is high.
Development along with aircraft industry; The life-span of aeromotor is more and more longer; Production practices are badly in need of providing a kind of test run method that can quicken the examination of aeromotor life-span of science more; Problems such as to carry out the test period that test run exists actual life according to engine long to solve, and funds consumption is big.
Summary of the invention
Engine life test run examination to prior art; Not distinguishing the different user modes of engine influences engine life; Carry out the problem of test run examination existence without exception actual life by engine; The object of the invention aims to provide a kind of aeromotor life-span long-life examination and quickens the test run method, to shorten aeromotor life-span long-life examination run-in period, reduces life-span examination test run expense.
Basic thought of the present invention is to the engine life not damaged or damage less little load user mode and it is converted to the state that high load capacity uses in obtaining using through derivation; Time with the high engine load state is examined the time as engine life, from tested number and the test period that reaches effective reduction engine.
The test run method is quickened in aeromotor life-span long-life examination provided by the invention, and its main contents comprise:
(1) collects the operating position data of engine when aircraft is carried out different aerial mission;
(2) according to the engine operating position data of collecting; Within a certain period of time average number of starts of statistics engine, stop frequency, minimum steady-working state is adjusted to the number of times of maximum rating, is adjusted to the number of times of maximum rating from aerial minimum steady-working state from ground; In the shared ratio of different aerial missions; In the shared ratio of various user modes, the ambient conditions when different user mode;
(3) on above-mentioned statistical basis; According to life requirements, number of starts, stop frequency and the average single flight time of engine; Confirm the time that each needed time of work of engine and different operating state are distributed, different conditions transition form and number of times, number of starts;
(4) according to the conventional working specification of using of engine, become the typical of engines state to use curve above-mentioned data fusion, and then obtain reflecting that engine rotor rotating speed, the time dependent typicalness of engine interior diverse location place temperature use curve;
(5) use curve according to the typical of engines state, adopt rain stream method, extract main, the less important user mode of engine load;
(6) adopt damage equivalent principle creep rupture life, the load less important state time of engine under different user modes, different loads factor situation is converted into the main state of the high engine load time or deletes formation high engine load state use curve;
(7) request for utilization, test preparation and the personnel according to test platform dispose establishment test run program, confirm the engine actual tests time.
In technique scheme, the aerial mission that engine is carried out in fighter plane mainly contains dog fight, air to surface, low-latitude flying and other aerial mission.The user mode of engine when aircraft is carried out different aerial mission is the engine load state, mainly contains slow train, centre, maximum, state exchange, the anti-several kinds of stastus formats that push away and stop.Wherein maximum user mode is the main load condition of engine, and other user mode is less important load condition.The operating position data of engine when aircraft is carried out different aerial mission can come from the measured data of existing aircraft, also can come from the predetermined engine request for utilization of airplane design.For the data of existing aircraft utilization situation, specifically can from the data such as log, aircraft resume and engine maintenance record of aircraft, collect.
Each user mode of engine, promptly the load condition of engine is corresponding with the engine power control arm gear, and in the aircraft floor minimum steady-working state that goes, engine power control arm is positioned at the slow train gear like engine; In the minimum steady-working state of aircraft airflight, gear in the middle of engine power control arm is positioned at; In aircraft maximal rate working flight state, engine motor oil door bar is positioned at maximum gear.
At the environment of the engine described in the technique scheme in different conditions, the temperature environment when being engine operation, height environment, speed environment etc., said environment comprises its environment on the one hand at least.
