CN111947830A - High-temperature dynamic pressure probe structure of main combustion chamber of aircraft engine - Google Patents
High-temperature dynamic pressure probe structure of main combustion chamber of aircraft engine Download PDFInfo
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- CN111947830A CN111947830A CN202010754444.XA CN202010754444A CN111947830A CN 111947830 A CN111947830 A CN 111947830A CN 202010754444 A CN202010754444 A CN 202010754444A CN 111947830 A CN111947830 A CN 111947830A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L23/00—Devices or apparatus for measuring or indicating or recording rapid changes, such as oscillations, in the pressure of steam, gas, or liquid; Indicators for determining work or energy of steam, internal-combustion, or other fluid-pressure engines from the condition of the working fluid
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L23/00—Devices or apparatus for measuring or indicating or recording rapid changes, such as oscillations, in the pressure of steam, gas, or liquid; Indicators for determining work or energy of steam, internal-combustion, or other fluid-pressure engines from the condition of the working fluid
- G01L23/26—Details or accessories
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L23/00—Devices or apparatus for measuring or indicating or recording rapid changes, such as oscillations, in the pressure of steam, gas, or liquid; Indicators for determining work or energy of steam, internal-combustion, or other fluid-pressure engines from the condition of the working fluid
- G01L23/26—Details or accessories
- G01L23/28—Cooling means
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- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measuring Fluid Pressure (AREA)
Abstract
The invention belongs to the technical field of aeroengine measuring devices, and discloses a high-temperature dynamic pressure probe structure of a main combustion chamber of an aeroengine, which comprises a pressure guiding device, a probe shell, a high-temperature dynamic pressure sensor and a semi-infinite long pipe, wherein the pressure guiding device is connected with one end of the probe shell, the semi-infinite long pipe is connected with the other end of the probe shell, and the high-temperature dynamic pressure sensor is arranged in the probe shell; the probe shell comprises a pressure guiding pipe, a cooling device and a sensor mounting seat, one end of the pressure guiding pipe is connected with the pressure guiding device, the cooling device cools the pressure guiding pipe, the other end of the pressure guiding pipe is connected with the sensor mounting seat, a high-temperature dynamic pressure sensor is arranged in the sensor mounting seat, and the other end of the sensor mounting seat is connected with a semi-infinite long pipe. The high-temperature dynamic pressure probe structure of the main combustion chamber of the aero-engine can reliably measure the pulsating static pressure in the combustion chamber of the aero-engine for a long time, and the amplitude-frequency characteristic of a measured signal is good.
Description
Technical Field
The invention belongs to the technical field of aeroengine measuring devices, relates to a pressure detection structure for an aeroengine, and particularly relates to a high-temperature dynamic pressure probe structure for a main combustion chamber of the aeroengine.
Background
With the technical development of the advanced combustion chamber part, the combustion chamber part is gradually optimized in design and test, the internal combustion pulsation condition of the combustion chamber is reliably mastered in the debugging and testing processes of the combustion chamber part, and the method has important significance for the performance test of the main combustion chamber.
Due to the high-temperature and high-pressure working environment in the combustion chamber, the conventional dynamic pressure sensor cannot directly measure the high-temperature dynamic pressure. At present, high-temperature gas in a combustion chamber is mainly led out through a longer pressure leading pipe in China and then is measured, and the measuring method has the defects that the dynamic pressure measuring frequency range is small (within 300 Hz), and the measured dynamic pressure measuring error is large due to the fact that the amplitude ratio and the frequency response characteristic are poor.
For high-temperature dynamic pressure inside the combustion chamber, an accurate and reliable probe structure is required in actual measurement to realize dynamic pressure front-end measurement.
CN201310112329.2 discloses a dynamic total pressure probe, which aims to measure the dynamic total pressure of the unsteady airflow of a gas turbine and comprises a kirl fairing, a rigid pressure guiding pipe, a dynamic pressure sensor support and a semi-infinite-length flexible pressure guiding pipe. The dynamic total pressure probe designed by the patent can not measure high-temperature dynamic airflow (1000 ℃).
