CN101915622B - Rotatory test temperature measuring equipment of aircraft engine rotor part - Google Patents
Rotatory test temperature measuring equipment of aircraft engine rotor part Download PDFInfo
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- CN101915622B CN101915622B CN201010262267.XA CN201010262267A CN101915622B CN 101915622 B CN101915622 B CN 101915622B CN 201010262267 A CN201010262267 A CN 201010262267A CN 101915622 B CN101915622 B CN 101915622B
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Abstract
The invention belongs to an aircraft engine testing technology and relates to an improvement of rotatory test temperature measuring equipment of an aircraft engine rotor part. The temperature measuring equipment comprises a baseplate (1), a lever bracket (8) and a thermocouple assembly, and is characterized by being provided with a single-arm lever mechanism formed by an electromagnet driving mechanism, a connecting bar hinge shaft (6), a lever (7), a thermocouple assembly mounting plate (11) and a connecting screw (12), wherein the electromagnet driving mechanism comprises an electromagnet mounting base (2), an electromagnet (4) and a connecting bar (5). The temperature measuring equipment has high driving reliability, and can meet the need for measuring the temperature of a rotor assembly with larger axial dimension. The installation position of the temperature measuring equipment can be adjusted freely according to the testing needs.
Description
Technical field
The invention belongs to the aeromotor measuring technology, relate to improvement rotatory test temperature measuring equipment of aircraft engine rotor part.
Background technology
Aircraft engine rotor part is when for example single-deck part or rotor assembly carry out hot rotation test, because tested parts are at high speed rotating, temperature survey is the technological difficulties of test.At present, a kind of structure of thermocouple temperature measuring apparatus is referring to Fig. 1, and it is made up of base plate 1, lever dolly 8, thermocouple assembly, cylinder driving mechanism 16 and the both arms scissors leverage that is installed on the lever dolly 8.The piston of cylinder driving mechanism 16 is connected by web member 18 with the left end of both arms scissors leverage, the right-hand member of both arms scissors leverage is connected with a thermocouple assembly 20 respectively, when the piston of cylinder driving mechanism 16 stretches out to the right, the left end of both arms scissors leverage opens under the effect of back-moving spring 19, the right-hand member of both arms scissors leverage is also followed open; When the piston of cylinder driving mechanism 16 reclaimed left, the left end of both arms scissors leverage was closed under the effect of pulling force, makes the right-hand member of both arms scissors leverage also follow closure.Measured tested parts are between two arms of both arms scissors leverage right-hand member.The shortcoming of this temperature measuring equipment is: the first, cylinder drives poor reliability.Because temperature measuring equipment is arranged in vacuum environment, the cylinder driving mechanism is easy to produce trouble or failure because of revealing.The second, the open distance of both arms scissors leverage is limited, can not satisfy the needs of the bigger rotor assembly thermometric of axial dimension.Three, its position must be fixed, and is difficult to adjust the installation site as required neatly, and limitation is arranged during thermometric.
Summary of the invention
The objective of the invention is: propose a kind of needs that drive the reliability height, can satisfy the bigger rotor assembly thermometric of axial dimension, be convenient to adjust the rotatory test temperature measuring equipment of aircraft engine rotor part of installation site.
Technical scheme of the present invention is: rotatory test temperature measuring equipment of aircraft engine rotor part, comprise base plate, lever dolly and thermocouple assembly, the base of lever dolly is fixed on the base plate by the lever dolly gib screw, the lever dolly axis hole that level is arranged on lever dolly, in this lever dolly axis hole, lever shaft is arranged, thermocouple assembly is made up of thermopair holder, holding screw and thermopair, thermopair is through in the thermopair mounting hole of thermopair holder, by holding screw thermopair is locked; It is characterized in that, by a single-arm lever mechanism that forms by solenoid actuated mechanism, connecting rod link axle, lever, thermocouple assembly installing plate and attachment screw; The lever axis hole that level is arranged at the middle part of lever, this lever shaft borehole jack make lever and lever dolly form hinge and are connected on lever shaft; Solenoid actuated mechanism is by the electromagnet mount pad, electromagnet and connecting rod are formed, the electromagnet mount pad is fixed on the base plate by the mount pad gib screw, be positioned at the left side of lever dolly, electromagnet is fixed on the electromagnet mount pad, the lower end of connecting rod is connected with the upper end of the moving iron core of electromagnet, the waist shape left side hinge shaft hole that level is arranged at the left end of lever, there is the connecting rod axis hole of level the upper end of connecting rod, the connecting rod link axle is through in above-mentioned connecting rod axis hole and the left hinge shaft hole, the upper end of connecting rod is connected with the left end formation hinge of lever, right-hand member at lever has vertical through hole, there is mounting hole on the plate face left side of thermocouple assembly installing plate, attachment screw is through in the through hole of the mounting hole of above-mentioned thermocouple assembly installing plate and lever, the right-hand member of thermocouple assembly installing plate and lever is connected to integral body, the thermopair holder, has to allow the hole of passing that thermopair passes on the plate face of thermocouple assembly installing plate by screw retention on the plate face of thermocouple assembly installing plate; The centre distance of left hinge shaft hole and lever dolly axis hole is less than the distance of lever dolly axis hole to lever right-hand member through hole on the lever.