In technique scheme, the typical of engines state uses the fusion method of curve to be: the engine start number of times that obtains, different load state and shared time, different conditions conversion times etc. are reasonably made up according to the conventional working specification of using of engine.It generally is starting process that the typical of engines state uses the beginning of curve, and finishes with the parking of engine; After engine start with before stopping, can arrange one section idling rating to be used for the warming-up and the cooling of engine,, even can use intermediateness that engine is carried out warming-up for individual engines; The state exchange of engine, warming-up then can be set after finishing; As from ground minimum steady-working state adjust to maximum rating; Or get back to the minimum working stability duty in ground from middle duty, the typical of engines state uses the conversion times of different operating state in the curve should be suitable with the different conditions conversion times that obtains in the such scheme; Moreover each load condition and shared time can reasonably distribute before and after the different conditions conversion.As previously mentioned, after engine start with before stopping, can distribute one section idling rating to be used for the warming-up and the cooling of engine, also can suitably add a little slow trains or intermediateness between the state exchange, to reduce the lasting maneuvering load of engine.Generally when merging typical of engines state use curve, can require to set environment for use temperature, height and the speed of engine according to different environment.The typical of engines state uses the fusion process of curve as shown in Figure 5.
In technique scheme; Adopting the creep rupture life damage equivalent principle time of the less important state of engine to be converted into time of the main state of high engine load; Usually adopt with engine load increase time conversion proportion and reduce gradually to change; With the time of engine in the less important load condition of slow train, press (5.0～10.0): 1 converts the time of engine in the peak load state to, and the time of the less important load condition in centre is pressed (1.5～3.0): 1 converts the time of engine in the peak load state to; The time of other less important load conditions is deleted, do not consider to convert into the time of peak load state.Convert the less important load condition of the engine time to engine in the concrete ratio of peak load state time, depend on the type of engine, because of engine difference difference.
Rain stream method described in the technique scheme is claimed the cat head method again, and procedure is as shown in Figure 7, and t makes ordinate with the time, and load P makes horizontal ordinate.Like this, the broken line that several peak-to-valley value points are linked to be just looks like a multilayer pagoda roof, and imagines that rain stream stays by certain rule from cat head, can realize rain stream cycle count.The primitive rule of rain-flow counting is:
---rain stream originates in each peak value, valley successively;
---the rain stream that originates in peak value (valley) will be located to fall at next valley (peak value), and the rain stream that falls runs into following two kinds of situation then to be stopped:
The rain stream that originates in peak value runs into the peak value that is equal to or higher than it just to be stopped;
The rain stream that originates in valley runs into the valley that is equal to or less than it just to be stopped;
---the rain stream that originates in peak value, valley runs into top-down rain stream just to be stopped, and at this moment, flows to such an extent that starting point and terminal point are kept a circulation in mind according to this rain.
Use engine life examination provided by the invention to quicken the test run method; Engine operating position by collection obtains is set out; A typicalness that obtains in the engine use uses curve; According to the principle of rain stream method, identify in the examination test run not damaged or damage less state (being less important state) and it is converted to higher load condition or deletion, and then obtain a higher load condition use curve that can be used for actual examination test run with the life damage equivalence.Methodological science provided by the invention is reasonable, foundation is abundant, and transformation result more approaches actual conditions, and conversion accuracy and reliability are higher; And method of the present invention is simple, easy to operate, thereby has reduced the life-span endurance test that engine is wasted time and energy, and for long-life engine designs with engineering development basic data is provided.
Description of drawings
Accompanying drawing 1 is that test run method step sketch is quickened in long-life engine life-span examination of the present invention.
Accompanying drawing 2 is engine load condition curve maps when aircraft is carried out each main aerial mission.
Accompanying drawing 3 is that the engine of an embodiment is in carrying out different aerial mission proportion distribution plans.
Accompanying drawing 4 is each user mode proportion distribution plan of engine of an embodiment.
Accompanying drawing 5 is engine environment for use temperature profiles of an embodiment.
Accompanying drawing 6 is typical of engines user mode curve fusion process synoptic diagram of the present invention.
Accompanying drawing 7 is rain stream method principle schematic, among the figure the 2,4,6, the 8th, and load peak point, the 1,3,5, the 7th, load peak valley point.
