CN104481608B - Temperature measuring equipment, whirlpool oar aero-engine and thermometry - Google Patents
Temperature measuring equipment, whirlpool oar aero-engine and thermometry Download PDFInfo
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- CN104481608B CN104481608B CN201410626150.3A CN201410626150A CN104481608B CN 104481608 B CN104481608 B CN 104481608B CN 201410626150 A CN201410626150 A CN 201410626150A CN 104481608 B CN104481608 B CN 104481608B
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Abstract
The invention provides a kind of temperature measuring equipment, whirlpool oar aero-engine and thermometry. This temperature measuring equipment includes: electric connector; Multiple thermocouples, for measuring the temperature of the discharge gas of aero-engine, are connected in parallel between multiple thermocouples, and electrically connect on electrical connectors. Application technical scheme so that the temperature measuring equipment in aero-engine can work steadily in the long term, and improves the accuracy that the temperature measuring equipment delivery temperature to aero-engine measures.
Description
Technical field
The present invention relates to engine apparatus field, in particular to a kind of temperature measuring equipment, whirlpool oar aero-engine and thermometry.
Background technology
Outlet air temperature is a very important parameter of aero-engine, pilot judges aero-engine whether overtemperature by monitoring delivery temperature, and pilot occurs taking urgent measure in overtemperature situation to ensure that aero-engine is properly functioning in aero-engine.
Certain whirlpool oar aero-engine is by measuring the fuel gas temperature at turbine outlet place, and the temperature signal measuring gained converts to signal of telecommunication output. At present, this existing delivery temperature measurement apparatus of whirlpool oar aero-engine is to adopt 4 thermocouples (i.e. 4 probes) to arrange in the way of being connected in series, and this delivery temperature measurement apparatus is that the mode exported by single channel converts the temperature signal of measurement gained to signal of telecommunication output.
At present, the reliability of existing delivery temperature measurement apparatus is not high, its series circuit easily breaks down (one of them thermocouple break may result in whole device cannot normal operation), so that this delivery temperature measurement apparatus collects inaccurate temperature signal, it could even be possible to the temperature therefore collected is lower than actual temperature, thus affecting the judgement of pilot, bring potential safety hazard to flight.
Summary of the invention
A kind of temperature measuring equipment of offer, whirlpool oar aero-engine and thermometry are provided, to solve in the measurement process in prior art, the delivery temperature of whirlpool oar aero-engine measured, the inaccurate problem of temperature measurement result of temperature measuring equipment job insecurity and its output.
To achieve these goals, according to an aspect of the invention, it is provided a kind of temperature measuring equipment includes: electric connector; Multiple thermocouples, for measuring the temperature of the discharge gas of aero-engine, are connected in parallel between multiple thermocouples, and electrically connect on electrical connectors.
Further, electric connector includes: the first input portion and the second input portion, and the first input portion and the second input portion are arranged in parallel on electrical connectors, and the temperature data of multiple thermocouples detection is delivered to electric connector by the first input portion and/or the second input portion; First output portion and the second output portion, the first output portion and the second output portion are arranged in parallel on electrical connectors, and the first output portion and/or the second output portion are electrically connected the temperature results after device processes for exporting.
Further, electric connector also includes: the first shielding part, and thermocouple connects cable by first and is connected electrically in the first input portion, and the first shielding part has the first shielding part being arranged on the first connection cable; Secondary shielding portion, thermocouple connects cable by second and is connected electrically in the second input portion, and secondary shielding portion has the secondary shielding part being arranged on the second connection cable.
Further, each thermocouple includes multiple temperature probe being arranged in parallel.
To achieve these goals, according to an aspect of the invention, it is provided a kind of whirlpool oar aero-engine, including discharge chamber, the cavity wall of discharge chamber being provided with temperature measuring equipment, temperature measuring equipment includes aforesaid temperature measuring equipment.
Further, circumferentially disposed along cavity wall of multiple thermocouples.
Further, temperature measuring equipment includes 8 thermocouples.
Further, 4 thermocouples are symmetrically disposed in cavity wall with other 4 thermocouples.
