CN106525444A - Jet-engine-gas-based apparatus and method for thermal shock and thermal fatigue testing - Google Patents
Jet-engine-gas-based apparatus and method for thermal shock and thermal fatigue testing Download PDFInfo
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- CN106525444A CN106525444A CN201610853810.0A CN201610853810A CN106525444A CN 106525444 A CN106525444 A CN 106525444A CN 201610853810 A CN201610853810 A CN 201610853810A CN 106525444 A CN106525444 A CN 106525444A
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- thermal shock
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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
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses a jet-engine-gas-based apparatus and method for thermal shock and thermal fatigue testing. When a micro turbine engine works, fuel gas from a jet nozzle is used as a gas source; after convergence of the gas with cooling gas in a mixing device with a bypass, tail gas with the adjustable temperature is generated and is used as high-temperature bleed air for testing; a bleed air jet position for thermal shock is adjusted by an adjustable support frame; and a periodic thermal shock work condition of a test piece is simulated by rotation of the test piece on a rotary test stand. A bleed air temperature control system formed by a thermocouple, a cooling gas bypass, an electrically controlled butterfly valve, and a controller and the like is used for controlling the temperature of bleed air to be in a preset test range. Using the apparatus provided by the invention, the technical support can be provided for thermal shock and thermal fatigue testing and analysis of the thermal end component of the aero-engine.
Description
Technical field
The present invention relates to aero-engine hot-end component or other be related to thermal shock and thermal fatigue test technical field.
Background technology
The portion such as the hot-end component of aero-engine, such as combustor, the turbine disk, rotor, stator, after-burner, jet pipe
Operationally due to the change of engine behavior, Jing often meets with the problem of thermal shock and heat exhaustion to part, and the problems referred to above are in boat
Must pay attention to during empty numbers of hot-side engine part design and study, at present, how be manufactured similarly to boat in laboratory conditions
Fast-changing temperature field under the conditions of empty numbers of hot-side engine component working, realizes the thermal shock and thermal fatigue test of associated components
It is a difficult problem.Accordingly, it would be desirable to develop a kind of new assay device to solve the above problems.
The content of the invention
For the problems referred to above and Shortcomings, the invention provides test battery device and method, the device reliably can be produced
Raw controllable high-temperature combustion gas stream is used as thermal shock and the source of the gas of thermal fatigue test, and using simply driving, transmission and installs regulation
Mechanism, realizes the thermal shock cycle of rotary part and the purpose of thermal fatigue test.
For achieving the above object, assay device of the present invention can be adopted the following technical scheme that：
A kind of thermal shock and thermal fatigue test apparatus based on jet engine combustion gas, it is characterised in that：Including vertically to
The rotating shaft of upper extension, be installed in rotating shaft and with rotating shaft rotate test board, drive shaft rotate driving means, installed in examination
Test the testpieces of disk outer rim, be arranged above testpieces and spout towards testpieces turbo-jet engine, house worm gear spray
The test jet pipe of gas electromotor, the tapping equipment being arranged at below testpieces；The tapping equipment include trumpet-shaped collection port,
Delivery pipe below collection port and the floss hole below delivery pipe, are provided with cooling nozzles in the delivery pipe.
In the present invention, testpieces is arranged on the whirling test stand, can carry out constant speed rotation according to test requirements document；Can be logical
Cross turbo-jet engine controllable high-temperature combustion gas stream is produced as the source of the gas simulation test piece of thermal shock and thermal fatigue test by week
Phase thermal shock operating mode, can also carry out the complicated thermal shock test for considering centrifugal force；The tapping equipment for arranging simultaneously can be to waste gas
Lowered the temperature and dilution process after discharge, it is ensured that the experimental enviroment of test site and safety.
And the test method in the present invention can be employed the following technical solutions：
Start driving means, testing stand is rotated by the default thermal shock frequency of thermal shock test, cooling nozzles in delivery pipe
Start cooling operations；
Turbo-jet engine is adjusted to predeterminated position,
Turbo-jet engine outlet gas temperature stabilization starts the thermal shock test of testpieces to test requirements document；
Off-test, closes assay device.
