CN102094711A - Device for measuring total pressure and total temperature of air flow at inlet of aeromotor - Google Patents
Device for measuring total pressure and total temperature of air flow at inlet of aeromotor Download PDFInfo
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- CN102094711A CN102094711A CN2011100003171A CN201110000317A CN102094711A CN 102094711 A CN102094711 A CN 102094711A CN 2011100003171 A CN2011100003171 A CN 2011100003171A CN 201110000317 A CN201110000317 A CN 201110000317A CN 102094711 A CN102094711 A CN 102094711A
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Abstract
The invention discloses a device for measuring the total pressure and total temperature of air flow at an inlet of an aeromotor. The device provided by the invention is characterized by consisting of a fixed seat, a fixed nut, a total pressure tube, a total temperature tube and a pressure sensor, wherein the total temperature tube is connected with the total pressure tube through screw threads, the total pressure tube is connected with the fixed seat through threads, the fixed seat is fixed at the front edge of a rectifying support column on the inlet casing of the motor through the threads on the fixed seat by the fixed nut, and the pressure sensor is connected with an inner screw thread hole on the fixed seat through an adapter; the total temperature tube is internally provided with a precise temperature sensitive resistor; and an air-bleed tube adapter on the fixed seat 1 is provided with a flow limiter which is used for regulating the air flow introduced from the rear part of a compressor. According to the invention, not only can the measurement of the total pressure and total temperature of air flow at the inlet of a motor be realized, but also the total pressure tube can be prevented from air flow stagnation and the passageway can be prevented from being frozen.
Description
Technical field
The present invention is a kind of measuring device of aeroengine inlet air flow stagnation pressure stagnation temperature.Thereby the measurement of engine intake place stagnation temperature and stagnation pressure helped the situation of the charge air flow of motor monitored accurately controls the engine oil amount accurately.The invention belongs to the aeroengine technical field of measurement and test.
Background technique
Along with development of Aeroengines, controlling level to motor is improving constantly, how motor is controlled accurately and seemed more important, accurately the prerequisite of control is to measure accurately and real-time, will be accurately measurement result in time feed back to control system and could carry out effectively control motor, and the stagnation temperature in the same cross section of air-flow, engine intake place and stagnation pressure directly have influence on the working state of motor.As the main aerodynamic parameter in engine intake cross section, its significance is well imagined, and is apparent to its significance of accurately measuring.Aeroengine in the past can't realize regulating according to the conversion of engine intake air-flow the function of control parameters of engine owing to do not adopt full powers limit digital controller, and therefore the stagnation temperature total-pressure probe is not installed at the engine intake place yet.
Summary of the invention
The object of the present invention is to provide a kind of measuring device of aeroengine inlet air flow stagnation pressure stagnation temperature, to solve aeroengine inlet air-flow stagnation pressure, total temperature measurement problem.
For achieving the above object, the present invention takes following design proposal: a kind of measuring device of aeroengine inlet air flow stagnation pressure stagnation temperature is characterized in that: it by fixed base 1, set screw nut 2, stagnation pressure tube 3, stagnation temperature pipe 4, pressure transducer 5, form.Its structural representation such as Fig. 1.
Stagnation temperature pipe 4 and stagnation pressure tube 3 are by being threaded, stagnation pressure tube links together by screw thread and fixed base 1, set screw nut 2 is fixed on rectification pillar leading edge on the engine charge casing to fixed base by the screw thread on the fixed base 1, and pressure transducer 5 is connected with interior threaded hole on the fixed base 1 by joint.Accurate temperature sensitive resister 7 is housed in the stagnation temperature pipe 4 is A level pt100 platinum resistor.In the air entraining pipe joint 8 on the fixed base 1 restrictor 9 is housed, is used for regulating the air tolerance of introducing behind the gas compressor.
Described temperature sensitive resister is an A level pt100 platinum resistor.
The measuring device of described aeroengine inlet air flow stagnation pressure stagnation temperature is the leading edge that is fixedly mounted on the upper left rectification pillar in suitable course on the engine charge casing by set screw nut.
The measuring device of a kind of aeroengine inlet air flow of the present invention stagnation pressure stagnation temperature, its advantage and effect are: (1) is simple in structure, and process aspect is realized easily.(2) realize measurement by the pressure, the temperature transducer that are installed on this device to the same section stagnation pressure of aeroengine inlet air flow stagnation temperature.(3) method of hot air behind the employing introducing gas compressor has solved under the aerial cryogenic conditions problem that stagnation pressure tube diffusion passage freezes.
