CN201163220Y - Armored thermocouple calibrating device for aircraft engine - Google Patents
Armored thermocouple calibrating device for aircraft engine Download PDFInfo
- Publication number
- CN201163220Y CN201163220Y CN 200720311046 CN200720311046U CN201163220Y CN 201163220 Y CN201163220 Y CN 201163220Y CN 200720311046 CN200720311046 CN 200720311046 CN 200720311046 U CN200720311046 U CN 200720311046U CN 201163220 Y CN201163220 Y CN 201163220Y
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- standard
- armoured thermocouple
- temperature
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- digital voltmeter
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- 238000009434 installation Methods 0.000 claims abstract description 10
- 230000037431 insertion Effects 0.000 claims 1
- 238000003780 insertion Methods 0.000 claims 1
- 238000005485 electric heating Methods 0.000 abstract 3
- 238000000034 method Methods 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 230000002277 temperature effect Effects 0.000 description 1
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Abstract
The utility model belongs to aeroengine test technique relates to and improves aeroengine armor thermocouple calibrating installation. The device comprises an electric heating furnace [1], a temperature equalizing block [3], a standard armored thermocouple [4], an ice bottle [5], a first digital voltmeter [6] and a second digital voltmeter [8 ]; the device is characterized by comprising a standard temperature display controller [9], wherein the output end of a standard armored thermocouple [4] is immersed in an ice bottle [5] and then is connected with the temperature input end of the standard temperature display controller [9] through a lead; the control output end of the standard temperature display control instrument [9] is connected with the input end of the electric heating furnace [1 ]. The utility model discloses can the temperature of accurate control electric heating furnace [1], control accuracy is high, and constant temperature is effectual, has improved examination efficiency.
Description
Technical field
The utility model belongs to the aeromotor measuring technology, relates to aeromotor armoured thermocouple calibrating installation is improved.
Background technology
The aeromotor armoured thermocouple calibrating installation that adopts is referring to Fig. 1 at present, and it is made up of electric furnace 1, manual voltage regulator 2, block 3, standard armoured thermocouple 4, ice chest 5, first digital voltmeter 6 and second digital voltmeter 8.Block 3 is positioned at electric furnace 1, and in the standard armoured thermocouple mounting hole that standard armoured thermocouple 4 inserts on the block 3, terminal ice chest 5 backs of immersing of the output of standard armoured thermocouple 4 are connected by the input end of lead with first digital voltmeter 6; Block 3 has the calibrating hole of installing by calibrating armoured thermocouple 7, is examined and determine armoured thermocouple 7 and inserts in the above-mentioned calibrating hole, and the output terminal of being examined and determine armoured thermocouple 7 is connected with the input end of second digital voltmeter 8.Change the height of the Control of Voltage temperature of input electric furnace 1 by manual voltage regulator 2.The shortcoming of this calibrating installation is: the moving pressure regulator 4 of the temperature armrest of electric furnace 1 is regulated, and control accuracy is poor.On each calibrating point, if the temperature height then needs voltage is turned down; Otherwise, then need voltage is heightened.So each point all will repeatedly be regulated, and not only the constant temperature effect is bad, and efficient is extremely low, and error is big.
Summary of the invention
The purpose of this utility model is: propose a kind of control accuracy height, good constant-temperature effect, aeromotor armoured thermocouple calibrating installation that calibrating efficient is high.
The technical solution of the utility model is: aeromotor armoured thermocouple calibrating installation, and it comprises electric furnace 1, block 3, standard armoured thermocouple 4, ice chest 5, first digital voltmeter 6 and second digital voltmeter 8; Block 3 is positioned at electric furnace 1, and in the standard armoured thermocouple mounting hole that standard armoured thermocouple 4 inserts on the block 3, terminal ice chest 5 backs of immersing of the output of standard armoured thermocouple 4 are connected by the input end of lead with first digital voltmeter 6; Block 3 has the calibrating hole of installing by calibrating armoured thermocouple 7, is examined and determine armoured thermocouple 7 and inserts in the above-mentioned calibrating hole, and the output terminal of being examined and determine armoured thermocouple 7 is connected with the input end of second digital voltmeter 8; It is characterized in that having a standard temperature to show controller 9, terminal ice chest 5 backs of immersing of the output of standard armoured thermocouple 4 show that by lead and standard temperature the temperature input end of controller 9 is connected; Standard temperature shows that the control output end of controller 9 is connected with the input end of electric furnace 1.
