CN105651408A - Aero-engine exhaust gas temperature sensor - Google Patents
Aero-engine exhaust gas temperature sensor Download PDFInfo
- Publication number
- CN105651408A CN105651408A CN201510965746.0A CN201510965746A CN105651408A CN 105651408 A CN105651408 A CN 105651408A CN 201510965746 A CN201510965746 A CN 201510965746A CN 105651408 A CN105651408 A CN 105651408A
- Authority
- CN
- China
- Prior art keywords
- armoured thermocouple
- thermocouple cable
- lining
- mount pad
- housing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K7/00—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements
- G01K7/02—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using thermoelectric elements, e.g. thermocouples
- G01K7/04—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using thermoelectric elements, e.g. thermocouples the object to be measured not forming one of the thermoelectric materials
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K13/00—Thermometers specially adapted for specific purposes
- G01K13/02—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K13/00—Thermometers specially adapted for specific purposes
- G01K13/02—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow
- G01K13/024—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow of moving gases
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measuring Temperature Or Quantity Of Heat (AREA)
Abstract
The invention discloses an aero-engine exhaust gas temperature sensor. A cable is fixed in a bushing in a penetration way. The bushing is welded and fixed on a flange plate and a segment of armored thermocouple cables is exposed. The flange plate is provided with an installing hole assembled with an engine case. The three armored thermocouple cables are formed through bending and matched with the shape of the engine case, and the exposed ends corresponding to the flange plate are evenly distributed in a circumferential direction. One end, which is away from the flange plate, of each armored thermocouple cable is sealed and fixedly connected in a socket. The temperature sensor is low in weight (120g), high in response time (tau0.632 is 1.5s), accurate in temperature measurement precision (precision is +/-4 DEG C at temperature of 1000 DEG C) and integrated in functions of temperature measurement and signal transmission so that the use requirements of new aero-engines can be met. The technical appraisal proves that all the indexes can meet the use requirements.
Description
Technical field
The invention belongs to temperature sensor, particularly relate to a kind of small-sized integrated design temperature sensor for aircraft engine exhaust.
Background technology
Exhaust temperature of aircraft engine signal need to be gathered by thermocouple temperature sensor, domestic novel aircraft engine is just to trend developments such as big thrust loading, high rotating speed, high-temperatures, traditional exhaust gas temperature sensor adopts split-type design, quality is heavy and dismounting is complicated, insulation decline easily occurs and affect temperature measurement accuracy under integral high-temperature environment. Therefore the exhaust gas temperature sensor developing gently (weight is light), fast (time of response is fast), accurate (temperature measurement accuracy is accurate) is very important to the development of China's aircraft engine.
Summary of the invention
The object of the present invention aims to provide a kind of exhaust temperature of aircraft engine sensor, solves the problem that this type of sensor is light, fast, accurate.
The above-mentioned purpose of the present invention, to be achieved by the following technical programs: a kind of exhaust temperature of aircraft engine sensor, it is characterized in that being connected formed by socket and three groups of armoured thermocouple cables, sleeve pipe, ring flanges, wherein said armoured thermocouple cable cross-under is fixed in sleeve pipe, described sleeve pipe is fixedly welded on ring flange and exposes one section of armoured thermocouple cable, and described ring flange is provided with the open holes filled mutually with motor case; One end that three armoured thermocouple cable bending and moldings expose with motor case form fit and corresponding ring flange is that circumference is uniformly distributed, and each bar armoured thermocouple cable is fixed in socket away from one end sealing of ring flange.
Further, described socket is provided with abutting end subgroup, mount pad, the housing of cannula-like and lining, wherein mount pad sealing is fixed in one end of housing and is provided with the threading hole of cross-under armoured thermocouple cable, the other end of described housing is connected in the sealing of abutting end subgroup, inside the housing being lining between mount pad and abutting end subgroup in described lining, described armoured thermocouple cable cross-under location and mount pad and lead-in wire couple mutually with abutting end subgroup, fill out and be provided with devitrified glass and seal in lining.
Further, described armoured thermocouple cable is the fine rule type thermocouple cable of �� 2.5mm.
The application implementation of technical solution of the present invention, the remarkable advantage comparing to prior art is: this temperature sensor weight light (120g), time of response fast (�� 0.632 is 1.5s), temperature measurement accuracy standard (when 1000 DEG C, precision is �� 4 DEG C), integrate and survey temperature and signal transfer functions, it is possible to meet the service requirements of novel aircraft engine.Service requirements all can be met through the every index of technical evaluation.
Accompanying drawing explanation
Fig. 1 is the main TV structure schematic diagram of exhaust gas temperature sensor of the present invention.
Fig. 2 is the left view structural representation of exhaust gas temperature sensor of the present invention.