Description of drawings
Figure 1 shows that the structural representation of apparatus of the present invention.
Figure 2 shows that the partial enlarged drawing of A part among Fig. 1.
Figure 3 shows that the mounting point schematic representation of apparatus of the present invention.
Concrete label is as follows among the figure:
1, fixed base; 2, set screw nut; 3, stagnation pressure tube; 4, stagnation temperature pipe; 5, pressure transducer;
6, inlet hole; 7, temperature sensitive resister; 8, air entraining pipe joint; 9, restrictor; 10, engine intake air-flow; 11, anti-icing air-flow; 12, stagnation pressure tube diffusion passage; 13, anti-icing air-flow path.
Embodiment
The total temperature measurement integrated device of a kind of aeroengine import stagnation pressure of the present invention, structure be as shown in Figure 1, 2: be made up of fixed base 1, set screw nut 2, stagnation pressure tube 3, stagnation temperature pipe 4, pressure transducer 5.Engine intake air-flow 10 enters stagnation pressure tube diffusion passage 12, measures stagnation pressure by pipeline by pressure transducer; Air-flow on the same cross section of engine intake, enter stagnation in the stagnation temperature pipe by the inlet hole on the stagnation temperature pipe 4, by the temperature sensitive resister 7(pt100 platinum resistor in the stagnation temperature pipe) measurement air-flow stagnation temperature, the signal that pressure transducer 5 and temperature sensitive resister 7 record directly is sent to the numerical control system of motor, thereby realizes the measurement to engine intake air-flow stagnation pressure stagnation temperature.By the air entraining pipe joint 8 on the fixed base 1 hot air behind the gas compressor is incorporated in the stagnation pressure tube 3 simultaneously, has effectively prevented the problem that stagnation pressure tube diffusion passage 12 freezes under the cryogenic conditions aloft; Restrictor 9 in the air entraining pipe joint can be adjusted the size of bleed tolerance.Aeroengine import stagnation pressure stagnation temperature measuring device is fixedly installed in the leading edge of engine charge casing superinverse course upper left side rectification pillar by set screw nut, need guarantee during installation that stagnation pressure tube diffusion passage axis comes flow path direction over against air, angular error is ± 3 °, as shown in Figure 3.
Claims (3)
1. the measuring device of an aeroengine inlet air flow stagnation pressure stagnation temperature, it is characterized in that: it is made up of fixed base, set screw nut, stagnation pressure tube, stagnation temperature pipe, pressure transducer: stagnation temperature pipe and stagnation pressure tube are by being threaded, stagnation pressure tube links together by screw thread and fixed base, set screw nut is fixed on rectification pillar leading edge on the engine charge casing to fixed base by the screw thread on the fixed base, and pressure transducer is connected with interior threaded hole on the fixed base by joint; Accurate temperature sensitive resister is housed in the stagnation temperature pipe; In the air entraining pipe joint on the fixed base restrictor is housed, is used for regulating the air tolerance of introducing behind the gas compressor.
2. the measuring device of aeroengine inlet air flow stagnation pressure stagnation temperature according to claim 1 is characterized in that: described temperature sensitive resister is an A level pt100 platinum resistor.