The utility model has the advantages that: adopt standard temperature to show the accurately temperature of control electric furnaces 1 of controller 9, participation that need not the people, control accuracy height, good constant-temperature effect has alleviated operator's labour intensity, has improved calibrating efficient, manually compare, reduce by about 1/3 calibrating time.
Description of drawings
Fig. 1 is existing aeromotor armoured thermocouple calibrating installation structure principle chart.
Fig. 2 is a structure principle chart of the present utility model.
Embodiment
Be described in further detail the utility model is bright below.Referring to Fig. 2, aeromotor armoured thermocouple calibrating installation, it comprises electric furnace 1, block 3, standard armoured thermocouple 4, ice chest 5, first digital voltmeter 6 and second digital voltmeter 8; Block 3 is positioned at electric furnace 1, and in the standard armoured thermocouple mounting hole that standard armoured thermocouple 4 inserts on the block 3, terminal ice chest 5 backs of immersing of the output of standard armoured thermocouple 4 are connected by the input end of lead with first digital voltmeter 6; Block 3 has the calibrating hole of installing by calibrating armoured thermocouple 7, is examined and determine armoured thermocouple 7 and inserts in the above-mentioned calibrating hole, and the output terminal of being examined and determine armoured thermocouple 7 is connected with the input end of second digital voltmeter 8; It is characterized in that having a standard temperature to show controller 9, terminal ice chest 5 backs of immersing of the output of standard armoured thermocouple 4 show that by lead and standard temperature the temperature input end of controller 9 is connected; Standard temperature shows that the control output end of controller 9 is connected with the input end of electric furnace 1.
The utility model shows that by standard armoured thermocouple 4 and standard temperature 9 pairs of electric furnaces of controller 1 form closed-loop control, thereby accurately controls the temperature of electric furnace 1.
Among the embodiment of the present utility model, the model of institute's accepted standard display temperature controller 9 is to be Xiamen space light AI-708 type.
Claims (1)
1, aeromotor armoured thermocouple calibrating installation, it comprises electric furnace [1], block [3], standard armoured thermocouple [4], ice chest [5], first digital voltmeter [6] and second digital voltmeter [8]; Block [3] is positioned at electric furnace [1], in the standard armoured thermocouple mounting hole on standard armoured thermocouple [4] the insertion block [3], terminal ice chest [5] back of immersing of the output of standard armoured thermocouple [4] is connected by the input end of lead with first digital voltmeter [6]; Block [3] has the calibrating hole of installing by calibrating armoured thermocouple [7], is examined and determine armoured thermocouple [7] and inserts in the above-mentioned calibrating hole, and the output terminal of being examined and determine armoured thermocouple [7] is connected with the input end of second digital voltmeter [8]; It is characterized in that having a standard temperature to show controller [9], terminal ice chest [5] back of immersing of the output of standard armoured thermocouple [4] shows that by lead and standard temperature the temperature input end of controller [9] is connected; Standard temperature shows that the control output end of controller [9] is connected with the input end of electric furnace [1].