Description of the drawings
Fig. 1 is the structural representation of thermal shock of the present invention based on microjet combustion gas and thermal fatigue test apparatus
Figure.
Specific embodiment
Below in conjunction with the accompanying drawings, further elucidate the present invention, it should be understood that these embodiments be merely to illustrate the present invention and without
In the scope for limiting the controllable hail discharger of aero-engine environmental test of the present invention, after the present invention has been read, this
Modification of the art personnel to the various equivalent form of values of the present invention falls within the application claims limited range.
Refer to shown in Fig. 1, the present invention is disclosed a kind of thermal shock based on microjet combustion gas and tried with heat exhaustion
Experiment device, including the rotating shaft 17 for extending straight up, is installed in rotating shaft 17 and turns with the test board 25 of the rotation of rotating shaft 17, driving
The driving means of axle rotation, base 21, the base 21 are provided with the shelf for carrying positioning rotating shaft 17, and the driving means also set
Put 21 on base.Wherein rotating shaft 17 is positioned with one group of thrust bearing 18 and one group of plain bearing 19；Test board 25 is with upper and lower two
Group briquetting 26 is arranged in rotating shaft 17.In the present embodiment, driving means include motor 23, install the installed part 22 of motor 23
And the speed change system 20 of connection motor output shaft and rotating shaft.Realized by the rotating speed of 23 adjustment of rotational speed rotating shaft 17 of controlled motor
Controllable thermal shock frequency, the thermal shock cycle operating mode of simulation test piece 28, or the complicated thermal shock operating mode with centrifugal force load.
Also include the testpieces 28 installed in 25 outer rim of test board, be arranged above testpieces 28 and spout is towards the miniature of testpieces 28
Turbo-jet engine 1, the test jet pipe 2 for housing turbo-jet engine 1, carrying turbo-jet engine 1 and test jet pipe 2
Carriage assembly, the carriage assembly includes scalable truss 6, vertical type cylinder support 9.Truss 6 adopts 11 slide rail of a set of roller
10 and 7 tooth bar of gear, 8 translation device be arranged on vertical type cylinder support 9 on.Here, using roller slide rail 10 and rack-and-pinion translation
Device 8 is arranged on the vertical type cylinder support 9, and the vertical type cylinder support 9 is supported by the reinforcement 12 for being welded on bottom, is made
With the adjustment horizontal level of universal wheel 13 positioned at 9 bottom of vertical type cylinder support, thermal shock test can be determined according to test requirements document
Use bleed eject position.In addition, test 2 inwall of jet pipe is circumferentially provided with by cooling gas in 1 nozzle of turbo-jet engine
Road nozzle 5, the connection choke valve 4 of cooling gas bypass nozzle 5 and outside cooling source of the gas 3.The test outlet of jet pipe 2 is provided with thermometric use
Thermocouple sensor 27, thermocouple sensor 27 and choke valve 4 connect into control loop with PRC controllers 29.Here, by electricity
The bleed temperature control of the parts such as even sensor 27, cooling gas bypass nozzle 5, choke valve 4, PRC controllers 29 composition
System, cooling compressed air or liquid nitrogen gas enter engine gas by the cooling bleed bypass and nozzle and blend,
Adjustment fuel gas temperature, can be according to test requirements document Control experiment bleed temperature in preset range.
Also include being arranged at the tapping equipment 14 below testpieces 28.The tapping equipment include trumpet-shaped collection port,
Delivery pipe below collection port and the floss hole below delivery pipe 16, are provided with cooling nozzles 15 in the delivery pipe.
By cooling nozzles 15 spray water waste gas is lowered the temperature and dilution process after discharge, it is ensured that the experimental enviroment of test site and peace
Entirely.
Further, annular guard board 24 is provided with around the testpieces 28, and collection port is located at 24 scope of annular guard board
Within.
And the test method of said apparatus is：
Start driving means, testing stand is rotated by the default thermal shock frequency of thermal shock test, cooling nozzles in delivery pipe
Start cooling operations；
Turbo-jet engine is adjusted to predeterminated position,
Turbo-jet engine outlet gas temperature stabilization starts the thermal shock test of testpieces to test requirements document；
Off-test, closes assay device.
