CN207529247U - A kind of sensor thermostat measured for aeroengine thrust - Google Patents
A kind of sensor thermostat measured for aeroengine thrust Download PDFInfo
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- CN207529247U CN207529247U CN201721396386.8U CN201721396386U CN207529247U CN 207529247 U CN207529247 U CN 207529247U CN 201721396386 U CN201721396386 U CN 201721396386U CN 207529247 U CN207529247 U CN 207529247U
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- power transmission
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Abstract
The utility model is related to a kind of sensor thermostat measured for aeroengine thrust, including metal connecting plate, heat-insulated connecting plate, connection bolt, thermal insulation housing, heat insulating washer, power transmission screw rod, power transmission collet, self temperature control heating tape and pressure head；For the equipment in the larger environment of outdoor testing equipment and temperature change, the measurement accuracy of sensor can be improved using thermostat, reduce sensor zero is floatd；For the test bay of benchmark test bay and thrust measure precision more than 0.25%, by the raising of measurement sensor service precision, make being improved for rack measurement accuracy；The device can be used for having used the transformation of rack dynamometric system for many years, can improve the measurement accuracy of existing rack dynamometric system.
Description
Technical field
The utility model belongs to engine measuring field, and in particular to one kind is used for aeroengine thrust measurement sensor
Thermostat.
Background technology
In engine test facility, the measurement accuracy of load cell is most important, it is related to entire engine test
Can the measurement accuracy of equipment reach desired design requirement, and the region in China is vast, and weather conditions are multifarious, especially
In the Northeast, summer, outside air temperature can reach 40 ° or more, and winter outside air temperature can be reduced to -40 ° hereinafter, the temperature difference reaches again
To 80 ° or more, maximum temperature reaches under 120 ° of temperature environment in stratochamber, is sensed under the temperature difference condition of difference big in this way
The measurement accuracy of device is certain to influenced to different extents, measurement error caused by how reducing due to the environment temperature,
Become us and improve an important indicator of engine test ability, particularly along with a large amount of engine test facilities in China
For example outdoor test bay of construction, the environmental conditions such as benchmark test bay it is more complicated severe, measurement accuracy requires higher testing stand
It establishes, the demand to sensor thermostat is more urgent.
Utility model content
Purpose of utility model：The heat exchange between thrust measurement sensor and external environment is reduced, according to the temperature of sensor
Degree situation can automatically adjust the external temperature of sensor.
Technical solution：A kind of sensor thermostat measured for aeroengine thrust is provided, is connected including metal
Plate 1, heat-insulated connecting plate 2, connection bolt 3, thermal insulation housing 4, heat insulating washer 5, power transmission screw rod 6, power transmission collet 7, temp auto-controlled electricity
The torrid zone 9 and pressure head 8；
Thermal insulation housing 4, power transmission collet 7 and heat-insulated connecting plate 2 surround heat-insulation chamber, 3 thrust measurement of connection bolt
Sensor is arranged in heat-insulation chamber, and 6 one end of power transmission screw rod is connect with thrust measurement sensor measurement end, the other end and power transmission every
Hot jacket 7 is held out against；Threaded hole is provided on heat-insulated connecting plate 2, connection bolt 3 is connect by threaded hole with sensor connecting pin；
Self temperature control heating tape is arranged in the heat-insulation chamber, for the temperature in heat-insulation chamber to be kept constant；
Heat-insulated 2 outer patch of connecting plate, which is close to, is connected to metal connecting plate 1, and metal connecting plate is provided with through-hole, and connection bolt passes through
The through-hole and there are gaps with through-hole, connects and sets the heat insulating washer 5 between bolt and metal connecting plate；Power transmission is heat-insulated
Set 7 is fixedly connected with pressure head；
2 material of heat-insulated connecting plate is ceramics.
Further, the material of thermal insulation housing 4 is polyurethane foam.
Further, the material of heat insulating washer 5 is ceramics.
Further, the material of power transmission collet 7 is ceramics.
Further, it is enclosed with heat insulation cap 10 on the nut of the connection bolt.
Advantageous effect：
1. for the equipment in the larger environment of outdoor testing equipment and temperature change, biography can be improved using thermostat
The measurement accuracy of sensor, reduce sensor zero are floatd.
2. for the test bay of benchmark test bay and thrust measure precision more than 0.25%, used by measurement sensor
The raising of precision makes being improved for rack measurement accuracy.
3. the device can be used for having used the transformation of rack dynamometric system for many years, existing rack dynamometric system can be improved
Measurement accuracy.
Description of the drawings
Fig. 1 is the structure diagram of the prior art；
Fig. 2 is the structure diagram of the utility model；
Wherein：1- metal connecting plates；The heat-insulated connecting plates of 2-；3- connection bolts；4- thermal insulation housings；5- heat insulating washers；
6- power transmission screw rods；7- power transmission collets；8- pressure heads；9- self temperature control heating tapes；10- heat insulation caps；11- sensors.
Specific embodiment
The utility model is described in further detail below in conjunction with the accompanying drawings, is please referred to Fig.1.
