CN103267636A - Heating device for aero-engine spindle thermal state strength test - Google Patents
Heating device for aero-engine spindle thermal state strength test Download PDFInfo
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- CN103267636A CN103267636A CN2013101701998A CN201310170199A CN103267636A CN 103267636 A CN103267636 A CN 103267636A CN 2013101701998 A CN2013101701998 A CN 2013101701998A CN 201310170199 A CN201310170199 A CN 201310170199A CN 103267636 A CN103267636 A CN 103267636A
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Abstract
The invention belongs to the aero-engine test technology, and relates to improvement of a heating device for an aero-engine spindle thermal state strength test. The heating device for the aero-engine spindle thermal state strength test is characterized by comprising a heating unit, wherein the heating unit is composed of two to four tube-type electric heater assemblies and an end cover (11), and each tube-type electric heater assembly is composed of electric heating tubes (8), a locating nut (9) and a locking nut (10). The heating device for the aero-engine spindle thermal state strength test ensures the fact that the temperature of a spindle to be tested meets the requirements of the test, reduces occupied space, and provides conditions for installation of other test devices.
Description
Technical field
The invention belongs to the aeromotor experimental technique, relate to the improvement to the heating arrangement that is used for the test of aeromotor main shaft hot strength.
Background technology
The aero gas turbine engine main shaft is the vitals that connects pneumatic plant and turbine part and transmitted power, in case fracture defect occurs, can cause extremely serious consequence.Therefore require main shaft to have very high reliability and extremely low destructive rate.
During engine operation, main shaft is bearing loads such as bigger moment of torsion, moment of flexure, axial force, gyroscopic couple, centrifugal force and vibration, and the main shaft of working in the engine high-temperature district also receives thermal load etc., and these are bigger to engine spindle influence fatigue lifetime.Only depend on stress analysis and material test, can't estimate the fatigue lifetime of main shaft exactly.Main shaft test is by exerciser the load that requires to be applied to the examination position of main shaft, and operating load and the state of temperature at simulation test main shaft examination position guarantee that main shaft has boundary condition and the Temperature Distribution of state of flight on the engine truly.By under the hot environment main shaft being carried out static strength examination or fatigue life test checking, determine its static strength or fatigue lifetime, provide structural strength conclusion or predetermined safe cycle life.
Because the needs on the engine structure, main shaft often is designed to different geometric configuratioies, be processed with geometric configuratioies such as step, hole, groove, spline, end face tooth, middle hollow thereon, these positions all are the positions that main shaft stress is concentrated, it also is the key position of main shaft, usually local stress is very high, and the life-span of main shaft generally all is to be determined by the very high dangerouse cross-section of these local stresses.In addition, temperature has two aspects to the testpieces Fatigue Life, and the one, cause that material mechanical performance descends, and causes testpieces to reduce fatigue lifetime; The 2nd, inhomogeneous Temperature Distribution produces thermal stress and changes with the use circulation of mechanical stress with engine in testpieces, cause the fatigure failure of testpieces.
In the past at " main shaft exerciser " when carrying out the engine spindle hot test, be at the testpieces outside surface some groups " joints connect belt electric heaters " to be installed vertically to heat, a kind of heating arrangement structure for the test of aeromotor main shaft hot strength is referring to Fig. 1.Quilt test aeromotor main shaft 2 is tubular shafts, the left flange of its left end is connected with the right-hand member flange of preceding group section 1 by bolt, the left end flange of preceding group section 1 is connected with the fixedly connected end of strength testing facility by bolt, and the left end flange of preceding group section 1 has center pit; Be connected by the left end flange of bolt with back group section 4 left ends by the right-hand member flange of test aeromotor main shaft 2, the right-hand member flange of back group section 4 is connected with the loading end of strength testing facility by bolt, and said heating arrangement is made up of belt electric heater 3 and 6 temperature sensors 5 that the many groups joint that is enclosed in main shaft 2 outsides connects.Inner chamber and outside surface at shaft experiment spare 2 respectively lays 3 temperature sensors 5 respectively, is used for measuring the temperature of shaft experiment spare inner chamber and outside surface.