According to a further aspect in the invention, it is provided that a kind of thermometry, aforesaid temperature measuring equipment measures the temperature of aero-engine, comprises the following steps:
Step S1: the application thermocouple temperature measurement to the discharge gas of aero-engine;
Step S2: application electric connector receives the temperature signal that electroheat pair measurement obtains, and temperature signal is converted into the signal of telecommunication with output temperature measurement result.
Application technical scheme, by multiple thermocouples are connected in parallel by soft connection cable, overcome the shortcoming being connected in series in prior art, so that temperature measuring equipment works steadily in the long term, and improve temperature measuring equipment to thermometric accuracy.
Accompanying drawing explanation
The Figure of description constituting the part of the application is used for providing a further understanding of the present invention, and the schematic description and description of the present invention is used for explaining the present invention, is not intended that inappropriate limitation of the present invention. In the accompanying drawings:
Fig. 1 illustrates the structural representation of the embodiment of the temperature measuring equipment according to the present invention.
Wherein, above-mentioned accompanying drawing includes the following drawings labelling:
100, mounting box; 10, electric connector;
20, thermocouple; 21, temperature probe;
31, the first shielding part; 32, secondary shielding portion;
41, first connects cable; 42, second connects cable.
Detailed description of the invention
It should be noted that when not conflicting, the embodiment in the application and the feature in embodiment can be mutually combined. Describe the present invention below with reference to the accompanying drawings and in conjunction with the embodiments in detail.
As it is shown in figure 1, according to an aspect of the present invention, The embodiment provides a kind of temperature measuring equipment (in Fig. 1, Y represents the model of the electric connector 10 of this temperature measuring equipment).This temperature measuring equipment includes electric connector 10 and multiple overabundant heat thermocouple 20, and wherein, multiple thermocouples 20, for measuring the temperature of gas, are connected in parallel between multiple thermocouples 20, and are connected electrically on electric connector 10.
By multiple thermocouples are connected in parallel by soft connection cable, overcome in the form that the multiple thermocouple of the shortcoming being connected in series in prior art is connected in series, time the temperature probe of a thermocouple generation open circuit or thermocouple damages wherein, then whole temperature measuring equipment just can not the temperature data measured of ON operation or temperature measuring equipment inaccurate, so that temperature measuring equipment works steadily in the long term, and improve temperature measuring equipment to thermometric accuracy.
Referring again to shown in Fig. 1, electric connector 10 includes the first input portion, the second input portion, the first output portion A and the second output portion B. First input portion and the second input portion are arranged in parallel on electric connector 10, and the temperature data of multiple thermocouples 20 detection is delivered to electric connector 10 by the first input portion and/or the second input portion; First output portion A and the second output portion B is arranged in parallel on electric connector 10, and the first output portion A and/or the second output portion B is electrically connected the temperature results after device 10 processes for exporting. The positive wire in the first input portion is connected in the first positive terminal figure 1 above of electric connector shown in label 2, and the cathode conductor in the first input portion is connected in the first negative terminal figure 1 above of electric connector shown in label 3. In the same manner, the positive wire in the second input portion is connected in the second positive terminal figure 1 above of electric connector shown in label 4, and the cathode conductor in the second input portion is connected in the second negative terminal figure 1 above of electric connector shown in label 5. When the delivery temperature of whirlpool oar aero-engine is measured by temperature measuring equipment, the gas of discharge is carried out temperature detection by thermocouple 20, and temperature signal is delivered in electric connector and carries out signal conversion, after electric connector converts the temperature signal of input to the signal of telecommunication, the signal of telecommunication comprising temperature information is exported by electric connector by the first output portion A and/or the second output portion B. First output portion A and the second output portion B is owing to being arranged in parallel, when the first output portion A and the second output portion B connects work simultaneously time, thus the signal of telecommunication comprising temperature information of the first output portion A and the second output portion B output is essentially identical, then collects and be shown in same display instrument; Time as the first output portion A or the second output portion B, one of them breaks down and cannot be carried out normal output services, now, the second output portion B or the first output portion A just independent the output by the signal of telecommunication including temperature information remaining able to normal operation extremely shows in instrument. So, temperature measuring equipment be exactly achieve the output of double; two nargin utilize the first output portion A and the second output portion B realize output signal simultaneously or wherein an output portion fault time utilize another one intact output portion signal is continued to put out, to ensure the operation that works steadily in the long term of temperature measuring equipment.
