CN103267636B - For the heating arrangement of aero-engine spindle thermal state strength test - Google Patents
For the heating arrangement of aero-engine spindle thermal state strength test Download PDFInfo
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- CN103267636B CN103267636B CN201310170199.8A CN201310170199A CN103267636B CN 103267636 B CN103267636 B CN 103267636B CN 201310170199 A CN201310170199 A CN 201310170199A CN 103267636 B CN103267636 B CN 103267636B
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- 238000012360 testing method Methods 0.000 title claims abstract description 56
- 238000010438 heat treatment Methods 0.000 title claims abstract description 34
- 238000005485 electric heating Methods 0.000 claims abstract description 21
- 238000000429 assembly Methods 0.000 claims abstract description 4
- 230000000712 assembly Effects 0.000 claims abstract description 4
- 238000005259 measurement Methods 0.000 claims description 7
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 6
- 239000010425 asbestos Substances 0.000 claims description 6
- 229910052895 riebeckite Inorganic materials 0.000 claims description 6
- 239000004744 fabric Substances 0.000 claims description 3
- 238000009413 insulation Methods 0.000 claims description 3
- 229910052742 iron Inorganic materials 0.000 claims description 3
- 238000009434 installation Methods 0.000 abstract description 5
- 238000005516 engineering process Methods 0.000 abstract description 3
- 230000007423 decrease Effects 0.000 abstract description 2
- 238000002474 experimental method Methods 0.000 description 6
- 230000035882 stress Effects 0.000 description 5
- 238000013459 approach Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 230000033228 biological regulation Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
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- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention belongs to aero-engine test technology, relate to the improvement to the heating arrangement for aero-engine spindle thermal state strength test.It is characterized in that: have a heating unit be made up of 2 to 4 tube electric heater assemblies and end cap (11); Tube electric heater assembly is made up of electric heating tube (8), setscrew nut (9) and set nut (10).This invention ensures that the temperature by testing main shaft meets testing requirements, and decrease the space occupied by heating arrangement, for the installation of other testing equipments provides condition.
Description
Technical field
The invention belongs to aero-engine test technology, relate to the improvement to the heating arrangement for aero-engine spindle thermal state strength test.
Background technology
Aero gas turbine engine main shaft connects pneumatic plant and turbine part and the vitals of transmitted power, once there is fracture defect, can cause extremely serious consequence.Therefore require that main shaft has very high reliability and extremely low destructive rate.
During engine operation, main shaft subjects the loads such as larger moment of torsion, moment of flexure, axial force, gyroscopic couple, centrifugal force and vibration, also receives thermal load etc. at the main shaft of engine high-temperature district work, and these are larger on engine spindle impact fatigue lifetime.Only by stress analysis and material test, the fatigue lifetime of main shaft can't be estimated exactly.Main shaft test is by exerciser by the load applying that the requires examination position to main shaft, and operating load and the state of temperature at position examined by simulation test main shaft truly, ensures that main shaft has boundary condition and the Temperature Distribution of state of flight on engine.By carrying out static strength examination or fatigue life test checking to main shaft under hot environment, determining its static strength or fatigue lifetime, providing structural strength conclusion or predetermined safe cycle life.
Due to the needs on engine structure, main shaft is often designed to different geometric configuratioies, be processed with the geometric configuratioies such as step, hole, groove, spline, end-tooth, middle hollow thereon, these positions are all the positions that principal stress is concentrated, also be the key position of main shaft, usual local stress is very high, and the life-span of main shaft is all generally determined by the dangerouse cross-section that these local stresses are very high.In addition, the impact of temperature on testpieces fatigue lifetime has two aspects, and one is cause material mechanical performance to decline, and causes testpieces to reduce fatigue lifetime; Two be uneven Temperature Distribution produce in testpieces thermal stress together with mechanical stress with engine use circulation and change, cause the fatigure failure of testpieces.
When carrying out engine spindle hot test on " main shaft exerciser " in the past, be install some groups " the belt electric heaters that joint connects " vertically at testpieces outside surface to heat, a kind of heating arrangement structure for aero-engine spindle thermal state strength test is see Fig. 1.Tubular shafts by test aeromotor main shaft 2, the left flange of its left end is by the right-hand member Flange joint of bolt and front group section 1, the left end flange of front group section 1 is fixedly connected with to hold is connected by bolt and strength testing facility, and the left end flange of front group section 1 is with center pit; By the left end Flange joint of the right-hand member flange of test aeromotor main shaft 2 by bolt and rear group section 4 left end, the right-hand member flange of rear group section 4 is connected with the loading end of strength testing facility by bolt, and the belt electric heater 3 that said heating arrangement is connected by the many groups joint be enclosed in outside main shaft 2 and 6 temperature sensors 5 form.3 temperature sensors 5 are respectively laid, for measuring the temperature of shaft experiment part inner chamber and outside surface respectively at the inner chamber of shaft experiment part 2 and outside surface.