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200720311046 CN201163220Y (en) | 2007-12-20 | 2007-12-20 | Armored thermocouple calibrating device for aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200720311046 CN201163220Y (en) | 2007-12-20 | 2007-12-20 | Armored thermocouple calibrating device for aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201163220Y true CN201163220Y (en) | 2008-12-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200720311046 Expired - Fee Related CN201163220Y (en) | 2007-12-20 | 2007-12-20 | Armored thermocouple calibrating device for aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201163220Y (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102944735A (en) * | 2012-11-21 | 2013-02-27 | 重庆材料研究院 | Automatic test system and test method for thermoelectric forces of thermocouple wires |
| CN103063329A (en) * | 2012-12-28 | 2013-04-24 | 沪东重机有限公司 | Calibration method for marine diesel engine temperature-measurement thermocouple |
| CN103575425A (en) * | 2012-07-24 | 2014-02-12 | 浙江泰索科技有限公司 | Automatic compensation-type thermocouple metrological verification polarity extension connector |
| CN104458061A (en) * | 2014-12-25 | 2015-03-25 | 上海冉曦电子仪器有限公司 | Combined thermocouple calibration furnace |
| CN104458059A (en) * | 2014-11-25 | 2015-03-25 | 安徽恒源煤电股份有限公司 | Calibration device of thermocouple series |
| CN105865658A (en) * | 2015-01-23 | 2016-08-17 | 北京空间飞行器总体设计部 | Ground calibration method of miniature sheathed thermocouple |
| CN106197756A (en) * | 2015-05-28 | 2016-12-07 | 北京卫星环境工程研究所 | Spacecraft thermal test hot thermocouple response test instrument |
| CN107101747A (en) * | 2017-01-22 | 2017-08-29 | 北京交通发展研究院 | A kind of standard thermometer and its application method |
| CN107314834A (en) * | 2017-08-07 | 2017-11-03 | 苏州市计量测试研究所 | A kind of curved surfaces thermometer calibration device and calibration method |
-
2007
- 2007-12-20 CN CN 200720311046 patent/CN201163220Y/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103575425A (en) * | 2012-07-24 | 2014-02-12 | 浙江泰索科技有限公司 | Automatic compensation-type thermocouple metrological verification polarity extension connector |
| CN102944735A (en) * | 2012-11-21 | 2013-02-27 | 重庆材料研究院 | Automatic test system and test method for thermoelectric forces of thermocouple wires |
| CN103063329A (en) * | 2012-12-28 | 2013-04-24 | 沪东重机有限公司 | Calibration method for marine diesel engine temperature-measurement thermocouple |
| CN104458059A (en) * | 2014-11-25 | 2015-03-25 | 安徽恒源煤电股份有限公司 | Calibration device of thermocouple series |
| CN104458061A (en) * | 2014-12-25 | 2015-03-25 | 上海冉曦电子仪器有限公司 | Combined thermocouple calibration furnace |
| CN105865658A (en) * | 2015-01-23 | 2016-08-17 | 北京空间飞行器总体设计部 | Ground calibration method of miniature sheathed thermocouple |
| CN105865658B (en) * | 2015-01-23 | 2018-08-07 | 北京空间飞行器总体设计部 | A kind of ground scaling method of miniature armoured thermocouple |
| CN106197756A (en) * | 2015-05-28 | 2016-12-07 | 北京卫星环境工程研究所 | Spacecraft thermal test hot thermocouple response test instrument |
| CN107101747A (en) * | 2017-01-22 | 2017-08-29 | 北京交通发展研究院 | A kind of standard thermometer and its application method |
| CN107314834A (en) * | 2017-08-07 | 2017-11-03 | 苏州市计量测试研究所 | A kind of curved surfaces thermometer calibration device and calibration method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| ASS | Succession or assignment of patent right |
Owner name: GUIZHOU LIYANG AERO-ENGINE CO., LTD. Free format text: FORMER OWNER: GUIZHOU LIYANG AERO ENGINE CO., LTD. Effective date: 20110414 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| COR | Change of bibliographic data |
Free format text: CORRECT: ADDRESS; FROM: 561102 MAILBOX 5, PINGBA COUNTY, GUIZHOU PROVINCE TO: 561102 MAILBOX 207, PINGBA COUNTY, GUIZHOU PROVINCE |
|
| TR01 | Transfer of patent right |
Effective date of registration: 20110414 Address after: 561102 Guizhou province Pingba County box 207 Patentee after: Guizhou Liyang Aerospace Power Co., Ltd. Address before: 561102 Guizhou province Pingba County box No. 5 Patentee before: Guizhou Liyang Aero Engine Co., Ltd. |
|
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20081210 Termination date: 20151220 |
|
| EXPY | Termination of patent right or utility model |