Advantage of the present invention is: drive the reliability height, can satisfy the needs of the bigger rotor assembly thermometric of axial dimension, the installation site of temperature measuring equipment is convenient to adjust, and can adjust the installation site neatly according to the test needs.
Description of drawings
Fig. 1 is a kind of structural representation of existing thermocouple temperature measuring apparatus.
Fig. 2 is a structural representation of the present invention.
Embodiment
Below the present invention is described in further details.Referring to Fig. 2, rotatory test temperature measuring equipment of aircraft engine rotor part, comprise base plate 1, lever dolly 8 and thermocouple assembly, the base of lever dolly 8 is fixed on the base plate 1 by lever dolly gib screw 10, the lever dolly axis hole that level is arranged on lever dolly 8 has lever shaft 9 in this lever dolly axis hole.
Thermocouple assembly is made up of thermopair holder 13, holding screw 14 and thermopair 15, and thermopair 15 is through in the thermopair mounting hole of thermopair holder 13, by holding screw 14 thermopair 15 is locked.
It is characterized in that, by a single-arm lever mechanism that forms by solenoid actuated mechanism, connecting rod link axle 6, lever 7, thermocouple assembly installing plate 11 and attachment screw 12.The lever axis hole that level is arranged at the middle part of lever 7, this lever shaft borehole jack make lever 7 form hinge with lever dolly 8 and are connected on lever shaft 9.On lever 7, have a plurality of lever axis holes, with the convenient proportionate relationship of adjusting lever.
Solenoid actuated mechanism is made up of electromagnet mount pad 2, electromagnet 4 and connecting rod 5, electromagnet mount pad 2 is fixed on the base plate 1 by mount pad gib screw 3, be positioned at the left side of lever dolly 8, electromagnet 4 is fixed on the electromagnet mount pad 2, and the lower end of connecting rod 5 is connected with the upper end of electromagnet 4 moving iron cores.Employing solenoid actuated mechanism has improved the driving reliability in vacuum environment greatly.When the moving iron core of electromagnet 4 protruded upward, the right-hand member of lever 7 descended; When the moving iron core of electromagnet 4 was regained downwards, the right-hand member of lever 7 rose.
At the left end of lever 7 the waist shape left side hinge shaft hole of level is arranged, there is the connecting rod axis hole of level the upper end of connecting rod 5, and connecting rod link axle 6 is through in above-mentioned connecting rod axis hole and the left hinge shaft hole, and the upper end of connecting rod 5 is connected with the left end formation hinge of lever 7.
Right-hand member at lever 7 has vertical through hole, there is mounting hole on the plate face left side of thermocouple assembly installing plate 11, attachment screw 12 is through in the through hole of the mounting hole of above-mentioned thermocouple assembly installing plate 11 and lever 7, the right-hand member of thermocouple assembly installing plate 11 and lever 7 is connected to integral body, thermopair holder 13, has to allow the hole of passing that thermopair 15 passes on the plate face of thermocouple assembly installing plate 11 by screw retention on the plate face of thermocouple assembly installing plate 11.
The centre distance of left hinge shaft hole and lever dolly axis hole is less than the distance of lever dolly axis hole to lever 7 right-hand member through holes on the lever 7.
Principle of work of the present invention is: adopt the double-arm lever temperature measuring mechanism of the single-arm lever temperature measuring mechanism replacement cylinder driving of solenoid actuated, the measurement reliability is improved greatly; The solenoid actuated mechanism size is little, is convenient to install, and can be installed in the position that the dut temperature field need be measured, and has satisfied the thermometric needs of Complex Temperature Field.Simultaneously, because the motion amplitude of single-arm lever is unrestricted, the needs of the bigger engine rotor part thermometric of axial dimension have been satisfied.
In one embodiment of the present of invention, electromagnet 4 adopts finished parts.