Embodiment
Certain model long-life high thrust motor is the outfit engine of existing aircraft, and it is 2000 hours that (use) life-span is overhauled in the design of engine, and per hour fuel consumption is 3 tons.The life-span examination of engine adopts the method for acceleration test run of the present invention to carry out the life-span examination.Life-span examination process is following:
1, from the data such as log, aircraft resume and engine maintenance record of aircraft, collects the data of aircraft utilization situation;
2, according to the data of collecting; The average number of starts of statistics engine in 2000 hours, stop frequency, ground are adjusted to the number of times of maximum rating, are adjusted to the number of times of maximum rating from minimum steady-working state in the air from minimum steady-working state, are respectively 1321 times, 1207 times, 1235 times, 698 times; Drafting place engine is in the load condition curve (shown in accompanying drawing 2) of main aerial mission; Add up engine in the shared ratio of different aerial missions (shown in accompanying drawing 3), dog fight task 30%, air-to-surface mission 40%, low idle task 20%, other tasks 10%; And then obtain the shared ratio of various load conditions and distribute by (shown in accompanying drawing 4), slow train 45%, middle 20%, maximum 10%, state change 9%, instead push away 8%, stop 8%; Temperature environment situation (shown in the accompanying drawing 5) when different user mode.
3, on above-mentioned statistical basis; Life requirements, number of starts, stop frequency according to engine; Confirm that the engine start number of times is 1207; Each needed time of work be 1 hour 39 minutes 25 seconds (with 2000 hours life-spans of engine divided by stop frequency 1207) and different operating state time of being distributed (according to the shared ratio distributed data of adding up of various load conditions; Be modified to slightly: slow train 46.5%; Middle 23%, maximum 8%, state exchange 7.5%, instead push away 7%, stop 8%), different conditions transition form and number of times (the ground number of times of adjusting to maximum rating from minimum steady-working state is 1, adjusts to the number of times 0.5 of maximum rating in the air from minimum steady-working state).
4, according to the conventional working specification of using of engine, become engine to use curve above-mentioned data fusion.In this practical implementation; At first begin to be designed to engine start with what engine used curve; Check with the warming-up of realization engine and to engine behavior by stepped increase engine condition behind the idling rating work 5min, stop in intermediateness at last; Intermediateness stops the initial stage and near ending phase, accomplishes the conversion that amounts to 6 centres, idling rating, to gather together enough the requirement of idling rating working time; In the interstage that intermediateness stops, accomplish the conversion of 3 intermediatenesses to takeoff condition, to satisfy the requirement of state exchange number of times, gather together enough the requirement of maximum rating working time simultaneously; Be that engine staged ground reduces user mode to idling rating after intermediateness stops and finishes, the last 5min of idling rating uses the anti-push mode of engine and stops, and so far whole typicalness uses the curve fusion process to finish basically.According to the requirement of engine environment for use, temperature, height and Mach number that different conditions uses in using curve, have also been stipulated.For further analysis, typical state uses the curve ordinate also to use stress or temperature is represented.Fusion process is shown in accompanying drawing 5.
5, use curve according to the typical of engines state, adopt rain stream method, extract main, the less important state of engine load.Rain stream ratio juris is shown in accompanying drawing 7.
6, adopt damage equivalent principle creep rupture life, the less important state of the load time under the different user modes of engine, the different loads factor situation is converted into the main state of the high engine load time or deletes formation high engine load state use curve.The slow train less important state of loading converted the main state of high load capacity into by 5: 1, and the less important state of shoulder load converted the main state of high load capacity into by 1.5: 1, and other less important state time of loading is by deleting.
7, request for utilization, test preparation and the personnel according to test platform dispose establishment test run program, confirm that the engine actual tests time is 150 hours.Per hour test fuel consumption and be not more than 4 tons.
Adopt acceleration test run method of the present invention, effectively shortened test period, the more important thing is that the fuel consume cost is merely original 1/10, has saved a large amount of funds spendings.