3. the measuring device of aeroengine inlet air flow stagnation pressure stagnation temperature according to claim 1 is characterized in that: the measuring device of described aeroengine inlet air flow stagnation pressure stagnation temperature is the leading edge that is fixedly mounted on the upper left rectification pillar in suitable course on the engine charge casing by set screw nut.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100003171A CN102094711A (en) | 2011-01-04 | 2011-01-04 | Device for measuring total pressure and total temperature of air flow at inlet of aeromotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100003171A CN102094711A (en) | 2011-01-04 | 2011-01-04 | Device for measuring total pressure and total temperature of air flow at inlet of aeromotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102094711A true CN102094711A (en) | 2011-06-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2011100003171A Pending CN102094711A (en) | 2011-01-04 | 2011-01-04 | Device for measuring total pressure and total temperature of air flow at inlet of aeromotor |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103323051A (en) * | 2013-05-13 | 2013-09-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Compound feeling component used for aircraft engine performance test |
| CN104034532A (en) * | 2014-06-09 | 2014-09-10 | 中国航空工业集团公司沈阳发动机设计研究所 | Total temperature and total pressure wing-shaped sensing part |
| CN105143611A (en) * | 2013-03-20 | 2015-12-09 | 西门子股份公司 | Gas turbine and method for operating the gas turbine |
| CN105319069A (en) * | 2015-11-17 | 2016-02-10 | 中国空空导弹研究院 | A solid ramjet engine afterburning chamber total pressure test device and a total pressure tube thereof |
| CN105571765A (en) * | 2015-12-15 | 2016-05-11 | 长春航空液压控制有限公司 | Single point pressure measuring device with anti-icing function |
| CN110735672A (en) * | 2019-10-11 | 2020-01-31 | 中国航发沈阳发动机研究所 | shunt ring and intermediate casing sector section structure with same |
| CN113804449A (en) * | 2020-06-17 | 2021-12-17 | 中国航发商用航空发动机有限责任公司 | Total temperature detection device and aeroengine |
| CN114371013A (en) * | 2022-01-06 | 2022-04-19 | 中国航发贵阳发动机设计研究所 | Air test pipeline of aircraft engine |
| CN115356113A (en) * | 2022-09-01 | 2022-11-18 | 中国科学院工程热物理研究所 | Device for measuring outlet temperature and pressure of gas compressor in engine |
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| CN201908725U (en) * | 2011-01-04 | 2011-07-27 | 北京航空航天大学 | Measuring device for total pressure and total temperature of inlet airflow of aircraft engine |
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| US3343417A (en) * | 1965-04-12 | 1967-09-26 | United Aircraft Corp | Temperature and pressure probe |
| US4403872A (en) * | 1979-11-05 | 1983-09-13 | Rosemount Inc. | Flow device for sensors |
| US5353628A (en) * | 1991-07-26 | 1994-10-11 | Westinghouse Electric Corporation | Steam purity monitor |
| CN1330766A (en) * | 1998-10-20 | 2002-01-09 | 航空电子特制品有限公司 | Aircraft probe with integral air temp. sensor |
| US6490510B1 (en) * | 1999-04-30 | 2002-12-03 | Thales Avionics S.A. | Fixed multifunction probe for aircraft |
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| CN1662796A (en) * | 2002-06-14 | 2005-08-31 | 奥谢陶尔公司 | De-iced total air temperature sensor |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105143611A (en) * | 2013-03-20 | 2015-12-09 | 西门子股份公司 | Gas turbine and method for operating the gas turbine |
| US9915166B2 (en) | 2013-03-20 | 2018-03-13 | Siemens Aktiengesellschaft | Gas turbine and method for operating the gas turbine |
| CN103323051A (en) * | 2013-05-13 | 2013-09-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Compound feeling component used for aircraft engine performance test |
| CN104034532B (en) * | 2014-06-09 | 2016-06-08 | 中国航空工业集团公司沈阳发动机设计研究所 | Total temperature wing detector probe of total pressure |
| CN104034532A (en) * | 2014-06-09 | 2014-09-10 | 中国航空工业集团公司沈阳发动机设计研究所 | Total temperature and total pressure wing-shaped sensing part |
| CN105319069A (en) * | 2015-11-17 | 2016-02-10 | 中国空空导弹研究院 | A solid ramjet engine afterburning chamber total pressure test device and a total pressure tube thereof |
| CN105571765A (en) * | 2015-12-15 | 2016-05-11 | 长春航空液压控制有限公司 | Single point pressure measuring device with anti-icing function |
| CN110735672A (en) * | 2019-10-11 | 2020-01-31 | 中国航发沈阳发动机研究所 | shunt ring and intermediate casing sector section structure with same |
| CN113804449A (en) * | 2020-06-17 | 2021-12-17 | 中国航发商用航空发动机有限责任公司 | Total temperature detection device and aeroengine |
| CN113804449B (en) * | 2020-06-17 | 2024-03-26 | 中国航发商用航空发动机有限责任公司 | Total temperature detection device and aeroengine |
| CN114371013A (en) * | 2022-01-06 | 2022-04-19 | 中国航发贵阳发动机设计研究所 | Air test pipeline of aircraft engine |
| CN114371013B (en) * | 2022-01-06 | 2024-03-19 | 中国航发贵阳发动机设计研究所 | Aeroengine air test pipeline |
| CN115356113A (en) * | 2022-09-01 | 2022-11-18 | 中国科学院工程热物理研究所 | Device for measuring outlet temperature and pressure of gas compressor in engine |
| CN115356113B (en) * | 2022-09-01 | 2024-04-19 | 中国科学院工程热物理研究所 | Device for measuring outlet temperature and pressure of air compressor in engine |
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Application publication date: 20110615 |