Disclosure of Invention
In order to solve the problems, the invention provides a high-temperature dynamic pressure probe structure of a main combustion chamber of an aero-engine, which realizes the monitoring of internal combustion pulsation of the combustion chamber of the aero-engine, and has the following use working conditions: temperature 1273K and pressure 1000 kPa.
The technical scheme of the invention is as follows:
a high-temperature dynamic pressure probe structure of a main combustion chamber of an aircraft engine comprises a pressure guiding device, a probe shell, a high-temperature dynamic pressure sensor and a semi-infinite tube, wherein the pressure guiding device is connected with one end of the probe shell, the semi-infinite tube is connected with the other end of the probe shell, and the high-temperature dynamic pressure sensor is arranged in the probe shell; the probe shell comprises a pressure guiding pipe, a cooling device and a sensor mounting seat, one end of the pressure guiding pipe is connected with the pressure guiding device, the cooling device cools the pressure guiding pipe, the other end of the pressure guiding pipe is connected with the sensor mounting seat, a high-temperature dynamic pressure sensor is arranged in the sensor mounting seat, and the other end of the sensor mounting seat is connected with a semi-infinite long pipe.
Further, the pressure guiding device determines that the distance between a measuring point of the pulsating pressure and the high-temperature dynamic pressure sensor is less than 150 mm.
Further, the distance between the measuring point of the pulsating pressure and the high-temperature dynamic pressure sensor is determined by the pressure guiding device to be 120mm to 150 mm. This range has a good amplitude ratio and frequency response for dynamic pressure signals in the 1500Hz range.
Further, cooling device is including advancing pipe, sleeve pipe and exit tube, and the sleeve pipe cover has the cavity between the pipe is pressed in the drainage to the sleeve pipe outside, sleeve pipe and drainage, and the sleeve pipe is connected respectively and is advanced pipe and exit tube, and cooling medium gets into in the sleeve pipe through advancing the pipe, cools off the interior gas of drainage, then discharges through the exit tube.
Further, the inlet flow pressure of the cooling medium was 200 kPa. The inlet temperature of the common fuel gas is 1250K, and researches show that the cooling effect is obvious when cooling medium of 200kPa is adopted to cool the high-temperature fuel gas.
Furthermore, the cooling medium is cooling water, the inlet pipe is a water inlet pipe, the outlet pipe is a water outlet pipe of the outlet pipe, and the sleeve is a cooling water jacket.
Furthermore, the cooling medium is cooling gas, the inlet pipe is an air inlet pipe, the outlet pipe is an air outlet pipe, and the sleeve is a cooling gas sleeve.
Furthermore, a gas pipeline for connecting the pressure leading pipe and the semi-infinite pipe is arranged in the sensor mounting seat, a long through hole is formed above the middle of the gas pipeline, and the high-temperature dynamic pressure sensor is inserted into the long through hole.
Furthermore, the shell of the pressure guiding device has the same structural form as the ignition electric nozzle of the combustion chamber. Therefore, the combustion chamber can be installed by using the structure of the combustion chamber, no additional measuring point is needed to be designed, and the measuring effect of the position is the best.
The invention has the advantages that: the high-temperature dynamic pressure probe structure of the main combustion chamber of the aero-engine can reliably measure the pulsating static pressure in the combustion chamber of the aero-engine for a long time, and the amplitude-frequency characteristic of a measured signal is good.
Drawings
FIG. 1 is a schematic diagram of a high temperature dynamic pressure measurement system of an embodiment of the present invention;
FIG. 2 is a schematic view of a high temperature dynamic pressure probe installation;
FIG. 3 is a diagram of the positions of monitoring points of a gas leading-out section;
FIG. 4 is a graph of temperature versus time at three stations under 200kPa cooling water pressure;
the device comprises a pressure guide device 1, a probe shell 2, a pressure guide pipe 2-1, a cooling device 2-2, a sensor mounting seat 2-3, a high-temperature dynamic pressure sensor 3, a semi-infinite pipe 4, a device 5 and a measuring point 6.
Detailed Description
This section is an example of the present invention and is provided to explain and illustrate the technical solutions of the present invention.