Claims (10)
1. the test run method is quickened in an aeromotor life-span long-life examination, it is characterized in that mainly comprising:
(1) collects the operating position data of engine when aircraft is carried out different aerial mission;
(2) according to the engine operating position data of collecting; Within a certain period of time average number of starts of statistics engine, stop frequency, minimum steady-working state is adjusted to the number of times of maximum rating, is adjusted to the number of times of maximum rating from aerial minimum steady-working state from ground; In the shared ratio of different aerial missions; In the shared ratio of various user modes, the ambient conditions when different user mode;
(3) on above-mentioned statistical basis; According to life requirements, number of starts, stop frequency and the average single flight time of engine; Confirm the time that each needed time of work of engine and different operating state are distributed, different conditions transition form and number of times, number of starts;
(4) according to the conventional working specification of using of engine, become the typical of engines state to use curve above-mentioned data fusion, and then obtain reflecting that engine rotor rotating speed, the time dependent typicalness of engine interior diverse location place temperature use curve;
(5) use curve according to the typical of engines state, adopt rain stream method, extract main, the less important user mode of engine load;
(6) adopt damage equivalent principle creep rupture life, the load less important state time of engine under different user modes, different loads factor situation is converted into the main state of the high engine load time or deletes formation high engine load state use curve;
(7) request for utilization, test preparation and the personnel according to test platform dispose establishment test run program, confirm the engine actual tests time.
2. the test run method is quickened in aeromotor life-span long-life according to claim 1 examination, it is characterized in that said aerial mission mainly contains dog fight, air to surface and low-latitude flying and other.
3. the test run method is quickened in aeromotor life-span long-life examination according to claim 1, it is characterized in that said user mode mainly contains slow train, centre, maximum, state exchange, the anti-several kinds of stastus formats that push away and stop.
4. the test run method is quickened in aeromotor life-span long-life examination according to claim 3, it is characterized in that said maximum user mode is the main load condition of engine, and other user mode is less important load condition.
5. the test run method is quickened in aeromotor life-span long-life examination according to claim 4; It is characterized in that converting engine to engine in the ratio of peak load state time in the less important load condition time; Reduce gradually to change with the engine load scaling up, when the peak load state 1 to 1.
6. the test run method is quickened in aeromotor life-span long-life examination according to claim 5; It is characterized in that engine in time of the less important load condition of slow train by (5.0～10.0): 1 converts the time of engine in the peak load state to, in time of the less important load condition in centre by (1.5～3.0): 1 converts the time of engine in the peak load state to.
7. quicken the test run method according to the examination of described aeromotor life-span long-life of one of claim 1 to 6, it is characterized in that said environment is at least the environment of one side in temperature, height and the speed.
8. quicken the test run method according to the examination of described aeromotor life-span long-life of one of claim 1 to 6, it is characterized in that engine request for utilization predetermined when the operating position data of engine when aircraft is carried out different aerial mission come from measured data or the airplane design of existing aircraft.
9. the test run method is quickened in aeromotor life-span long-life according to claim 7 examination, it is characterized in that engine request for utilization predetermined when the operating position data of engine when aircraft is carried out different aerial mission come from measured data or the airplane design of existing aircraft.