Its principle of work is: during test, organize the belt electric heater 3 energising heating main shafts 2 that the joint connects, the temperature of temperature sensor measurement main shaft 2 inner chambers and outside surface more.Its shortcoming is: the first, the temperature of main shaft 2 does not satisfy testing requirements.Temperature approach≤20 of testing requirements main shaft 2 surfaces externally and internallies ℃, because the belt electric heater 3 that above-mentioned joint connects is positioned at the outside of main shaft 2, the thermal loss of convection heat transfer' heat-transfer by convection is big, causes the temperature approach of main shaft 2 surfaces externally and internallies greater than 20 ℃, the maximum temperature difference value is above 35 ℃.The second, the belt electric heater 3 that connects of above-mentioned joint is positioned at the outside of main shaft 2, has taken big quantity space, and the installation of other testing equipments is affected.
Summary of the invention
The objective of the invention is: propose a kind of improved heating arrangement for the test of aeromotor main shaft hot strength, to guarantee being satisfied testing requirements by the temperature of test main shaft, and reduce the occupied space of heating arrangement, for the installation of other testing equipments provides condition.
Technical scheme of the present invention is: the heating arrangement that is used for the test of aeromotor main shaft hot strength, quilt test aeromotor main shaft 2 is tubular shafts, the left flange of its left end is connected with the right-hand member flange of preceding group section 1 by bolt, the left end flange of preceding group section 1 is connected with the fixedly connected end of strength testing facility by bolt, and the left end flange of preceding group section 1 has center pit; Be connected by the left end flange of bolt with back group section 4 left ends by the right-hand member flange of test aeromotor main shaft 2, the right-hand member flange of back group section 4 is connected with the loading end of strength testing facility by bolt, said heating arrangement comprises 6 temperature sensors 5, inner chamber and outside surface at shaft experiment spare 2 respectively lays 3 respectively, is used for measuring the temperature of shaft experiment spare inner chamber and outside surface; It is characterized in that: by a heating unit of being formed by 2 to 4 tube electric heater assemblies and end cap 11; End cap 11 is plectanes, the left port place of group section 1 center pit before end cap 11 is sealed on, be fixed on by screw on the left side of preceding group section 1, the heating tube mounting hole that is uniformly distributed along the circumference is arranged at end cap 11, the quantity of heating tube mounting hole is identical with the quantity of tube electric heater assembly, and 3 temperature sensor mounting holes that are uniformly distributed along the circumference are arranged in the outside of mounting hole; The tube electric heater assembly is by electric heating tube 8, setscrew nut 9 and set nut 10 are formed, left end at electric heating tube 8 has external thread, setscrew nut 9 and set nut 10 are screwed on the above-mentioned external thread, the left end of electric heating tube 8 is through in the 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, be fixed on the end cap 11 by setscrew nut 9 and set nut 10 left end with electric heating tube 8, the right-hand member of electric heating tube 8 puts in the inner cavity of right section of main shaft 2, and the lead-in wire of electric heating tube 8 is drawn from the heating tube fairlead of the fixedly connected end of strength testing facility; 3 temperature sensors 5 of inner chamber, 3 sensor mounting holes from end cap 11 respectively are inserted into the inner chamber of main shaft 2, gap asbestos cloth jam-pack between temperature sensor 5 and the sensor mounting hole, temperature sensor 5 lead-in wire draw from the sensor lead hole of the fixedly connected end of strength testing facility, the interior cavity temperature of the first temperature sensor measurement main shaft, 2 left side sections wherein, the interior cavity temperature in the second temperature sensor measurement main shaft, 2 stage casings, three-temperature sensor is measured the interior cavity temperature of main shaft 2 right sections; 3 temperature sensors 5 of outside surface bind with iron wire between shaft experiment spare outside surface and asbestos heat-insulation layer 12.