A kind of sensor thermostat measured for aeroengine thrust is provided, including metal connecting plate 1, heat-insulated company
Fishplate bar 2, connection bolt 3, thermal insulation housing 4, heat insulating washer 5, power transmission screw rod 6, power transmission collet 7, self temperature control heating tape 9 and pressure head
8；
Thermal insulation housing 4, power transmission collet 7 and heat-insulated connecting plate 2 surround heat-insulation chamber, 3 thrust measurement of connection bolt
Sensor is arranged in heat-insulation chamber, and 6 one end of power transmission screw rod is connect with thrust measurement sensor measurement end, the other end and power transmission every
Hot jacket 7 is held out against；Threaded hole is provided on heat-insulated connecting plate 2, connection bolt 3 is connect by threaded hole with sensor connecting pin；
Self temperature control heating tape is arranged in the heat-insulation chamber, for the temperature in heat-insulation chamber to be kept constant；
Heat-insulated 2 outer patch of connecting plate, which is close to, is connected to metal connecting plate 1, and metal connecting plate is provided with through-hole, and connection bolt passes through
The through-hole and there are gaps with through-hole, connects and sets the heat insulating washer 5 between bolt and metal connecting plate；Power transmission is heat-insulated
Set 7 is fixedly connected with pressure head；
2 material of heat-insulated connecting plate is ceramics.
Further, the material of thermal insulation housing 4 is polyurethane foam.
Further, the material of heat insulating washer 5 is ceramics.
Further, the material of power transmission collet 7 is ceramics.
Further, it is enclosed with heat insulation cap 10 on the nut of the connection bolt.
Claims (6)
1. a kind of sensor thermostat measured for aeroengine thrust, including metal connecting plate, heat-insulated connecting plate, company
Connecting bolt, thermal insulation housing, heat insulating washer, power transmission screw rod, power transmission collet, self temperature control heating tape and pressure head；
Thermal insulation housing, power transmission collet and heat-insulated connecting plate surround heat-insulation chamber, and the connection bolt thrust measurement sensor is set
It puts in heat-insulation chamber, and power transmission screw rod one end is connect with thrust measurement sensor measurement end, the other end is held out against with power transmission collet；
Threaded hole is provided on heat-insulated connecting plate, connection bolt is connect by threaded hole with sensor connecting pin；
Self temperature control heating tape is arranged in the heat-insulation chamber, for the temperature in heat-insulation chamber to be kept constant；
Heat-insulated connecting plate outer patch, which is close to, is connected to metal connecting plate, and metal connecting plate is provided with through-hole, and connection bolt passes through described
Through-hole and with through-hole there are gap, connect and the heat insulating washer be set between bolt and metal connecting plate；Power transmission collet and pressure
Head is fixedly connected.
2. a kind of sensor thermostat measured for aeroengine thrust as described in claim 1, it is characterised in that：
The heat-insulated connecting plate material is ceramics.
3. a kind of sensor thermostat measured for aeroengine thrust as described in claim 1, it is characterised in that：
The material of thermal insulation set is polyurethane foam.
4. a kind of sensor thermostat measured for aeroengine thrust as described in claim 1, it is characterised in that：
The material of heat insulating washer is ceramics.
5. a kind of sensor thermostat measured for aeroengine thrust as described in claim 1, it is characterised in that：
The material of power transmission collet is ceramics.
6. a kind of sensor thermostat measured for aeroengine thrust as described in claim 1, it is characterised in that：
Heat insulation cap is enclosed on the nut of the connection bolt.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721396386.8U CN207529247U (en) | 2017-10-25 | 2017-10-25 | A kind of sensor thermostat measured for aeroengine thrust |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721396386.8U CN207529247U (en) | 2017-10-25 | 2017-10-25 | A kind of sensor thermostat measured for aeroengine thrust |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207529247U true CN207529247U (en) | 2018-06-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721396386.8U Active CN207529247U (en) | 2017-10-25 | 2017-10-25 | A kind of sensor thermostat measured for aeroengine thrust |
Country Status (1)
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| CN (1) | CN207529247U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112362469A (en) * | 2020-09-29 | 2021-02-12 | 东莞材料基因高等理工研究院 | Small punch test device |
| CN112616199A (en) * | 2020-12-01 | 2021-04-06 | 上海数捷电气有限公司 | Constant temperature type position measurement sensor |
| CN116812167A (en) * | 2023-07-04 | 2023-09-29 | 涵涡智航科技(玉溪)有限公司 | Measuring device for torque and lift force of aircraft power system |
-
2017
- 2017-10-25 CN CN201721396386.8U patent/CN207529247U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112362469A (en) * | 2020-09-29 | 2021-02-12 | 东莞材料基因高等理工研究院 | Small punch test device |
| CN112616199A (en) * | 2020-12-01 | 2021-04-06 | 上海数捷电气有限公司 | Constant temperature type position measurement sensor |
| CN116812167A (en) * | 2023-07-04 | 2023-09-29 | 涵涡智航科技(玉溪)有限公司 | Measuring device for torque and lift force of aircraft power system |
| CN116812167B (en) * | 2023-07-04 | 2024-01-26 | 涵涡智航科技(玉溪)有限公司 | Measuring device for torque and lift force of aircraft power system |
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