10. the test run method is quickened in aeromotor life-span long-life examination according to claim 9, it is characterized in that the operating position data that engine is carried out different aerial missions in aircraft come from log, aircraft resume and the engine maintenance record that has aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110314410XA CN102749196A (en) | 2011-10-17 | 2011-10-17 | Service life examining accelerating test run method for long-service-life aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110314410XA CN102749196A (en) | 2011-10-17 | 2011-10-17 | Service life examining accelerating test run method for long-service-life aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102749196A true CN102749196A (en) | 2012-10-24 |
Family
ID=47029564
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110314410XA Pending CN102749196A (en) | 2011-10-17 | 2011-10-17 | Service life examining accelerating test run method for long-service-life aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102749196A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104748967A (en) * | 2013-12-27 | 2015-07-01 | 中航商用航空发动机有限责任公司 | Method for optimizing turbofan engine performance simulation platform under the condition of rain absorption |
| CN105608316A (en) * | 2015-12-17 | 2016-05-25 | 中国航空工业集团公司沈阳发动机设计研究所 | Method for calculating actual service life of flame tube in main combustion chamber of engine |
| CN107092964A (en) * | 2016-10-31 | 2017-08-25 | 海航航空技术有限公司 | The first inspection control method of aircraft maintenance project |
| CN110414038A (en) * | 2019-06-12 | 2019-11-05 | 江西冠一通用飞机有限公司 | A kind of Aircraft life monitoring method based on history flying quality |
| CN110646205A (en) * | 2019-10-31 | 2020-01-03 | 中国航发成都发动机有限公司 | Acceleration equivalent test method for long-life aircraft engine |
| CN112431676A (en) * | 2020-11-19 | 2021-03-02 | 中国航发沈阳发动机研究所 | Self-protection control method for aircraft engine in non-warmed state |
| CN112710472A (en) * | 2020-12-24 | 2021-04-27 | 奇瑞汽车股份有限公司 | Engine cold start test method and device |
| CN114544177A (en) * | 2022-02-25 | 2022-05-27 | 中国航发沈阳发动机研究所 | Core machine durability test method for typical use state of complete engine |
| CN114662212A (en) * | 2022-02-22 | 2022-06-24 | 中国航发沈阳发动机研究所 | Method for determining typical transient working history spectrum of aero-engine |
| CN114876647A (en) * | 2022-06-01 | 2022-08-09 | 中国航发沈阳发动机研究所 | Method and system for automatically executing warming-up of aircraft engine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS593335A (en) * | 1982-06-30 | 1984-01-10 | Hitachi Ltd | Method for maintenance and monitor of gas turbine plant |
| JP2005194977A (en) * | 2004-01-09 | 2005-07-21 | Hino Motors Ltd | Device and method for testing transient characteristic of internal combustion engine |
| CN101620045A (en) * | 2009-07-31 | 2010-01-06 | 北京航空航天大学 | Method for evaluating reliability of stepping stress quickened degradation experiment based on time sequence |
| CN101894221A (en) * | 2010-08-02 | 2010-11-24 | 北京航空航天大学 | Method for predicting service life of product by accelerated degradation testing based on degenerate distribution non-stationary time series analysis |
-
2011
- 2011-10-17 CN CN201110314410XA patent/CN102749196A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS593335A (en) * | 1982-06-30 | 1984-01-10 | Hitachi Ltd | Method for maintenance and monitor of gas turbine plant |
| JP2005194977A (en) * | 2004-01-09 | 2005-07-21 | Hino Motors Ltd | Device and method for testing transient characteristic of internal combustion engine |
| CN101620045A (en) * | 2009-07-31 | 2010-01-06 | 北京航空航天大学 | Method for evaluating reliability of stepping stress quickened degradation experiment based on time sequence |
| CN101894221A (en) * | 2010-08-02 | 2010-11-24 | 北京航空航天大学 | Method for predicting service life of product by accelerated degradation testing based on degenerate distribution non-stationary time series analysis |
Non-Patent Citations (2)
| Title |
|---|
| 张逸民: "燃气涡轮发动机加速模拟试车加速系数的估算", 《哈尔滨工业大学学报》 * |
| 龚庆祥: "飞机环境振动状态-时间谱的编制与应用", 《航空学报》 * |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104748967B (en) * | 2013-12-27 | 2017-10-31 | 中国航发商用航空发动机有限责任公司 | Inhale the fanjet performance simulation pad optimization method under rain operating mode |
| CN104748967A (en) * | 2013-12-27 | 2015-07-01 | 中航商用航空发动机有限责任公司 | Method for optimizing turbofan engine performance simulation platform under the condition of rain absorption |
| CN105608316A (en) * | 2015-12-17 | 2016-05-25 | 中国航空工业集团公司沈阳发动机设计研究所 | Method for calculating actual service life of flame tube in main combustion chamber of engine |