Its principle of work is: during test, the belt electric heater 3 electrified regulation main shaft 2 that many group joints connect, the temperature of temperature sensor measurement main shaft 2 inner chamber and outside surface.Its shortcoming is: the first, the temperature of main shaft 2 does not meet testing requirements.Temperature approach≤20 DEG C of testing requirements main shaft 2 surfaces externally and internally, the belt electric heater 3 connected due to above-mentioned joint is positioned at the outside of main shaft 2, and the thermal loss of convection heat transfer' heat-transfer by convection is large, and cause the temperature approach of main shaft 2 surfaces externally and internally to be greater than 20 DEG C, maximum temperature difference value is more than 35 DEG C.The second, the belt electric heater 3 that above-mentioned joint connects is positioned at the outside of main shaft 2, occupies large quantity space, the installation of other testing equipments is affected.
Summary of the invention
The object of the invention is: the heating arrangement for aero-engine spindle thermal state strength test proposing a kind of improvement, to ensure to be met testing requirements by the temperature of test main shaft, and the space of reducing occupied by heating arrangement, for the installation of other testing equipments provides condition.
Technical scheme of the present invention is: for the heating arrangement of aero-engine spindle thermal state strength test, tubular shafts by test aeromotor main shaft 2, the left flange of its left end is by the right-hand member Flange joint of bolt and front group section 1, the left end flange of front group section 1 is fixedly connected with to hold is connected by bolt and strength testing facility, and the left end flange of front group section 1 is with center pit, by the left end Flange joint of the right-hand member flange of test aeromotor main shaft 2 by bolt and rear group section 4 left end, the right-hand member flange of rear group section 4 is connected with the loading end of strength testing facility by bolt, said heating arrangement comprises 6 temperature sensors 5,3 are respectively laid, for measuring the temperature of shaft experiment part inner chamber and outside surface respectively at the inner chamber of shaft experiment part 2 and outside surface, it is characterized in that: the heating unit be made up of 2 to 4 tube electric heater assemblies and end cap 11 by, end cap 11 is plectanes, end cap 11 is sealed on the left port place of front group section 1 center pit, be fixed by screws on the left side of front group section 1, end cap 11 has the heating tube mounting hole be uniformly distributed along the circumference, the quantity of heating tube mounting hole is identical with the quantity of tube electric heater assembly, has 3 temperature sensor fixing hole be uniformly distributed along the circumference in the outside of mounting hole, tube electric heater assembly is by electric heating tube 8, setscrew nut 9 and set nut 10 form, at the left end of electric heating tube 8 with external thread, setscrew nut 9 and set nut 10 are screwed on above-mentioned external thread, the left end of electric heating tube 8 is through in heating tube mounting hole, setscrew nut 9 is positioned at the right of end cap 11, set nut 10 is positioned at the left side of end cap 11, by setscrew nut 9 and set nut 10, the left end of electric heating tube 8 is fixed on end cap 11, the right-hand member of electric heating tube 8 puts in the inner cavity of right section of main shaft 2, the lead-in wire of electric heating tube 8 is drawn from the heating tube fairlead being fixedly connected with end of strength testing facility, 3 temperature sensors 5 of inner chamber are inserted in the inner chamber of main shaft 2 from the sensor mounting hole of 3 end cap 11 respectively, gap between temperature sensor 5 and sensor mounting hole asbestos cloth jam-pack, temperature sensor 5 lead-in wire from strength testing facility be fixedly connected with end sensor lead hole draw, the interior cavity temperature of left section of the first temperature sensor measurement main shaft 2 wherein, the interior cavity temperature in the second temperature sensor measurement main shaft 2 stage casing, three-temperature sensor measures the interior cavity temperature of right section of main shaft 2, 3 temperature sensors 5 of outside surface, between shaft experiment part outside surface and asbestos heat-insulation layer 12, bind with iron wire.