Advantage of the present invention is: proposed a kind of improved heating arrangement for the test of aeromotor main shaft hot strength, guaranteed to be satisfied testing requirements by the temperature of test main shaft, and reduced the occupied space of heating arrangement, for the installation of other testing equipments provides condition.
Description of drawings
Fig. 1 is a kind of structural representation of the heating arrangement for aeromotor main shaft hot strength test.
Fig. 2 is structural representation of the present invention.
Embodiment
Below the present invention is described in further details.Referring to Fig. 2, the heating arrangement that is used for the test of aeromotor main shaft hot strength, quilt test aeromotor main shaft 2 is tubular shafts, the left flange of its left end is connected with the right-hand member flange of preceding group section 1 by bolt, the left end flange of preceding group section 1 is connected with the fixedly connected end of strength testing facility by bolt, and the left end flange of preceding group section 1 has center pit; Be connected by the left end flange of bolt with back group section 4 left ends by the right-hand member flange of test aeromotor main shaft 2, the right-hand member flange of back 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: by a heating unit of being formed by 2 to 4 tube electric heater assemblies and end cap 11; End cap 11 is plectanes, the left port place of group section 1 center pit before end cap 11 is sealed on, be fixed on by screw on the left side of preceding group section 1, the heating tube mounting hole that is uniformly distributed along the circumference is arranged at end cap 11, the quantity of heating tube mounting hole is identical with the quantity of tube electric heater assembly, and 3 temperature sensor mounting holes that are uniformly distributed along the circumference are arranged in the outside of mounting hole; The tube electric heater assembly is by electric heating tube 8, setscrew nut 9 and set nut 10 are formed, left end at electric heating tube 8 has external thread, setscrew nut 9 and set nut 10 are screwed on the above-mentioned external thread, the left end of electric heating tube 8 is through in the 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, be fixed on the end cap 11 by setscrew nut 9 and set nut 10 left end with electric heating tube 8, the right-hand member of electric heating tube 8 puts in the inner cavity of right section of main shaft 2, and the lead-in wire of electric heating tube 8 is drawn from the heating tube fairlead of the fixedly connected end of strength testing facility; 3 temperature sensors 5,3 sensor mounting holes from end cap 11 respectively are inserted into the inner chamber of main shaft 2, gap asbestos cloth jam-pack between temperature sensor 5 and the sensor mounting hole, temperature sensor 5 lead-in wire draw from the sensor lead hole of the fixedly connected end of strength testing facility, the interior cavity temperature of the first temperature sensor measurement main shaft, 2 left side sections wherein, the interior cavity temperature in the second temperature sensor measurement main shaft, 2 stage casings, three-temperature sensor is measured the interior cavity temperature of main shaft 2 right sections; 3 temperature sensors 5 of outside surface bind with iron wire between shaft experiment spare outside surface and asbestos heat-insulation layer 12.
Principle of work of the present invention is: because electric heating tube 8 is installed in the inner chamber of main shaft 2, reduced the temperature loss that thermal convection causes greatly, guaranteed the temperature difference Pass Test requirement of main shaft 2 surfaces externally and internallies.Evidence, behind employing the present invention, the temperature difference of main shaft 2 surfaces externally and internallies can reach in 15 ℃.In addition, the present invention does not occupy the space outerpace of main shaft 2 fully, has made things convenient for the installation of other testing equipments.
One embodiment of the present of invention, the electric heating tube that adopts is finished parts.