In addition, the concrete methods of realizing and approach of the present invention is a lot, the above is only the preferred embodiment of the present invention.
It should be pointed out that for those skilled in the art, under the premise without departing from the principles of the invention, can also do
Go out some improvements and modifications, these improvements and modifications also should be regarded as protection scope of the present invention.It is clearly not each in the present embodiment
Ingredient can use prior art to be realized.
Claims (8)
1. a kind of thermal shock and thermal fatigue test apparatus based on jet engine combustion gas, it is characterised in that：Including straight up
The rotating shaft of extension, be installed in rotating shaft and with rotating shaft rotate test board, drive shaft rotate driving means, installed in test
The testpieces of disk outer rim, be arranged above testpieces and spout towards testpieces turbo-jet engine, house turbo-jet
The test jet pipe of electromotor, the tapping equipment being arranged at below testpieces；The tapping equipment includes trumpet-shaped collection port, position
In the delivery pipe below collection port and the floss hole below delivery pipe, in the delivery pipe, cooling nozzles are provided with.
2. the thermal shock and thermal fatigue test apparatus based on jet engine combustion gas according to claim 1, its feature exist
In：The driving means include the speed change system of motor and connection motor output shaft and rotating shaft.
3. the thermal shock and thermal fatigue test apparatus based on jet engine combustion gas according to claim 1 and 2, its feature
It is：Also include base, the base is provided with the shelf for carrying positioning rotating shaft, and the driving means are also disposed on base.
4. the thermal shock and thermal fatigue test apparatus based on jet engine combustion gas according to claim 3, its feature exist
In：The rotating shaft is provided with the briquetting component of test board clamping position.
5. the thermal shock and thermal fatigue test apparatus based on jet engine combustion gas according to claim 1, its feature exist
In：Also include the carriage assembly for carrying turbo-jet engine and test jet pipe, the carriage assembly includes scalable truss, stands
Formula cylindrical holder；Truss adopts a set of roller slide rail and rack-and-pinion translation device to be arranged on vertical type cylinder support.
6. the thermal shock and thermal fatigue test apparatus based on jet engine combustion gas according to claim 1, its feature exist
In：Test nozzle wall is circumferentially provided with cooling gas bypass nozzle, cooling gas bypass in turbo-jet engine nozzle
Nozzle connects choke valve and outside cooling source of the gas；Test nozzle exit is provided with thermocouple for measuring temperature sensor, thermocouple sensing
Device and choke valve connect into control loop with PRC controllers.
7. the thermal shock and thermal fatigue test apparatus based on jet engine combustion gas according to claim 1 and 2, its feature
It is：Annular guard board is provided with around the testpieces, and within the scope of collection port is located at annular guard board.
8. the such as test of thermal shock and thermal fatigue test apparatus of any one of the claim 1 to 7 based on jet engine combustion gas
Method, it is characterised in that：
Start driving means, testing stand is rotated by the default thermal shock frequency of thermal shock test, cooling nozzles start in delivery pipe
Cooling operations；
Turbo-jet engine is adjusted to predeterminated position,
Turbo-jet engine outlet gas temperature stabilization starts the thermal shock test of testpieces to test requirements document；
Off-test, closes assay device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610853810.0A CN106525444A (en) | 2016-09-27 | 2016-09-27 | Jet-engine-gas-based apparatus and method for thermal shock and thermal fatigue testing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610853810.0A CN106525444A (en) | 2016-09-27 | 2016-09-27 | Jet-engine-gas-based apparatus and method for thermal shock and thermal fatigue testing |