Specifically, owing to space shuttle form is aerial at height, temperature measuring equipment is typically in high altitude environment to run work, thus it is easily subject to the interference of electromagnetic signal, in order to eliminate the electromagnetic signal interference to the signal of telecommunication of temperature measuring equipment, electric connector 10 also includes the first shielding part 31, secondary shielding portion 32. Thermocouple 20 is connected electrically in the first input portion by the first connection cable 41, and the first shielding part 31 has the first shielding part being arranged on the first connection cable 41;Thermocouple 20 is connected electrically in the second input portion by the second connection cable 42, and secondary shielding portion 32 has the secondary shielding part being arranged on the second connection cable 42. First shielding part 31 is connected on the first shielding binding post (in Fig. 1 shown in label 1) on electric connector 10, and secondary shielding portion 32 is connected on the secondary shielding binding post (in Fig. 1 shown in label 6) of electric connector 10.
Preferably, each thermocouple 20 includes multiple temperature probe 21 being arranged in parallel. Preferably, each thermocouple 20 is provided with two temperature probes 21 in parallel. Two temperature probes 21 in same thermocouple 20 adopt the form of parallel connection to install, so, even if a temperature probe 21 in thermocouple 20 damages, still the temperature probe 21 that another one is intact can be utilized to work on, ensure that temperature measuring equipment can normally run for a long time further.
According to another aspect of the present invention, the invention provides a kind of whirlpool oar aero-engine not shown, it includes discharge chamber, and the cavity wall of discharge chamber is provided with temperature measuring equipment, and this temperature measuring equipment includes aforesaid temperature measuring equipment.
Preferably, circumferentially disposed along cavity wall of multiple thermocouple 20. So, thermocouple 20 can carry out multi-faceted fixed point thermometric to discharging in discharge chamber gas, it is ensured that the accurate measurement to delivery temperature.
Temperature measuring equipment includes 8 thermocouples 20, and 4 in 8 thermocouples 20 with other 4 correspondingly and relative to discharge chamber axisymmetrical be arranged in cavity wall.
According to another aspect of the present invention, it is provided that a kind of thermometry, utilize aforesaid temperature measuring equipment to measure the temperature of aero-engine, comprise the following steps:
Step S1: the application thermocouple 20 temperature measurement to the discharge gas of aero-engine;
Step S2: application electric connector 10 receives thermocouple 20 and measures the temperature signal obtained, and temperature signal is converted into the signal of telecommunication with output temperature measurement result.
As can be seen from the above description, the above embodiments of the present invention achieve following technique effect:
Technical scheme makes temperature measuring equipment work steadily in the long term, and improves temperature measuring equipment to thermometric accuracy.
These are only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations. All within the spirit and principles in the present invention, any amendment of making, equivalent replacement, improvement etc., should be included within protection scope of the present invention.
Claims (8)
1. a temperature measuring equipment, is arranged in aero-engine, it is characterised in that including:
Electric connector (10);
Multiple thermocouples (20), for measuring the temperature of the discharge gas of described aero-engine, the plurality of thermocouple is connected in parallel between (20), and is connected electrically on described electric connector (10);
Described electric connector (10) includes the first input portion and the second input portion, described first input portion and described second input portion are arranged in parallel on described electric connector (10), and the temperature data that the plurality of thermocouple (20) detects is delivered to described electric connector (10) by described first input portion and/or described second input portion;
Described electric connector (10) also includes the first output portion A and the second output portion B, described first output portion A and described second output portion B is arranged in parallel on described electric connector (10), and described first output portion A and/or described second output portion B is for exporting the temperature results after described electric connector (10) processes;
The gas of discharge is carried out temperature detection by described thermocouple (20), and temperature signal is delivered in described electric connector (10) and carries out signal conversion, after described electric connector (10) converts the temperature signal of input to the signal of telecommunication, the signal of telecommunication comprising temperature information is exported by described electric connector (10) by described first output portion A and described second output portion B, when described first output portion A connects work with described second output portion B simultaneously time, the signal of telecommunication comprising temperature information that described first output portion A is identical with described second output portion B output, and collect and be shown in same display instrument.
