CN108168892A - Test bay thrust modification method in a kind of aero-engine room - Google Patents
Test bay thrust modification method in a kind of aero-engine room Download PDFInfo
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- CN108168892A CN108168892A CN201711219817.8A CN201711219817A CN108168892A CN 108168892 A CN108168892 A CN 108168892A CN 201711219817 A CN201711219817 A CN 201711219817A CN 108168892 A CN108168892 A CN 108168892A
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- engine
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- 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
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- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
Abstract
Test bay thrust modification method in a kind of aero-engine room, indoor " benchmark " test bay technology requirement determining and choosing：The selection of engine：20~25 hours durations of runs metastable engine of performance is selected, for engine under the conditions of same control law, thrust variation is not more than 0.1%；Engine performance admission technical solution determines：Engine performance will meet associated specifications when enrolling, and formulate detailed technical solution, ensure the true feasible of engine admission performance, reproducible.Advantages of the present invention：It saves and builds outdoor Test Rig and make model engine costliness expense, can complete by the indoor test bay thrust correction technique requirement in school, easy to implement, working specification, each model can be saved and make " model engine " expense.
Description
Technical field
The present invention relates to aero-engine technology field, more particularly to test bay thrust is repaiied in a kind of aero-engine room
Correction method.
Background technology
It currently without outdoor test bay, can not be formed " model engine ", it is impossible to require to complete hair according to national military standard technology
The thrust of Test Rig corrects work in motivation room.Therefore it needs to study a kind of indoor Test Rig thrust modification method, solve
Rack motor power calibration problem, to obtain the true thrust of engine.
Invention content
The purpose of the present invention is to solve test bay thrusts in engine room to correct problem, is really pushed away with obtaining engine
Power has provided test bay thrust modification method in a kind of aero-engine room.
The present invention provides test bay thrust modification methods in a kind of aero-engine room, it is characterised in that：The boat
Test bay thrust modification method includes in empty engine room：
Indoor " benchmark " test bay technology requirement determining and choosing：Indoor " benchmark " test bay technology requires to meet
GJB721-89《Spray fanjet test cell calibration specification in whirlpool》5.2 requirements, engine bench test system meters are required to meet
GJB241《Aeroturbine jet and turbofan general specification》Related request.
The selection of engine：20~25 hours durations of runs metastable engine of performance is selected, engine exists
Under the conditions of same control law, thrust variation is not more than 0.1%；
Engine performance admission technical solution determines：Engine performance will meet associated specifications when enrolling, and formulate
Detailed technical solution ensures the true feasible of engine admission performance, reproducible.
Engine passes through check test performance adjustment, and engine geometry channel Rule adjusting should meet engine control rule
Rule, performance indicator meet the requirement of manufacture technology, and wherein engine speed, delivery temperature and thrust state modulator are required in technology
± 1%；Meet metrology and measurement requirement with the crucial Measurement channel of admission performance related parameter such as rotating speed, temperature, pressure, thrust etc..
All adjustment positions related with performance carry out beating safety lead sealing after benchmark Test Rig enrolls performance test run, no
Allow to be adjusted or change again；Performance admission test program according to specially working out carries out performance admission, is sent out before enrolling performance
Motivation must fully carry out warming-up, and to determine engine actual performance, warm-up period is no less than 40min；At least carry out shape twice
With the admission performance test run of program, the interval time between any test run of admission performance twice starts is no less than 2h.
To reduce the influence enrolled to engine performance of atmospheric environment variation, close under conditions of 15 DEG C of atmospheric temperature into
Row, while atmospheric humidity requirement is no more than 50% during test run, atmospheric pressure is no more than 2%；If performance admission twice measures
The front and rear difference of thrust be more than 5%, reason should be searched, and carry out third time performance admission, until finally measure it is front and rear twice
Until the difference of thrust is no more than 5% during test run；All aircraft accessories are without loading, engine when engine performance enrolls test run
Without bleed.
Advantages of the present invention：
Test bay thrust modification method in aero-engine room of the present invention, save build outdoor Test Rig and
" model engine " expensive expense is made, can be completed by the indoor test bay thrust correction technique requirement in school, easy to implement, behaviour
Make specification, each model can be saved and make " model engine " expense.
Specific embodiment
Embodiment 1
The present invention provides test bay thrust modification methods in a kind of aero-engine room, it is characterised in that：The boat
Test bay thrust modification method includes in empty engine room：
Indoor " benchmark " test bay technology requirement determining and choosing：Indoor " benchmark " test bay technology requires to meet
GJB721-89《Spray fanjet test cell calibration specification in whirlpool》5.2 requirements, engine bench test system meters are required to meet
GJB241《Aeroturbine jet and turbofan general specification》Related request.
The selection of engine：20~25 hours durations of runs metastable engine of performance is selected, engine exists
Under the conditions of same control law, thrust variation is not more than 0.1%；
Engine performance admission technical solution determines：Engine performance will meet associated specifications when enrolling, and formulate
Detailed technical solution ensures the true feasible of engine admission performance, reproducible.