The invention relates to a high-temperature dynamic pressure probe structure of a main combustion chamber of an aircraft engine, which comprises a pressure guiding device 1, a probe shell 2, a high-temperature dynamic pressure sensor 3 and a semi-infinite long tube 4, wherein the pressure guiding device 1 is connected with one end of the probe shell 2, the semi-infinite long tube 4 is connected with the other end of the probe shell 2, and the high-temperature dynamic pressure sensor 3 is arranged in the probe shell 2; the probe shell comprises a pressure guiding pipe 2-1, a cooling device 2-2 and a sensor mounting seat 2-3, one end of the pressure guiding pipe 2-1 is connected with the pressure guiding device 1, the cooling device 2-2 cools the pressure guiding pipe 2-1, the other end of the pressure guiding pipe 2-1 is connected with the sensor mounting seat 2-3, a high-temperature dynamic pressure sensor 3 is arranged in the sensor mounting seat 2-3, and the other end of the sensor mounting seat 2-3 is connected with a semi-infinite long pipe 4.
Wherein, the distance from the measuring point of the pulsating pressure determined by the pressure guiding device 1 to the high-temperature dynamic pressure sensor 3 is less than 150mm, and the most suitable distance is 120mm to 150 mm. This range possesses a good amplitude ratio and frequency response characteristic for dynamic pressure signals (in the 1500Hz range).
The cooling device 2-2 comprises an inlet pipe, a sleeve pipe and an outlet pipe, the sleeve pipe is sleeved outside the pressure guiding pipe 2-1, a cavity is arranged between the sleeve pipe and the pressure guiding pipe 2-1, the sleeve pipe is respectively connected with the inlet pipe and the outlet pipe, a cooling medium enters the sleeve pipe through the inlet pipe, cools the fuel gas in the pressure guiding pipe 2-1, and then is discharged through the outlet pipe.
The inlet flow pressure of the cooling medium was 200 kPa. The inlet temperature of the common fuel gas is 1250K, and researches show that the cooling effect is obvious when cooling medium of 200kPa is adopted to cool the high-temperature fuel gas.
The cooling medium can be cooling water, the corresponding inlet pipe is a water inlet pipe, the corresponding outlet pipe is a water outlet pipe, and the sleeve is a cooling water jacket; the cooling medium can also be cooling gas, the corresponding inlet pipe is an air inlet pipe, the corresponding outlet pipe is an air outlet pipe, and the sleeve is a cooling gas sleeve.
A gas pipeline for connecting the pressure leading pipe 2-1 and the semi-infinite pipe 4 is arranged in the sensor mounting seat 2-3, a long through hole is arranged above the middle part of the gas pipeline, and the high-temperature dynamic pressure sensor 3 is inserted in the long through hole.
The shell of the pressure guide device 1 has the same structural form as the ignition nozzle of the combustion chamber. Therefore, the combustion chamber can be installed by using the structure of the combustion chamber, no additional measuring point is needed to be designed, and the measuring effect of the position is the best.
Another embodiment of the present invention is described below with reference to the drawings.
The structure of the high-temperature dynamic pressure probe is shown in figure 1, the dynamic pressure probe adopts a semi-infinite long pipe form, the semi-infinite long pipe can effectively eliminate standing waves, the amplitude-frequency characteristic of signals is obviously improved, and the high-temperature dynamic pressure probe can be used for long-time reliable measurement of high-frequency dynamic pressure in a high-temperature environment through a cooling structure.
The probe comprises a pressure guiding device 1, a pressure guiding pipe 2-1, a probe shell 2, a high-temperature dynamic pressure sensor 3, a semi-infinite pipe 4 and the like. Through simulation calculation and dynamic pressure blowing calibration, the distance L between a pulsating pressure measuring point and a dynamic pressure sensor is determined to be within 150mm, and the dynamic pressure sensor has a good amplitude ratio and frequency response characteristic to a dynamic pressure signal (within 1500 Hz).
The cooling medium of this embodiment adopts the form of water, and from the experimental result, the water cooling effect can reach the design requirement.