Advantage of the present invention is: the heating arrangement for aero-engine spindle thermal state strength test proposing a kind of improvement, ensure that the temperature by testing main shaft meets testing requirements, and the space decreased occupied by heating arrangement, for the installation of other testing equipments provides condition.
Accompanying drawing explanation
Fig. 1 is a kind of structural representation of the heating arrangement for aero-engine spindle thermal state strength test.
Fig. 2 is structural representation of the present invention.
Embodiment
Below the present invention is described in further details.See Fig. 2, for the heating arrangement of aero-engine spindle thermal state strength test, tubular shafts by test aeromotor main shaft 2, the left flange of its left end is by the right-hand member Flange joint of bolt and front group section 1, the left end flange of front group section 1 is fixedly connected with to hold is connected by bolt and strength testing facility, and the left end flange of front group section 1 is with center pit, by the left end Flange joint of the right-hand member flange of test aeromotor main shaft 2 by bolt and rear group section 4 left end, the right-hand member flange of rear group section 4 is connected with the loading end of strength testing facility by bolt, and said heating arrangement comprises 6 temperature sensors 5, it is characterized in that: the heating unit be made up of 2 to 4 tube electric heater assemblies and end cap 11 by, end cap 11 is plectanes, end cap 11 is sealed on the left port place of front group section 1 center pit, be fixed by screws on the left side of front group section 1, end cap 11 has the heating tube mounting hole be uniformly distributed along the circumference, the quantity of heating tube mounting hole is identical with the quantity of tube electric heater assembly, has 3 temperature sensor fixing hole be uniformly distributed along the circumference in the outside of mounting hole, tube electric heater assembly is by electric heating tube 8, setscrew nut 9 and set nut 10 form, at the left end of electric heating tube 8 with external thread, setscrew nut 9 and set nut 10 are screwed on above-mentioned external thread, the left end of electric heating tube 8 is through in heating tube mounting hole, setscrew nut 9 is positioned at the right of end cap 11, set nut 10 is positioned at the left side of end cap 11, by setscrew nut 9 and set nut 10, the left end of electric heating tube 8 is fixed on end cap 11, the right-hand member of electric heating tube 8 puts in the inner cavity of right section of main shaft 2, the lead-in wire of electric heating tube 8 is drawn from the heating tube fairlead being fixedly connected with end of strength testing facility, 3 temperature sensors 5 are inserted in the inner chamber of main shaft 2 from the sensor mounting hole of 3 end cap 11 respectively, gap between temperature sensor 5 and sensor mounting hole asbestos cloth jam-pack, temperature sensor 5 lead-in wire from strength testing facility be fixedly connected with end sensor lead hole draw, the interior cavity temperature of left section of the first temperature sensor measurement main shaft 2 wherein, the interior cavity temperature in the second temperature sensor measurement main shaft 2 stage casing, three-temperature sensor measures the interior cavity temperature of right section of main shaft 2, 3 temperature sensors 5 of outside surface, between shaft experiment part outside surface and asbestos heat-insulation layer 12, bind with iron wire.
Principle of work of the present invention is: because electric heating tube 8 is arranged in the inner chamber of main shaft 2, substantially reduce the temperature loss that thermal convection causes, and ensure that the temperature difference Pass Test requirement of main shaft 2 surfaces externally and internally.Test proves, after adopting the present invention, the temperature difference of main shaft 2 surfaces externally and internally can reach within 15 DEG C.In addition, the present invention does not occupy the space outerpace of main shaft 2 completely, facilitates the installation of other testing equipments.
One embodiment of the present of invention, the electric heating tube adopted is finished parts.