| CN105608316B (en) * | 2015-12-17 | 2018-11-13 | 中国航空工业集团公司沈阳发动机设计研究所 | A method of calculating engine main chamber burner inner liner actual life |
| CN107092964A (en) * | 2016-10-31 | 2017-08-25 | 海航航空技术有限公司 | The first inspection control method of aircraft maintenance project |
| CN107092964B (en) * | 2016-10-31 | 2020-10-09 | 海航航空技术股份有限公司 | First inspection control method for aircraft maintenance project |
| CN110414038B (en) * | 2019-06-12 | 2022-09-30 | 江西冠一通用飞机有限公司 | Airplane service life monitoring method based on historical flight data |
| CN110414038A (en) * | 2019-06-12 | 2019-11-05 | 江西冠一通用飞机有限公司 | A kind of Aircraft life monitoring method based on history flying quality |
| CN110646205A (en) * | 2019-10-31 | 2020-01-03 | 中国航发成都发动机有限公司 | Acceleration equivalent test method for long-life aircraft engine |
| CN112431676A (en) * | 2020-11-19 | 2021-03-02 | 中国航发沈阳发动机研究所 | Self-protection control method for aircraft engine in non-warmed state |
| CN112431676B (en) * | 2020-11-19 | 2022-03-04 | 中国航发沈阳发动机研究所 | Self-protection control method for aircraft engine in non-warmed state |
| CN112710472A (en) * | 2020-12-24 | 2021-04-27 | 奇瑞汽车股份有限公司 | Engine cold start test method and device |
| CN114662212A (en) * | 2022-02-22 | 2022-06-24 | 中国航发沈阳发动机研究所 | Method for determining typical transient working history spectrum of aero-engine |
| CN114662212B (en) * | 2022-02-22 | 2024-03-19 | 中国航发沈阳发动机研究所 | Method for determining typical transient operation process spectrum of aero-engine |
| CN114544177A (en) * | 2022-02-25 | 2022-05-27 | 中国航发沈阳发动机研究所 | Core machine durability test method for typical use state of complete engine |
| CN114876647A (en) * | 2022-06-01 | 2022-08-09 | 中国航发沈阳发动机研究所 | Method and system for automatically executing warming-up of aircraft engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102749196A (en) | Service life examining accelerating test run method for long-service-life aircraft engine | |
| CN109835375B (en) | High-speed railway train automatic driving system based on artificial intelligence technology | |
| CN104375502B (en) | A kind of ground testing system being applicable to stratospheric airship power-supply controller of electric | |
| CN107387346B (en) | A kind of collection fraction and continous way generate electricity the pavement deceleration strip generating device that combines | |
| CN104140060A (en) | Synchronous jacking system of airplane | |
| CN209241054U (en) | Track power flatcar and its braking system | |
| CN201757031U (en) | Vertical shaft type multistage-fan-blade wind generator | |
| CN212172579U (en) | Comprehensive test bed for oil-electricity hybrid power transmission system of rotary wing aircraft | |
| CN102707231B (en) | Generator set primary frequency regulation analysis system based on matlab/simulink | |
| CN103698109B (en) | A kind of detent high-speed and energy-saving life experiment platform | |
| CN103192996A (en) | Method for determining drift-down flight path of large airplane | |
| CN110928273A (en) | Automatic testing method for automatic power generation control function test of photovoltaic power station | |
| CN109435927A (en) | Track power flatcar and its braking system and brake control method | |
| CN207274439U (en) | The parking systems energy supply station utilized based on distributed multiple-energy-source | |
| CN203732256U (en) | Turnover mechanism test platform | |
| CN210239914U (en) | Wind turbine blade on-line monitoring system | |
| Manicolo et al. | Investigating the power and energy flows for a kinetic energy recovery system from a landing aircraft | |
| Loth et al. | Super-rated offshore wind turbine with energy storage | |
| CN202102297U (en) | Engineering machinery vehicle remote management system | |
| Czarnigowski et al. | Analysis of operating parameters of the aircraft piston engine in real operating conditions | |
| CN110525454A (en) | A kind of state automatic identification method that diesel locomotive passes through tunnel | |
| Geng | Analysis and countermeasures to flight delay based on statistical data | |
| CN105788371A (en) | Systematic method for improving taking-off utilization rate of airport runway | |
| Peng et al. | Research of Aero-Engine Life Prediction Based on Take-Off EGTM | |
| Cao | Systems architecture trade study of more electric aircraft based on economic evaluation |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20121024 |