The high temperature pulsating pressure probe leads the combustion chamber inner wall surface static pressure out from the combustion chamber ignition device, see fig. 2. After the temperature of the high-temperature gas is reduced to a temperature range which can be measured by a high-frequency-response dynamic pressure sensor through the cooling water jacket (according to simulation of a simulation test, the actual effect of the cooling water jacket is determined to be capable of effectively reducing the high-temperature gas to the working range of the dynamic sensor), the high-temperature gas is sent to the dynamic pressure sensor and a semi-infinite long pipe measuring system at the rear part of the dynamic pressure sensor. And carrying out spectrum analysis on the dynamic pressure signal through a high-speed data acquisition system to realize real-time monitoring on combustion pulsation in the combustion chamber.
Referring to fig. 3-4, fig. 3 shows the position of 5 measuring points in the outlet pipe section for calculation and monitoring. The distance between the measuring point 3 and the water jacket outlet is 1cm, the distance between the measuring point 4 and the water jacket outlet is 2cm, and the distance between the measuring point 5 and the water jacket outlet is 3 cm. As can be seen from the simulation calculation in FIG. 4, when the inlet gas temperature is 1250K and the cooling water inlet water pressure is 200kPa, the cooling effect of the cooling water jacket on the high-temperature gas is remarkable.
The structural design principle is as follows: high-temperature fuel gas is led out from the combustion chamber through the pressure leading device and the pressure leading pipe, the fuel gas is pre-cooled through the cooling water jacket of the probe shell, and the temperature of the fuel gas is reduced to the working temperature of the dynamic pressure sensor and then reaches the measuring end of the sensor and the semi-infinite long pipe system (the semi-infinite long non-resonant pipe cavity eliminates the standing wave amplitude-frequency characteristic and is obviously improved).
The dynamic pressure probe blow calibration data is shown in the following table:
calibration data results at different pressure tube lumen lengths
Claims (9)
1. A high-temperature dynamic pressure probe structure of a main combustion chamber of an aircraft engine is characterized by comprising a pressure guiding device (1), a probe shell (2), a high-temperature dynamic pressure sensor (3) and a semi-infinite tube (4), wherein the pressure guiding device (1) is connected with one end of the probe shell (2), the semi-infinite tube (4) is connected with the other end of the probe shell (2), and the high-temperature dynamic pressure sensor (3) is arranged in the probe shell (2); the probe shell comprises a pressure guiding pipe (2-1), a cooling device (2-2) and a sensor mounting seat (2-3), one end of the pressure guiding pipe (2-1) is connected with the pressure guiding device (1), the cooling device (2-2) cools the pressure guiding pipe (2-1), the other end of the pressure guiding pipe (2-1) is connected with the sensor mounting seat (2-3), a high-temperature dynamic pressure sensor (3) is arranged in the sensor mounting seat (2-3), and the other end of the sensor mounting seat (2-3) is connected with a semi-infinite long pipe (4).
2. The high-temperature dynamic pressure probe structure of the main combustion chamber of the aircraft engine as claimed in claim 1, characterized in that the distance from the pressure-inducing device (1) to the high-temperature dynamic pressure sensor (3) for determining the pulsating pressure is less than 150 mm.
3. The high-temperature dynamic pressure probe structure of the main combustion chamber of the aircraft engine as claimed in claim 2, characterized in that the distance from the pressure-inducing device (1) to the high-temperature dynamic pressure sensor (3) for determining the pulsating pressure is 120mm to 150 mm.
4. The high-temperature dynamic pressure probe structure of the main combustion chamber of the aircraft engine as claimed in claim 1, wherein the cooling device (2-2) comprises an inlet pipe, a sleeve and an outlet pipe, the sleeve is sleeved outside the pressure guiding pipe (2-1), a cavity is formed between the sleeve and the pressure guiding pipe (2-1), the sleeve is respectively connected with the inlet pipe and the outlet pipe, a cooling medium enters the sleeve through the inlet pipe, cools the fuel gas in the pressure guiding pipe (2-1), and then is discharged through the outlet pipe.
5. The high temperature dynamic pressure probe structure for a main combustion chamber of an aircraft engine as claimed in claim 4, wherein the inlet flow pressure of the cooling medium is 200 kPa.