Claims (1)
1. for the heating arrangement of aero-engine spindle thermal state strength test, by test aeromotor main shaft (2) be tubular shaft, the left flange of its left end is by the right-hand member Flange joint of bolt and front group section (1), the left end flange of front group section (1) is fixedly connected with to hold is connected by bolt and strength testing facility, and the left end flange of front group section (1) is with center pit, by the left end Flange joint of the right-hand member flange of test aeromotor main shaft (2) by bolt and rear group section (4) left end, the right-hand member flange of rear group section (4) is connected with the loading end of strength testing facility by bolt, said heating arrangement comprises 6 temperature sensors (5), 3 are respectively laid, for measuring the temperature of main shaft (2) inner chamber and outside surface respectively at the inner chamber of main shaft (2) and outside surface, it is characterized in that: have a heating unit be made up of 2 to 4 tube electric heater assemblies and end cap (11), end cap (11) is a plectane, end cap (11) is sealed on the left port place of front group section (1) center pit, be fixed by screws on the left side of front group section (1), end cap (11) has the heating tube mounting hole be uniformly distributed along the circumference, the quantity of heating tube mounting hole is identical with the quantity of tube electric heater assembly, has 3 temperature sensor fixing hole be uniformly distributed along the circumference in the outside of mounting hole, tube electric heater assembly is by electric heating tube (8), setscrew nut (9) and set nut (10) composition, at the left end of electric heating tube (8) with external thread, setscrew nut (9) and set nut (10) are screwed on above-mentioned external thread, the left end of electric heating tube (8) is through in heating tube mounting hole, setscrew nut (9) is positioned at the right of end cap (11), set nut (10) is positioned at the left side of end cap (11), by setscrew nut (9) and set nut (10), the left end of electric heating tube (8) is fixed on end cap (11), the right-hand member of electric heating tube (8) puts in the inner cavity of right section of main shaft (2), the lead-in wire of electric heating tube (8) is drawn from the heating tube fairlead being fixedly connected with end of strength testing facility, 3 temperature sensors (5) of inner chamber are inserted in the inner chamber of main shaft (2) from 3 sensor mounting hole end cap (11) respectively, gap asbestos cloth jam-pack between temperature sensor (5) and sensor mounting hole, temperature sensor (5) lead-in wire from strength testing facility be fixedly connected with end sensor lead hole draw, the interior cavity temperature of left section of the first temperature sensor measurement main shaft (2) wherein, the interior cavity temperature in the second temperature sensor measurement main shaft (2) stage casing, three-temperature sensor measures the interior cavity temperature of right section of main shaft (2), 3 temperature sensors (5) of outside surface are positioned between main shaft (2) outside surface and asbestos heat-insulation layer (12), bind with iron wire.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310170199.8A CN103267636B (en) | 2013-05-10 | 2013-05-10 | For the heating arrangement of aero-engine spindle thermal state strength test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310170199.8A CN103267636B (en) | 2013-05-10 | 2013-05-10 | For the heating arrangement of aero-engine spindle thermal state strength test |
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| Publication Number | Publication Date |
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| CN103267636A CN103267636A (en) | 2013-08-28 |
| CN103267636B true CN103267636B (en) | 2015-10-28 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310170199.8A Active CN103267636B (en) | 2013-05-10 | 2013-05-10 | For the heating arrangement of aero-engine spindle thermal state strength test |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109798771A (en) * | 2019-01-31 | 2019-05-24 | 中国航发动力股份有限公司 | One kind testing heating device for aero-engine turbine disk low cycle fatigue life |
| CN109883610B (en) * | 2019-02-26 | 2021-02-05 | 中国航发沈阳发动机研究所 | Aeroengine axial force measuring heating calibration furnace |
| CN112051069B (en) * | 2019-06-05 | 2022-12-23 | 中国航发商用航空发动机有限责任公司 | Gas turbine test bench |
| CN111256988B (en) * | 2020-03-31 | 2021-07-06 | 中国航发动力股份有限公司 | Load loading device and method for strength test of low-pressure compressor shaft of engine |
| CN111638048B (en) * | 2020-05-28 | 2022-01-21 | 扬州大学 | Simulation device for rubbing fault caused by thermal bending of multistage bladed disk rotor |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4200784A (en) * | 1977-12-05 | 1980-04-29 | Westinghouse Electric Corp. | Hollow shaft bore heater assembly |
| CN202625256U (en) * | 2012-06-06 | 2012-12-26 | 贵阳铝镁设计研究院有限公司 | Electric heater for screw shaft |
-
2013
- 2013-05-10 CN CN201310170199.8A patent/CN103267636B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4200784A (en) * | 1977-12-05 | 1980-04-29 | Westinghouse Electric Corp. | Hollow shaft bore heater assembly |
| CN202625256U (en) * | 2012-06-06 | 2012-12-26 | 贵阳铝镁设计研究院有限公司 | Electric heater for screw shaft |
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| CN103267636A (en) | 2013-08-28 |
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Address after: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee after: AECC AVIATION POWER CO,LTD. Address before: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee before: AVIC AVIATION ENGINE Corp.,PLC Address after: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee after: AVIC AVIATION ENGINE Corp.,PLC Address before: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee before: XI'AN AVIATION POWER Co.,Ltd. |