2. temperature measuring equipment according to claim 1, it is characterised in that described electric connector (10) also includes:
First shielding part (31), described thermocouple (20) connects cable (41) by first and is connected electrically in described first input portion, and described first shielding part (31) has the first shielding part being arranged in described first connection cable (41);
Secondary shielding portion (32), described thermocouple (20) connects cable (42) by second and is connected electrically in described second input portion, and described secondary shielding portion (32) has the secondary shielding part being arranged in described second connection cable (42).
3. temperature measuring equipment according to claim 1 and 2, it is characterised in that each described thermocouple (20) includes two temperature probes being arranged side by side (21).
4. a whirlpool oar aero-engine, including discharge chamber, the cavity wall of described discharge chamber is provided with temperature measuring equipment, it is characterised in that described temperature measuring equipment includes the temperature measuring equipment according to any one of claims 1 to 3.
5. whirlpool according to claim 4 oar aero-engine, it is characterised in that circumferentially disposed along described cavity wall of the plurality of thermocouple (20).
6. whirlpool according to claim 5 oar aero-engine, it is characterised in that described temperature measuring equipment includes 8 described thermocouples (20).
7. whirlpool according to claim 6 oar aero-engine, it is characterised in that 4 described thermocouples (20) are arranged in described cavity wall correspondingly with other 4 each described thermocouples (20).
8. a thermometry, it is characterised in that utilize the temperature that the temperature measuring equipment according to any one of claim 1 to 3 measures aero-engine to comprise the following steps:
Step S1: utilize the described thermocouple (20) temperature of exhaust gas to described aero-engine;
Step S2: utilize described electric connector (10) to receive described thermocouple (20) and measure the temperature signal obtained, and temperature signal is converted into the signal of telecommunication with output temperature measurement result.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410626150.3A CN104481608B (en) | 2014-11-07 | 2014-11-07 | Temperature measuring equipment, whirlpool oar aero-engine and thermometry |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410626150.3A CN104481608B (en) | 2014-11-07 | 2014-11-07 | Temperature measuring equipment, whirlpool oar aero-engine and thermometry |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104481608A CN104481608A (en) | 2015-04-01 |
| CN104481608B true CN104481608B (en) | 2016-06-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410626150.3A Active CN104481608B (en) | 2014-11-07 | 2014-11-07 | Temperature measuring equipment, whirlpool oar aero-engine and thermometry |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3063343B1 (en) * | 2017-02-28 | 2019-06-07 | Safran Helicopter Engines | THERMOMETRIC MEASUREMENT BY MESHING PROBES, IN PARTICULAR WITHIN TURBOMACHINES |
| CN108955919A (en) * | 2018-09-20 | 2018-12-07 | 天津德尔泰热控系统有限公司 | A kind of novel fire resistant armoured thermocouple |
| CN109341873B (en) * | 2018-12-14 | 2020-12-04 | 中国航发沈阳发动机研究所 | Temperature probe |
| CN110132441A (en) * | 2019-05-31 | 2019-08-16 | 中国航发南方工业有限公司 | Redundance armoured thermocouple device and design method |
| CN110398296A (en) * | 2019-07-31 | 2019-11-01 | 中国人民解放军海军工程大学 | A kind of engine exhaust temperature cruising inspection system based on ModbusTCP/IP |
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| CN202851147U (en) * | 2012-08-09 | 2013-04-03 | 中国南方航空工业(集团)有限公司 | Wiring board assembly |
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| CN202851147U (en) * | 2012-08-09 | 2013-04-03 | 中国南方航空工业(集团)有限公司 | Wiring board assembly |
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| CN104481608A (en) | 2015-04-01 |
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Address after: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee after: China Hangfa South Industrial Co. Ltd. Address before: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee before: China Southern Airlines Industry (Group) Co., Ltd. |