Engine passes through check test performance adjustment, and engine geometry channel Rule adjusting should meet engine control rule
Rule, performance indicator meet the requirement of manufacture technology, and wherein engine speed, delivery temperature and thrust state modulator are required in technology
± 1%；Meet metrology and measurement requirement with the crucial Measurement channel of admission performance related parameter such as rotating speed, temperature, pressure, thrust etc..
All adjustment positions related with performance carry out beating safety lead sealing after benchmark Test Rig enrolls performance test run, no
Allow to be adjusted or change again；Performance admission test program according to specially working out carries out performance admission, is sent out before enrolling performance
Motivation must fully carry out warming-up, and to determine engine actual performance, warm-up period is no less than 40min；At least carry out shape twice
With the admission performance test run of program, the interval time between any test run of admission performance twice starts is no less than 2h.
To reduce the influence enrolled to engine performance of atmospheric environment variation, close under conditions of 15 DEG C of atmospheric temperature into
Row, while atmospheric humidity requirement is no more than 50% during test run, atmospheric pressure is no more than 2%；If performance admission twice measures
The front and rear difference of thrust be more than 5%, reason should be searched, and carry out third time performance admission, until finally measure it is front and rear twice
Until the difference of thrust is no more than 5% during test run；All aircraft accessories are without loading, engine when engine performance enrolls test run
Without bleed.
Embodiment 2
The present invention provides test bay thrust modification methods in a kind of aero-engine room, it is characterised in that：The boat
Test bay thrust modification method includes in empty engine room：
Indoor " benchmark " test bay technology requirement determining and choosing：Indoor " benchmark " test bay technology requires to meet
GJB721-89《Spray fanjet test cell calibration specification in whirlpool》5.2 requirements, engine bench test system meters are required to meet
GJB241《Aeroturbine jet and turbofan general specification》Related request.
The selection of engine：20~25 hours durations of runs metastable engine of performance is selected, engine exists
Under the conditions of same control law, thrust variation is not more than 0.1%；
Engine performance admission technical solution determines：Engine performance will meet associated specifications when enrolling, and formulate
Detailed technical solution ensures the true feasible of engine admission performance, reproducible.
Engine passes through check test performance adjustment, and engine geometry channel Rule adjusting should meet engine control rule
Rule, performance indicator meet the requirement of manufacture technology, and wherein engine speed, delivery temperature and thrust state modulator are required in technology
± 1%；Meet metrology and measurement requirement with the crucial Measurement channel of admission performance related parameter such as rotating speed, temperature, pressure, thrust etc..
To reduce the influence enrolled to engine performance of atmospheric environment variation, close under conditions of 15 DEG C of atmospheric temperature into
Row, while atmospheric humidity requirement is no more than 50% during test run, atmospheric pressure is no more than 2%；If performance admission twice measures
The front and rear difference of thrust be more than 5%, reason should be searched, and carry out third time performance admission, until finally measure it is front and rear twice
Until the difference of thrust is no more than 5% during test run；All aircraft accessories are without loading, engine when engine performance enrolls test run
Without bleed.
Embodiment 3
The present invention provides test bay thrust modification methods in a kind of aero-engine room, it is characterised in that：The boat
Test bay thrust modification method includes in empty engine room：
Indoor " benchmark " test bay technology requirement determining and choosing：Indoor " benchmark " test bay technology requires to meet
GJB721-89《Spray fanjet test cell calibration specification in whirlpool》5.2 requirements, engine bench test system meters are required to meet
GJB241《Aeroturbine jet and turbofan general specification》Related request.
The selection of engine：20~25 hours durations of runs metastable engine of performance is selected, engine exists
Under the conditions of same control law, thrust variation is not more than 0.1%；
Engine performance admission technical solution determines：Engine performance will meet associated specifications when enrolling, and formulate
Detailed technical solution ensures the true feasible of engine admission performance, reproducible.
Engine passes through check test performance adjustment, and engine geometry channel Rule adjusting should meet engine control rule
Rule, performance indicator meet the requirement of manufacture technology, and wherein engine speed, delivery temperature and thrust state modulator are required in technology
± 1%；Meet metrology and measurement requirement with the crucial Measurement channel of admission performance related parameter such as rotating speed, temperature, pressure, thrust etc..
To reduce the influence enrolled to engine performance of atmospheric environment variation, close under conditions of 15 DEG C of atmospheric temperature into
Row, while atmospheric humidity requirement is no more than 50% during test run, atmospheric pressure is no more than 2%；If performance admission twice measures
The front and rear difference of thrust be more than 5%, reason should be searched, and carry out third time performance admission, until finally measure it is front and rear twice
Until the difference of thrust is no more than 5% during test run；All aircraft accessories are without loading, engine when engine performance enrolls test run
Without bleed.