Claims (1)
1. the heating arrangement that is used for the test of aeromotor main shaft hot strength, quilt test aeromotor main shaft (2) is tubular shaft, the left flange of its left end is connected by the right-hand member flange of bolt with preceding group section (1), the left end flange of preceding group section (1) is connected with the fixedly connected end of strength testing facility by bolt, and the left end flange of preceding group section (1) has center pit; Be connected by the left end flange of bolt with back group section (4) left end by the right-hand member flange of test aeromotor main shaft (2), the right-hand member flange of back group section (4) is connected with the loading end of strength testing facility by bolt, said heating arrangement comprises 6 temperature sensors (5), inner chamber and outside surface at shaft experiment spare 2 respectively lays 3 respectively, is used for measuring the temperature of shaft experiment spare inner chamber and outside surface; It is characterized in that: a heating unit of being made up of 2 to 4 tube electric heater assemblies and end cap (11) is arranged; End cap (11) is a plectane, end cap (11) is sealed on the left port place of preceding group section (1) center pit, be fixed on by screw on the left side of preceding group section (1), the heating tube mounting hole that is uniformly distributed along the circumference is arranged at end cap (11), the quantity of heating tube mounting hole is identical with the quantity of tube electric heater assembly, and 3 temperature sensor mounting holes that are uniformly distributed along the circumference are arranged in the outside of mounting hole; The tube electric heater assembly is by electric heating tube (8), setscrew nut (9) and set nut (10) are formed, left end at electric heating tube (8) has external thread, setscrew nut (9) and set nut (10) are screwed on the above-mentioned external thread, the left end of electric heating tube (8) is through in the 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), be fixed on the end cap (11) by setscrew nut (9) and set nut (10) left end with electric heating tube (8), the right-hand member of electric heating tube (8) puts in the inner cavity of right section of main shaft (2), and the lead-in wire of electric heating tube (8) is drawn from the heating tube fairlead of the fixedly connected end of strength testing facility; 3 temperature sensors (5) of inner chamber, 3 sensor mounting holes from end cap (11) respectively are inserted into the inner chamber of main shaft (2), gap asbestos cloth jam-pack between temperature sensor (5) and the sensor mounting hole, temperature sensor (5) lead-in wire draw from the sensor lead hole of the fixedly connected end of strength testing facility, the interior cavity temperature of the first temperature sensor measurement main shaft (2) left side section wherein, the interior cavity temperature in second temperature sensor measurement main shaft (2) stage casing, three-temperature sensor is measured the interior cavity temperature of the right section of main shaft (2); 3 temperature sensors (5) of outside surface are positioned between shaft experiment spare outside surface and the 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 |
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| 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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| CN103267636A true CN103267636A (en) | 2013-08-28 |
| CN103267636B 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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Cited By (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 |
| CN109883610A (en) * | 2019-02-26 | 2019-06-14 | 中国航发沈阳发动机研究所 | Aero-engine axial direction power measurement heating calibration furnace |
| CN111256988A (en) * | 2020-03-31 | 2020-06-09 | 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 |
| CN111638048A (en) * | 2020-05-28 | 2020-09-08 | 扬州大学 | Simulation device for rubbing fault caused by thermal bending of multistage bladed disk rotor |
| CN112051069A (en) * | 2019-06-05 | 2020-12-08 | 中国航发商用航空发动机有限责任公司 | Gas turbine test bench and thermal stress resistant flange device thereof |
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 |
Cited By (7)
| 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 |
| CN109883610A (en) * | 2019-02-26 | 2019-06-14 | 中国航发沈阳发动机研究所 | Aero-engine axial direction power measurement heating calibration furnace |
| CN112051069A (en) * | 2019-06-05 | 2020-12-08 | 中国航发商用航空发动机有限责任公司 | Gas turbine test bench and thermal stress resistant flange device thereof |
| CN111256988A (en) * | 2020-03-31 | 2020-06-09 | 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 |
| 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 |
| CN111638048A (en) * | 2020-05-28 | 2020-09-08 | 扬州大学 | Simulation device for rubbing fault caused by thermal bending of multistage bladed disk rotor |
| 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 |
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| Publication number | Publication date |
|---|---|
| CN103267636B (en) | 2015-10-28 |
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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. |
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