6. The high temperature dynamic pressure probe structure of aircraft engine main combustion chamber as claimed in claim 5, wherein the cooling medium is cooling water, the inlet pipe is a water inlet pipe, the outlet pipe is a water outlet pipe, and the sleeve is a cooling water jacket.
7. The high temperature dynamic pressure probe structure of main combustion chamber of aircraft engine as claimed in claim 5, wherein the cooling medium is cooling air, the inlet tube is an air inlet tube, the outlet tube is an air outlet tube, and the sleeve is a cooling air jacket.
8. The high-temperature dynamic pressure probe structure of the main combustion chamber of the aircraft engine as claimed in claim 1, wherein a gas pipeline connecting the pressure guiding pipe (2-1) and the semi-infinite long pipe (4) is arranged in the sensor mounting seat (2-3), a long through hole is arranged above the middle part of the gas pipeline, and the high-temperature dynamic pressure sensor (3) is inserted into the long through hole.
9. The high-temperature dynamic pressure probe structure for the main combustion chamber of an aircraft engine as claimed in claim 1, characterized in that the housing of the pressure-inducing device (1) is the same as the ignition nozzle of the combustion chamber.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010754444.XA CN111947830A (en) | 2020-07-31 | 2020-07-31 | High-temperature dynamic pressure probe structure of main combustion chamber of aircraft engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010754444.XA CN111947830A (en) | 2020-07-31 | 2020-07-31 | High-temperature dynamic pressure probe structure of main combustion chamber of aircraft engine |
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| CN111947830A true CN111947830A (en) | 2020-11-17 |
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| CN202010754444.XA Pending CN111947830A (en) | 2020-07-31 | 2020-07-31 | High-temperature dynamic pressure probe structure of main combustion chamber of aircraft engine |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113504051A (en) * | 2021-06-23 | 2021-10-15 | 四川大学 | Gas-water composite cooling visual probe structure |
| CN114878065A (en) * | 2022-03-23 | 2022-08-09 | 西北工业大学 | Dynamic pressure probe for main combustion chamber of aircraft engine |
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| CN202420759U (en) * | 2011-12-29 | 2012-09-05 | 中国燃气涡轮研究院 | Dynamic pressure testing system for miniature tube cavities |
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| CN107036758A (en) * | 2017-05-05 | 2017-08-11 | 北京航空航天大学 | A kind of air cooling high temperature dynamic pressure probe |
| CN208399148U (en) * | 2018-07-19 | 2019-01-18 | 中国航发沈阳发动机研究所 | A kind of air cooling total pressure probe and combustor exit high-temperature fuel gas stagnation pressure test macro |
| CN110455542A (en) * | 2019-08-13 | 2019-11-15 | 中国航发贵阳发动机设计研究所 | A kind of operating condition type variable equipment water jetting cooler for high-temperature fuel gas |
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2020
- 2020-07-31 CN CN202010754444.XA patent/CN111947830A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202420759U (en) * | 2011-12-29 | 2012-09-05 | 中国燃气涡轮研究院 | Dynamic pressure testing system for miniature tube cavities |
| CN103398815A (en) * | 2013-08-01 | 2013-11-20 | 哈尔滨东安发动机（集团）有限公司 | Pressure probe |
| CN105547578A (en) * | 2016-02-15 | 2016-05-04 | 中国船舶重工集团公司第七〇五研究所 | High-temperature fuel gas dynamic pressure guiding-out device with cooling water jacket |
| CN107036758A (en) * | 2017-05-05 | 2017-08-11 | 北京航空航天大学 | A kind of air cooling high temperature dynamic pressure probe |
| CN208399148U (en) * | 2018-07-19 | 2019-01-18 | 中国航发沈阳发动机研究所 | A kind of air cooling total pressure probe and combustor exit high-temperature fuel gas stagnation pressure test macro |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113504051A (en) * | 2021-06-23 | 2021-10-15 | 四川大学 | Gas-water composite cooling visual probe structure |
| CN114878065A (en) * | 2022-03-23 | 2022-08-09 | 西北工业大学 | Dynamic pressure probe for main combustion chamber of aircraft engine |
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