Fig. 3 is the sectional view of exhaust gas temperature sensor signal output terminal of the present invention.
Embodiment
Below in conjunction with drawings and Examples, the present invention is described in detail.
As shown in Figure 1 to Figure 3, this exhaust temperature of aircraft engine sensor, connected formed by socket and three groups of armoured thermocouple cables 1, sleeve pipe 2, ring flanges 3, wherein said armoured thermocouple cable cross-under is fixed in sleeve pipe, described sleeve pipe is fixedly welded on ring flange and exposes one section of armoured thermocouple cable, and described ring flange is provided with the open holes filled mutually with motor case; One end that three armoured thermocouple cable bending and moldings expose with motor case form fit and corresponding ring flange is that circumference is uniformly distributed, and each bar armoured thermocouple cable is fixed in socket away from one end sealing of ring flange.
More refinement ground, above-mentioned socket is provided with abutting end subgroup 6, mount pad 8, the housing 4 of cannula-like and lining 7, wherein mount pad sealing is fixed in one end of housing and is provided with the threading hole of cross-under armoured thermocouple cable, the other end of described housing is connected in the sealing of abutting end subgroup, inside the housing being lining between mount pad and abutting end subgroup in described lining, described armoured thermocouple cable cross-under location and mount pad and lead-in wire and abutting end subgroup couple mutually, fill out and be provided with devitrified glass 5 and seal in lining.
Owing to aircraft engine exhaust section temperature field is uneven, the present invention adopts three to wait long armoured thermocouple cables, sets up three-dimensional model according to engine profile, by parallel at output terminal after number controlled pipe bender bending and molding, finally exports the medial temperature of 3. armoured thermocouple cable and sleeve pipe are fixed by vacuum brazing, and sleeve pipe and ring flange are fixed by argon arc welding, and ring flange and motor case are bolted. this engine thrust-weight ratio requires very high, weight and time of response to sensor require higher than traditional sensor, therefore the present invention selects external diameter to be the armoured thermocouple cable of �� 2.5mm, its metal wall thickness is only 0.3mm, general welding process is difficult to ensure that neither metallic walls is worn in weldering can tolerate again the comprehensive stress of temperature disturbance on engine, the present invention adopts BNi82CrSiB nickel-based solder that armoured thermocouple cable is carried out vacuum brazing, so not only can fix but also can remove the stress in bending of armoured thermocouple cable, in brazing process, control temperature is lower than standard 50 DEG C, soaking time 15min shorter in standard, prevent solder to metallic walls corrosion.
Please refer to Fig. 2 and Fig. 3, armoured thermocouple cable and mount pad are fixed by vacuum brazing, mount pad is connected by Laser Welding with lining, mount pad is connected by argon arc welding with housing, housing is connected by argon arc welding with socket, and armoured thermocouple cable thermo wires is connected by flame brazing with socket contact pin. this engine power is big, wall surface temperature height, the temperatures as high of sensor signal output terminal 500 DEG C, if armoured thermocouple signal output terminal blow-by causes insulation resistance to decline, its temperature measurement accuracy just is difficult to ensure, general material is difficult to ensure stopping property under 500 DEG C of high temperature, the present invention is sintered glass-ceramics in lining, this devitrified glass need to possess and nichrome, nickel silicon alloy, the coefficient of expansion that stainless steel 1Cr18Ni9Ti phase is mated, after sintering, leakage rate at 1 atmosphere pressure is not more than 1 �� 10-3Pa cm3/s, the normal temperature insulation resistance of sensor like this can ensure to be not less than 500M �� (500VDC), it it is the requirement of �� 4 DEG C when its precision can meet 1000 DEG C.
The foregoing is only the better embodiment of the present invention, not in order to limit the present invention. It is noted that for the person of ordinary skill of the art, every any amendment, replacement or improvement etc. done in the principle of the invention, all should be included within protection scope of the present invention.
Claims (3)
1. an exhaust temperature of aircraft engine sensor, it is characterized in that being connected formed by socket and three groups of armoured thermocouple cables, sleeve pipe, ring flanges, wherein said armoured thermocouple cable cross-under is fixed in sleeve pipe, described sleeve pipe is fixedly welded on ring flange and exposes one section of armoured thermocouple cable, and described ring flange is provided with the open holes filled mutually with motor case; One end that three armoured thermocouple cable bending and moldings expose with motor case form fit and corresponding ring flange is that circumference is uniformly distributed, and each bar armoured thermocouple cable is fixed in socket away from one end sealing of ring flange.