Claims (4)
1. a kind of test bay thrust modification method in aero-engine room, it is characterised in that：It is tried in the aero-engine room
Ride thrust modification method includes：
Indoor " benchmark " test bay technology requirement determining and choosing：Indoor " benchmark " test bay technology requires to meet GJB721-
89《Spray fanjet test cell calibration specification in whirlpool》5.2 requirements, engine bench test system meters are required to meet GJB241《Aviation
Turbojet and turbofan general specification》Related request.
The selection of engine：20~25 hours durations of runs metastable engine of performance is selected, engine is same
Under the conditions of control law, thrust variation is not more than 0.1%；
Engine performance admission technical solution determines：Engine performance will meet associated specifications when enrolling, formulate detailed
Technical solution, ensure engine admission performance it is true feasible, it is reproducible.
2. test bay thrust modification method in aero-engine room described in accordance with the claim 1, it is characterised in that：Engine passes through
Check test performance adjustment is crossed, engine geometry channel Rule adjusting should meet engine control regularity, and performance indicator meets
The requirement of factory technology, wherein engine speed, delivery temperature and thrust state modulator required in technology ± 1%；With enrolling performance
The crucial Measurement channel of relevant parameter such as rotating speed, temperature, pressure, thrust etc. meets metrology and measurement requirement.
3. test bay thrust modification method in aero-engine room described in accordance with the claim 1, it is characterised in that：It is tried in benchmark
All adjustment positions related with performance carry out beating safety lead sealing after the admission performance test run of ride frame, do not allow to be adjusted again or
Variation；Performance admission test program according to specially working out carries out performance admission, and admission performance front engine must be carried out fully
Warming-up, to determine engine actual performance, warm-up period is no less than 40min；It at least carries out twice just as the admission performance of program
Test run, the interval time between any test run of admission performance twice starts are no less than 2h.
4. test bay thrust modification method in aero-engine room described in accordance with the claim 1, it is characterised in that：It is big to reduce
The influence that engine performance is enrolled in gas environmental change carries out, while big during test run close under conditions of 15 DEG C of atmospheric temperature
The requirement of air humidity degree is no more than 50%, and atmospheric pressure is no more than 2%；If the difference before and after the thrust that performance admission twice measures surpasses
Cross 5%, reason should be searched, and carry out third time performance admission, until finally measure front and rear test run twice when thrust difference not
Until 5%；All aircraft accessories are without loading when engine performance enrolls test run, and engine is without bleed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711219817.8A CN108168892A (en) | 2017-11-29 | 2017-11-29 | Test bay thrust modification method in a kind of aero-engine room |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711219817.8A CN108168892A (en) | 2017-11-29 | 2017-11-29 | Test bay thrust modification method in a kind of aero-engine room |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108168892A true CN108168892A (en) | 2018-06-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711219817.8A Pending CN108168892A (en) | 2017-11-29 | 2017-11-29 | Test bay thrust modification method in a kind of aero-engine room |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102053017A (en) * | 2009-11-09 | 2011-05-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Method and system for testing air flow field of indoor engine test-bed |
| CN102393305A (en) * | 2011-10-28 | 2012-03-28 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for calibrating pushing force of trial run table inside engine room |
| CN104596769A (en) * | 2014-12-14 | 2015-05-06 | 中国航空工业集团公司北京长城计量测试技术研究所 | Real thrust measuring and calculating method for test run of aero-engine on indoor test bed |
| CN104777000A (en) * | 2015-05-04 | 2015-07-15 | 中国航空动力机械研究所 | Dynamic calibration method for turboshaft engine test bed |
| CN105300699A (en) * | 2015-11-20 | 2016-02-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for evaluating engine thrust transient performance |
-
2017
- 2017-11-29 CN CN201711219817.8A patent/CN108168892A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102053017A (en) * | 2009-11-09 | 2011-05-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Method and system for testing air flow field of indoor engine test-bed |
| CN102393305A (en) * | 2011-10-28 | 2012-03-28 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for calibrating pushing force of trial run table inside engine room |
| CN104596769A (en) * | 2014-12-14 | 2015-05-06 | 中国航空工业集团公司北京长城计量测试技术研究所 | Real thrust measuring and calculating method for test run of aero-engine on indoor test bed |
| CN104777000A (en) * | 2015-05-04 | 2015-07-15 | 中国航空动力机械研究所 | Dynamic calibration method for turboshaft engine test bed |
| CN105300699A (en) * | 2015-11-20 | 2016-02-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for evaluating engine thrust transient performance |
Non-Patent Citations (3)
| Title |
|---|
| 航空航天工业部四二〇厂: "《GJB721-89》", 24 August 1989 * |
| 贺孝涛 等: ""航空喷气发动机地面试车台校准技术及状态保持方法研究"", 《沈阳航空航天大学学报》 * |
| 魏海涛 等: ""涡喷涡扇发动机试车台校准"", 《计量技术》 * |
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Application publication date: 20180615 |