CN210664828U - Aeroengine EGT collection system - Google Patents
Aeroengine EGT collection system Download PDFInfo
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- CN210664828U CN210664828U CN201921628290.9U CN201921628290U CN210664828U CN 210664828 U CN210664828 U CN 210664828U CN 201921628290 U CN201921628290 U CN 201921628290U CN 210664828 U CN210664828 U CN 210664828U
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- thermistor
- thermocouple
- egt
- temperature
- aircraft engine
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Abstract
The utility model relates to an aeroengine EGT collection system, including thermocouple (2), thermocouple (2) are connected with wire box (4), still include thermistor (1), thermistor (1) are connected with wire box (4), gather group's monomer (3) and include at least one thermistor and at least one thermocouple. Compared with the prior art, whether the final display temperature is correct can be judged.
Description
Technical Field
The utility model belongs to the technical field of the aeroengine and specifically relates to an aeroengine EGT collection system is related to.
Background
EGT (EXHAUSTGASETMPERATURE) is an exhaust temperature system used to measure exhaust temperature. Turbine gas temperature, indicated using EGT, is a key parameter in engine operation. The turbine is the most thermally and mechanically stressed component of the engine, and in order to ensure reliable operation at high temperatures, the gas temperature in front of the turbine must be controlled. The ideal situation is to measure the total gas temperature before the turbine, namely the turbine inlet temperature, but the temperature is high, the temperature field distribution is not uniform, and the measurement is difficult. The temperature drop in the turbine is known, so measuring and limiting the exhaust gas temperature can achieve the purpose of limiting the total temperature of the gas before the turbine within an allowable range value.
At present, the EGT is mainly acquired by adopting thermocouples, each group of 4 thermocouples form an acquisition group monomer in the existing mode, a plurality of acquisition group monomers are arranged on a low-pressure turbine exhaust box in a surrounding mode, and the 4 thermocouples of each group are used for calculation after the mean value is obtained.
The temperature value is obtained by the electromotive force at the two ends of the thermocouple divided hot end and cold end, the electromotive force between the two ends of the thermocouple in a humid environment is reduced, the temperature display is caused to be lower than the true value of the temperature, and the temperature display has a false report at the moment.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing an aeroengine EGT collection system for overcoming the defect that above-mentioned prior art exists.
The purpose of the utility model can be realized through the following technical scheme:
the EGT collecting device for the aircraft engine comprises a thermocouple, a thermistor and a collecting group monomer, wherein the thermocouple is connected with a lead box, the thermistor is connected with the lead box, and the collecting group monomer comprises at least one thermistor and at least one thermocouple.
The thermocouple and the thermistor are connected with the wire box through cables, and the cables are covered with shielding layers.
The cold end of the thermocouple is connected with a nickel-aluminum alloy wiring terminal, and the hot end of the thermocouple is connected with a nickel-chromium alloy wiring terminal.
The thermistor is a thermistor with a temperature measuring range of-55-315 ℃.
The thermistor is an MF58 thermistor.
The wire box be equipped with drying device, drying device is for arranging the silica gel piece of wire box's inner wall in.
The silica gel sheet is added with cobaltous chloride.
The silica gel sheet is bonded with the inner wall of the lead box.
Compared with the prior art, the utility model has the advantages of it is following:
(1) the acquisition group monomer comprises at least one thermistor and at least one thermocouple, the resistance of the thermistor is reduced in a humid environment, and the temperature display is higher because the thermistor has a negative temperature coefficient; when the electromotive force between the two ends of the thermocouple in the humid environment is reduced, the temperature display is low; the combination of the two can judge whether the final display temperature is correct.
(2) The cable is covered with the shielding layer, can play the electric shield effect, guarantees the accuracy of cable transmission signal.
(3) The thermistor is a thermistor with the temperature measuring range of-55-315 ℃, and the temperature range covers the temperature range of the aircraft engine.
(4) The lead box is provided with the silica gel sheet arranged on the inner wall of the lead box, so that the lead box can be prevented from being wet to a certain extent.
(5) The silica gel piece is added with cobaltous chloride, can change the color after absorbing moisture, and staff can judge whether to change the silica gel piece according to the color.
Drawings
Fig. 1 is a schematic structural view of the present invention;
reference numerals:
1 is a thermistor; 2 is a thermocouple; 3 is a collection group monomer; and 4, a lead box.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. The embodiment is implemented on the premise of the technical solution of the present invention, and a detailed implementation manner and a specific operation process are given, but the scope of the present invention is not limited to the following embodiments.