Claims (1)
1. rotatory test temperature measuring equipment of aircraft engine rotor part, comprise base plate [1], lever dolly [8] and thermocouple assembly, the base of lever dolly [8] is fixed on the base plate [1] by lever dolly gib screw [10], the lever dolly axis hole that level is arranged on lever dolly [8], lever shaft [9] is arranged in this lever dolly axis hole, thermocouple assembly is made up of thermopair holder [13], holding screw [14] and thermopair [15], thermopair [15] is through in the thermopair mounting hole of thermopair holder [13], by holding screw [14] thermopair [15] is locked; It is characterized in that a single-arm lever mechanism that is made up of solenoid actuated mechanism, connecting rod link axle [6], lever [7], thermocouple assembly installing plate [11] and attachment screw [12] is arranged; The lever axis hole that level is arranged at the middle part of lever [7], this lever shaft borehole jack make lever [7] and lever dolly [8] form hinge and are connected on lever shaft [9]; Solenoid actuated mechanism is by electromagnet mount pad [2], electromagnet [4] and connecting rod [5] are formed, electromagnet mount pad [2] is fixed on the base plate [1] by mount pad gib screw [3], be positioned at the left side of lever dolly [8], electromagnet [4] is fixed on the electromagnet mount pad [2], the lower end of connecting rod [5] is connected with the upper end of the moving iron core of electromagnet [4], the waist shape left side hinge shaft hole that level is arranged at the left end of lever [7], there is the connecting rod axis hole of level the upper end of connecting rod [5], connecting rod link axle [6] is through in above-mentioned connecting rod axis hole and the left hinge shaft hole, the upper end of connecting rod [5] is connected with the left end formation hinge of lever [7], right-hand member at lever [7] has vertical through hole, there is mounting hole on the plate face left side of thermocouple assembly installing plate [11], attachment screw [12] is through in the through hole of the mounting hole of above-mentioned thermocouple assembly installing plate [11] and lever [7], the right-hand member of thermocouple assembly installing plate [11] and lever [7] is connected to integral body, thermopair holder [13] on the plate face of thermocouple assembly installing plate [11], has the hole of passing that permission thermopair [15] passes by screw retention on the plate face of thermocouple assembly installing plate [11]; Lever [7] is gone up the centre distance of left hinge shaft hole and lever dolly axis hole less than the distance of lever dolly axis hole to lever [7] right-hand member through hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010262267.XA CN101915622B (en) | 2010-08-23 | 2010-08-23 | Rotatory test temperature measuring equipment of aircraft engine rotor part |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010262267.XA CN101915622B (en) | 2010-08-23 | 2010-08-23 | Rotatory test temperature measuring equipment of aircraft engine rotor part |
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| Publication Number | Publication Date |
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| CN101915622A CN101915622A (en) | 2010-12-15 |
| CN101915622B true CN101915622B (en) | 2011-11-09 |
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| CN201010262267.XA Active CN101915622B (en) | 2010-08-23 | 2010-08-23 | Rotatory test temperature measuring equipment of aircraft engine rotor part |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103592045A (en) * | 2012-08-17 | 2014-02-19 | 苏州市兴博塑胶模具有限公司 | Thermocouple support |
| CN105352617B (en) * | 2015-12-09 | 2017-10-24 | 山东大学 | Lead type thermocouple piston face temperature survey connecting rod pin configuration |
| CN114018423B (en) * | 2021-11-02 | 2022-09-06 | 上海交通大学 | Thermocouple three-dimensional temperature field measuring device and using method thereof |
| CN116046195B (en) * | 2023-04-03 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Movable type aeroengine wheel disk temperature measuring device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1067371A1 (en) * | 1980-05-06 | 1984-01-15 | Чкд Дукла Народни Подник,Завод-Филиал "Татра Колин"(Инопредприятие) | Device for protecting temperature pickup |
| CN2289236Y (en) * | 1997-02-19 | 1998-08-26 | 唐山钢铁集团有限责任公司 | Steel ladle quick sampling (measuring temp.) device |
| US6071009A (en) * | 1997-10-03 | 2000-06-06 | Micron Technology, Inc. | Semiconductor wirebond machine leadframe thermal map system |
| CN2927014Y (en) * | 2005-12-27 | 2007-07-25 | 宝山钢铁股份有限公司 | Lever-type steel-pipe internal-wall temperature sensing device |
| CN201331385Y (en) * | 2009-01-04 | 2009-10-21 | 武汉钢铁(集团)公司 | Automatic continuous temperature measuring equipment for continuous caster |
-
2010
- 2010-08-23 CN CN201010262267.XA patent/CN101915622B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1067371A1 (en) * | 1980-05-06 | 1984-01-15 | Чкд Дукла Народни Подник,Завод-Филиал "Татра Колин"(Инопредприятие) | Device for protecting temperature pickup |
| CN2289236Y (en) * | 1997-02-19 | 1998-08-26 | 唐山钢铁集团有限责任公司 | Steel ladle quick sampling (measuring temp.) device |
| US6071009A (en) * | 1997-10-03 | 2000-06-06 | Micron Technology, Inc. | Semiconductor wirebond machine leadframe thermal map system |
| CN2927014Y (en) * | 2005-12-27 | 2007-07-25 | 宝山钢铁股份有限公司 | Lever-type steel-pipe internal-wall temperature sensing device |
| CN201331385Y (en) * | 2009-01-04 | 2009-10-21 | 武汉钢铁(集团)公司 | Automatic continuous temperature measuring equipment for continuous caster |
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| CN101915622A (en) | 2010-12-15 |
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Address after: Weiyang Xu Jia Wan 710021 Shaanxi city of Xi'an Province Patentee after: AECC AVIATION POWER CO,LTD. Address before: Weiyang Xu Jia Wan 710021 Shaanxi city of Xi'an Province Patentee before: AVIC AVIATION ENGINE Corp.,PLC Address after: Weiyang Xu Jia Wan 710021 Shaanxi city of Xi'an Province Patentee after: AVIC AVIATION ENGINE Corp.,PLC Address before: Weiyang Xu Jia Wan 710021 Shaanxi city of Xi'an Province Patentee before: XI'AN AVIATION POWER Co.,Ltd. |
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