CN201908725U - Measuring device for total pressure and total temperature of inlet airflow of aircraft engine - Google Patents
Measuring device for total pressure and total temperature of inlet airflow of aircraft engine Download PDFInfo
- Publication number
- CN201908725U CN201908725U CN2011200005384U CN201120000538U CN201908725U CN 201908725 U CN201908725 U CN 201908725U CN 2011200005384 U CN2011200005384 U CN 2011200005384U CN 201120000538 U CN201120000538 U CN 201120000538U CN 201908725 U CN201908725 U CN 201908725U
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- stagnation
- temperature
- measuring device
- pipe
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Abstract
The utility model discloses a measuring device for the total pressure and the total temperature of an inlet airflow of an aircraft engine, which is characterized by consisting of a fixed seat, a fixing nut, a total pressure pipe, a total temperature pipe and a pressure sensor. The total temperature pipe and the total pressure pipe are connected in a threaded manner, the total pressure pipe is connected with the fixed seat in a threaded manner, the fixed seat is fixed at the front edge of a diversion strut on an inlet casing of the engine by the aid of the fixing nut through the threads on the fixed seat, the pressure sensor is connected with an inner threaded hole on the fixed seat through a joint, a precise temperature sensing resistor is mounted in the total temperature pipe, and a flow limiter is mounted in a suction pipe joint on the fixed seat and used for regulating the volume of air led from an air compressor. The measuring device not only realizes measuring the total pressure and the total temperature of the inlet airflow of the aircraft engine, but prevents a passage from being iced due to stagnation of airflow in the total pressure pipe in the air by means of utilizing hot air after the air compressor is introduced.
Description
Technical field
The utility model 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 utility model 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.
The model utility content
The purpose of this utility model 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 utility model is taked 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 utility model stagnation pressure stagnation temperature, its advantage and effect are:
1, simple in structure, 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, the method for 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 the utility model device.
Figure 2 shows that the partial enlarged drawing of A part among Fig. 1.
Figure 3 shows that the utility model Unit Installation position view.
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 utility model, 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; The restrictor that is used for regulating the air tolerance of introducing behind the gas compressor is housed in the air entraining pipe joint on the fixed base.
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 |
|---|---|---|---|
| CN2011200005384U CN201908725U (en) | 2011-01-04 | 2011-01-04 | Measuring device for total pressure and total temperature of inlet airflow of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011200005384U CN201908725U (en) | 2011-01-04 | 2011-01-04 | Measuring device for total pressure and total temperature of inlet airflow of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201908725U true CN201908725U (en) | 2011-07-27 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011200005384U Expired - Fee Related CN201908725U (en) | 2011-01-04 | 2011-01-04 | Measuring device for total pressure and total temperature of inlet airflow of aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201908725U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102094711A (en) * | 2011-01-04 | 2011-06-15 | 北京航空航天大学 | Device for measuring total pressure and total temperature of air flow at inlet of aeromotor |
| CN102350564A (en) * | 2011-09-05 | 2012-02-15 | 沈阳黎明航空发动机(集团)有限责任公司 | Argon arc welding method for inlet casing gas-collecting hood having lock bottom welding joint |
| 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 |
| CN104848963A (en) * | 2013-09-05 | 2015-08-19 | 罗斯蒙特航天公司 | Supercritical total air temperature sensors |
| CN110595668A (en) * | 2019-09-17 | 2019-12-20 | 中国航发沈阳发动机研究所 | Engine performance test piece machine casket inner chamber measurement structure |
-
2011
- 2011-01-04 CN CN2011200005384U patent/CN201908725U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102094711A (en) * | 2011-01-04 | 2011-06-15 | 北京航空航天大学 | Device for measuring total pressure and total temperature of air flow at inlet of aeromotor |
| CN102350564A (en) * | 2011-09-05 | 2012-02-15 | 沈阳黎明航空发动机(集团)有限责任公司 | Argon arc welding method for inlet casing gas-collecting hood having lock bottom welding joint |
| CN104848963A (en) * | 2013-09-05 | 2015-08-19 | 罗斯蒙特航天公司 | Supercritical total air temperature sensors |
| CN104848963B (en) * | 2013-09-05 | 2018-03-30 | 罗斯蒙特航天公司 | Overcritical total air temperature sensor |
| 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 |
| 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 |
| CN110595668A (en) * | 2019-09-17 | 2019-12-20 | 中国航发沈阳发动机研究所 | Engine performance test piece machine casket inner chamber measurement structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110727 Termination date: 20140104 |