Examples
The embodiment provides an aeroengine EGT collection system, including thermocouple 2 and thermistor 1, thermocouple 2 and thermistor 1 all are connected with wire box 4, and collection group's monomer 3 includes at least one thermistor and at least one thermocouple.
Furthermore, the thermocouple 2 and the thermistor 1 are both connected with the wire box 4 through cables, and the cables are covered with shielding layers, so that an electric shielding effect can be achieved, and the accuracy of signal transmission of the cables is ensured; the cold end of the thermocouple 2 is connected with a nickel-aluminum alloy wiring terminal, and the hot end of the thermocouple 2 is connected with a nickel-chromium alloy wiring terminal, so that the temperature measured by the thermocouple 2 is more accurate;
the thermistor 1 is a thermistor with the temperature measuring range of-55-315 ℃, the temperature range covers the temperature range of the aircraft engine, and the thermistor 1 is an MF58 thermistor.
The wire box 4 is provided with a drying device which is a silica gel sheet arranged on the inner wall of the wire box 4, the silica gel sheet is a silica gel sheet added with cobaltous chloride, and the silica gel sheet is adhered to the inner wall of the wire box 4; can prevent wire box 4 humidity to a certain extent, the silica gel piece that adds cobaltous chloride can change the colour after absorbing moisture, and the staff can judge whether need change the silica gel piece according to the colour.
Taking the example that the collection group monomer 3 comprises two thermistors and two thermocouples as an example, the specific working mode is as follows: the electronic control unit (EEC) can receive signals of two thermistors and signals of two thermocouples, the signals of the two thermistors are averaged and calculated to obtain the temperature of the thermistors, the signals of the two thermocouples are averaged and calculated to obtain the temperature of the thermocouples, and the temperature of the thermistors and the temperature of the thermocouples are averaged to obtain the final temperature and display the final temperature; the resistance value of the thermistor 1 is reduced in a humid environment, and the temperature of the thermistor is higher due to the humidity because the thermistor 1 has a negative temperature coefficient; when the electromotive force between the two ends of the thermocouple 2 is reduced in a humid environment, the temperature of the thermocouple is lower due to the humidity; when the EEC judges that the temperature of the thermistor is higher and the temperature of the thermocouple is lower, the final temperature displayed at present is considered to be incorrect, and the display device is controlled to send out warning information.
Claims (8)
1. The EGT collecting device for the aircraft engine comprises a thermocouple (2), wherein the thermocouple (2) is connected with a lead box (4), and is characterized by further comprising a thermistor (1), the thermistor (1) is connected with the lead box (4), and a collecting group unit (3) comprises at least one thermistor and at least one thermocouple.
2. An aeroengine EGT collection device according to claim 1, wherein the thermocouple (2) and the thermistor (1) are both connected to the wire box (4) by a cable, and the cable is covered with a shielding layer.
3. The aircraft engine EGT collecting device as claimed in claim 1, characterized in that the cold end of the thermocouple (2) is connected with a nickel-aluminum alloy terminal, and the hot end of the thermocouple (2) is connected with a nickel-chromium alloy terminal.
4. The aircraft engine EGT collection device according to claim 1, wherein the thermistor (1) is a thermistor with a temperature measuring range of-55 ℃ to 315 ℃.
5. The aircraft engine EGT collection device according to claim 1, wherein the thermistor (1) is an MF58 thermistor.
6. The aircraft engine EGT collection device according to claim 1, characterized in that the wire box (4) is provided with a drying device, and the drying device is a silicon sheet arranged on the inner wall of the wire box (4).
7. The aircraft engine EGT collection device of claim 6, wherein the silica gel sheet is added with cobaltous chloride.
8. The aircraft engine EGT collection device according to claim 6, wherein the silicone sheet is adhered to the inner wall of the wire box (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921628290.9U CN210664828U (en) | 2019-09-27 | 2019-09-27 | Aeroengine EGT collection system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921628290.9U CN210664828U (en) | 2019-09-27 | 2019-09-27 | Aeroengine EGT collection system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210664828U true CN210664828U (en) | 2020-06-02 |
Family
ID=70811683
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921628290.9U Active CN210664828U (en) | 2019-09-27 | 2019-09-27 | Aeroengine EGT collection system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210664828U (en) |
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2019
- 2019-09-27 CN CN201921628290.9U patent/CN210664828U/en active Active
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