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| CN106525444A true CN106525444A (en) | 2017-03-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610853810.0A Pending CN106525444A (en) | 2016-09-27 | 2016-09-27 | Jet-engine-gas-based apparatus and method for thermal shock and thermal fatigue testing |
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| CN (1) | CN106525444A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112665864A (en) * | 2020-11-12 | 2021-04-16 | 南京航空航天大学 | Device and method for simulating random thermal shock load of aircraft engine |
| CN112710870A (en) * | 2020-12-21 | 2021-04-27 | 成都成发泰达航空科技有限公司 | Performance detection device for APU (auxiliary Power Unit) speed sensor |
| CN112730021A (en) * | 2020-11-30 | 2021-04-30 | 湘潭大学 | Vibration thermal shock coupling service working condition loading system and method |
| CN115574348A (en) * | 2021-07-05 | 2023-01-06 | 中国航发商用航空发动机有限责任公司 | Gas spraying system, thermal shock fatigue tester and gas spraying cooling method |
| WO2024077947A1 (en) * | 2022-10-12 | 2024-04-18 | 天津航天瑞莱科技有限公司 | Test run system for pulsating engine |
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| CN1546974A (en) * | 2003-12-09 | 2004-11-17 | 西北工业大学 | Aeroengine materials hot end environment experimental simulation method and device |
| US8281649B1 (en) * | 2010-06-11 | 2012-10-09 | Florida Turbine Technologies, Inc. | Advanced hot section materials and coatings test rig |
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| CN104634808A (en) * | 2015-01-20 | 2015-05-20 | 浙江大学宁波理工学院 | Device and method for thermal fatigue testing of metal material for manufacturing die casting mould |
| CN105699235A (en) * | 2016-04-28 | 2016-06-22 | 西安交通大学 | Gradient thermal shock test device based on halogen lamp cofocal heating technology |
| CN105890881A (en) * | 2016-04-06 | 2016-08-24 | 北京航空航天大学 | Thermal fatigue test device capable of simulating gas environment |
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| CN1546974A (en) * | 2003-12-09 | 2004-11-17 | 西北工业大学 | Aeroengine materials hot end environment experimental simulation method and device |
| US8281649B1 (en) * | 2010-06-11 | 2012-10-09 | Florida Turbine Technologies, Inc. | Advanced hot section materials and coatings test rig |
| CN103674753A (en) * | 2013-12-09 | 2014-03-26 | 昆明理工大学 | Test platform for thermal shock and thermal fatigue |
| CN203745188U (en) * | 2014-01-17 | 2014-07-30 | 昆明理工大学 | Test bench for simulating heat shock and heat fatigue of heated component |
| CN104634808A (en) * | 2015-01-20 | 2015-05-20 | 浙江大学宁波理工学院 | Device and method for thermal fatigue testing of metal material for manufacturing die casting mould |
| CN105890881A (en) * | 2016-04-06 | 2016-08-24 | 北京航空航天大学 | Thermal fatigue test device capable of simulating gas environment |
| CN105699235A (en) * | 2016-04-28 | 2016-06-22 | 西安交通大学 | Gradient thermal shock test device based on halogen lamp cofocal heating technology |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112665864A (en) * | 2020-11-12 | 2021-04-16 | 南京航空航天大学 | Device and method for simulating random thermal shock load of aircraft engine |
| CN112665864B (en) * | 2020-11-12 | 2022-05-03 | 南京航空航天大学 | Device and method for simulating random thermal shock load of aircraft engine |
| CN112730021A (en) * | 2020-11-30 | 2021-04-30 | 湘潭大学 | Vibration thermal shock coupling service working condition loading system and method |
| CN112710870A (en) * | 2020-12-21 | 2021-04-27 | 成都成发泰达航空科技有限公司 | Performance detection device for APU (auxiliary Power Unit) speed sensor |
| CN112710870B (en) * | 2020-12-21 | 2022-07-08 | 成都成发泰达航空科技有限公司 | Performance detection device for APU (auxiliary Power Unit) speed sensor |
| CN115574348A (en) * | 2021-07-05 | 2023-01-06 | 中国航发商用航空发动机有限责任公司 | Gas spraying system, thermal shock fatigue tester and gas spraying cooling method |
| CN115574348B (en) * | 2021-07-05 | 2023-11-17 | 中国航发商用航空发动机有限责任公司 | Gas spraying system, thermal shock fatigue tester and gas spraying cooling method |
| WO2024077947A1 (en) * | 2022-10-12 | 2024-04-18 | 天津航天瑞莱科技有限公司 | Test run system for pulsating engine |
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Application publication date: 20170322 |