2. exhaust temperature of aircraft engine sensor according to claim 1, it is characterized in that: described socket is provided with abutting end subgroup, mount pad, the housing of cannula-like and lining, wherein mount pad sealing is fixed in one end of housing and is provided with the threading hole of cross-under armoured thermocouple cable, the other end of described housing is connected in the sealing of abutting end subgroup, inside the housing being lining between mount pad and abutting end subgroup in described lining, described armoured thermocouple cable cross-under location and mount pad and lead-in wire couple mutually with abutting end subgroup, fill out and be provided with devitrified glass and seal in lining.
3. exhaust temperature of aircraft engine sensor according to claim 1, it is characterised in that: described armoured thermocouple cable is the fine rule type thermocouple cable of �� 2.5mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510965746.0A CN105651408A (en) | 2015-12-22 | 2015-12-22 | Aero-engine exhaust gas temperature sensor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510965746.0A CN105651408A (en) | 2015-12-22 | 2015-12-22 | Aero-engine exhaust gas temperature sensor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105651408A true CN105651408A (en) | 2016-06-08 |
Family
ID=56476624
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510965746.0A Pending CN105651408A (en) | 2015-12-22 | 2015-12-22 | Aero-engine exhaust gas temperature sensor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105651408A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106679835A (en) * | 2016-12-08 | 2017-05-17 | 苏州长风航空电子有限公司 | Armored thermocouple sensor |
| CN109781286A (en) * | 2018-12-25 | 2019-05-21 | 重庆材料研究院有限公司 | The preparation method of the temperature-detecting device of high temperature and high pressure environment and the device |
| CN110132440A (en) * | 2019-05-31 | 2019-08-16 | 中国航发南方工业有限公司 | The assembly device and assembly method of armoured thermocouple device |
| CN113566993A (en) * | 2020-04-28 | 2021-10-29 | 中国航发商用航空发动机有限责任公司 | Engine temperature measuring device and heat insulation lining thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2625876Y (en) * | 2002-12-30 | 2004-07-14 | 沈阳黎明航空发动机(集团)有限责任公司 | Rotary testing apparatus for temperature of engine combustion chamber temperature field |
| CN103090988A (en) * | 2012-12-27 | 2013-05-08 | 中航(苏州)雷达与电子技术有限公司 | Sheathed thermocouple junction box and sealing method thereof |
| CN204271301U (en) * | 2014-12-02 | 2015-04-15 | 苏州长风航空电子有限公司 | A kind of thermocouple binding post of exhaust gas temperature sensor |
| CN204269246U (en) * | 2014-12-02 | 2015-04-15 | 苏州长风航空电子有限公司 | A kind of multi-measuring point armoured thermocouple device being applied to aeromotor |
| US20150114098A1 (en) * | 2013-10-30 | 2015-04-30 | Denso Corporation | Airflow measuring device |
-
2015
- 2015-12-22 CN CN201510965746.0A patent/CN105651408A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2625876Y (en) * | 2002-12-30 | 2004-07-14 | 沈阳黎明航空发动机(集团)有限责任公司 | Rotary testing apparatus for temperature of engine combustion chamber temperature field |
| CN103090988A (en) * | 2012-12-27 | 2013-05-08 | 中航(苏州)雷达与电子技术有限公司 | Sheathed thermocouple junction box and sealing method thereof |
| US20150114098A1 (en) * | 2013-10-30 | 2015-04-30 | Denso Corporation | Airflow measuring device |
| CN204271301U (en) * | 2014-12-02 | 2015-04-15 | 苏州长风航空电子有限公司 | A kind of thermocouple binding post of exhaust gas temperature sensor |
| CN204269246U (en) * | 2014-12-02 | 2015-04-15 | 苏州长风航空电子有限公司 | A kind of multi-measuring point armoured thermocouple device being applied to aeromotor |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106679835A (en) * | 2016-12-08 | 2017-05-17 | 苏州长风航空电子有限公司 | Armored thermocouple sensor |
| CN106679835B (en) * | 2016-12-08 | 2019-05-24 | 苏州长风航空电子有限公司 | A kind of armored thermocouple sensor |
| CN109781286A (en) * | 2018-12-25 | 2019-05-21 | 重庆材料研究院有限公司 | The preparation method of the temperature-detecting device of high temperature and high pressure environment and the device |
| CN110132440A (en) * | 2019-05-31 | 2019-08-16 | 中国航发南方工业有限公司 | The assembly device and assembly method of armoured thermocouple device |
| CN110132440B (en) * | 2019-05-31 | 2021-02-09 | 中国航发南方工业有限公司 | Assembly device and assembly method of armored thermocouple device |
| CN113566993A (en) * | 2020-04-28 | 2021-10-29 | 中国航发商用航空发动机有限责任公司 | Engine temperature measuring device and heat insulation lining thereof |
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Application publication date: 20160608 |
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| RJ01 | Rejection of invention patent application after publication |