CN112033688A - System for measuring temperature flow field outside jet lobe of aircraft engine and control method thereof - Google Patents
System for measuring temperature flow field outside jet lobe of aircraft engine and control method thereof Download PDFInfo
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- CN112033688A CN112033688A CN202010455885.XA CN202010455885A CN112033688A CN 112033688 A CN112033688 A CN 112033688A CN 202010455885 A CN202010455885 A CN 202010455885A CN 112033688 A CN112033688 A CN 112033688A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K13/00—Thermometers specially adapted for specific purposes
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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Abstract
The invention relates to the technical field of aviation, in particular to an aeroengine tail jet lobe outer temperature flow field measuring system and a control method thereof, wherein the measuring system comprises a tail jet lobe flow field measuring device, a motor controller, a signal acquisition instrument, a switch and a PC (personal computer) control analysis system, the motor controller is connected with the tail jet lobe flow field measuring device, the motor controller is simultaneously connected with the switch, the switch is connected with the PC control analysis system, the signal acquisition instrument is simultaneously connected with the tail jet lobe flow field measuring device and the switch, the utilization rate of a sensor can be improved by adopting a rotary measuring mode, and the performance of the sensor can be fully exerted; the cross-shaped measurement mode can mutually avoid the mutual interference between the temperature arrangement harrow and the pressure arrangement harrow, thereby improving the measurement precision; the composition and the content of the tail-injected gas can be rapidly detected, the combustion degree of the fuel is analyzed, and a basis is provided for improving the combustion performance of the combustion chamber.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a system for measuring a temperature flow field outside a jet lobe at the tail of an aeroengine and a control method thereof.
Background
The tail jet flow generated by the gas turbine engine assembled on the airplane during working has the characteristics of high temperature, high pressure and high speed, the high-temperature characteristic of the tail jet flow has direct influence on personnel safety, the infrared radiation characteristics of the engine and the airplane, the engine deflector and the like, and an effective aeroengine tail jet lobe outer temperature flow field measurement system is urgently needed to simulate various aeroengine tail jet lobe outer flow field tests under the condition that no supporting equipment is arranged in the aeroengine tail jet lobe outer flow field measurement test, so that the effectiveness and the comprehensiveness in the test process are ensured.
However, the existing aeroengine tail flow field testing device has the problems of poor comprehensiveness, low measurement precision, low sensor utilization rate and no controllability in the measurement process, and cannot adapt to flow field testing tests of different tail jet lobe structures of aeroengines of different specifications and models.
Disclosure of Invention
The invention provides an aeroengine tail jet lobe outer temperature flow field measuring system and a control method thereof aiming at the defects of the existing engine tail jet lobe outer temperature flow field testing device.
In order to achieve the purpose, the invention provides the following technical scheme:
the system comprises a tail jet lobe flow field measuring device, a motor controller, a signal acquisition instrument, a switch and a PC (personal computer) control analysis system, wherein the motor controller is connected with the tail jet lobe flow field measuring device, the motor controller is simultaneously connected with the switch, the switch is connected and arranged on the PC control analysis system, and the signal acquisition instrument is simultaneously connected with the tail jet lobe flow field measuring device and the switch;
the tail jet lobe flow field measuring device comprises:
the device comprises an installation frame, wherein a movable transmission shaft is arranged on the installation frame close to the upper part, a gear fixing and moving frame is arranged on the movable transmission shaft, and a servo motor is arranged in front of the gear fixing and moving frame;
the temperature distribution rake and the pressure distribution rake are in a cross form, and the servo motor, the rotary transmission shaft, the bevel gear transmission structure, the temperature distribution rake and the pressure distribution rake are all arranged in front of the gear fixing and moving frame.
Furthermore, the tail jet lobe flow field measuring device further comprises a stepping motor, and the stepping motor is connected with the movable transmission shaft.
Furthermore, the stepping motor is also connected with the motor controller and the signal acquisition instrument, and the servo motor is connected with the motor controller.
Further, be close to removal transmission shaft department on the installation frame and be equipped with spacing sensor in a left side, spacing sensor in a right side and start position sensor from right side to left side in proper order.
Further, the lower part horizontal direction of installation frame sets up the slide rail, the both ends are fixed on the installation frame about the slide rail, the center mark point of slide rail is located the positive center of engine tail spout, and this center is also the center of rotation of temperature harrow and the pressure harrow of arranging.
Further, the shape of the gear fixing and moving frame is a triangular support, the gear fixing and moving frame comprises a moving rod, two supporting rods and a connecting block, one ends of the two supporting rods are respectively connected with the two ends of the moving rod, and the other ends of the two supporting rods are fixed together through the connecting block.
Furthermore, the movable rod can be movably sleeved on the movable transmission shaft, and the connecting block can be movably sleeved on the sliding rail.
Further, the back of the gear fixing and moving frame is provided with a gas collection probe distribution ring, and the center of the gas collection probe distribution ring is installed on a connecting block of the gear fixing and moving frame.
Furthermore, gas collecting probes are distributed on the gas collecting probe distribution ring.
The control method of the system for measuring the temperature and the flow field outside the jet lobe of the aircraft engine comprises the following steps:
when the test is started, the PC control analysis system sends a stepping motor/servo motor operation command to the tail jet lobe flow field measuring device through the motor controller so that the stepping motor/servo motor operates, the stepping motor of the tail jet lobe flow field measuring device moves to the initial position, and the servo motor is in an idle operation state; when the flow field of the tail jet lobe of the engine needs to be measured, the servo motor receives a rotation command, the rotating transmission shaft and the bevel gear transmission structure are controlled to drive the temperature distribution rake and the pressure distribution rake to rotate in the circumferential direction, so that a temperature distribution value and a pressure distribution value are measured, meanwhile, a gas collection probe obtains a gas value through testing, a signal acquisition instrument obtains test data such as the temperature distribution value, the pressure distribution value and the gas value, the test data are transmitted through a switch and input into a PC control analysis system.
The PC control analysis system comprises a tail jet lobe flow field analysis interface, the tail jet lobe flow field analysis interface comprises a file storage setting panel, a tail jet lobe flow field measuring device setting panel, a temperature distribution diagram display interface, a pressure distribution diagram display interface, a gas component indicating mark and a gas component content measuring device, before a test starts, a file storage position is selected through the file storage setting panel, the panel can also return the system to an initial state after a test is completed, and the tail jet lobe flow field measuring device setting panel is used for setting running parameters of a stepping motor, including a starting position, a moving distance and whether a specified position is reached;
meanwhile, setting servo motor operation parameters including rotation times, rotation angle, action time and whether the servo motor rotates for one circle, wherein the rotation angle is a feedback angle value, and judging whether the servo motor rotates in place;
the temperature distribution and the pressure distribution of the tail jet lobe flow field can be displayed in real time through the temperature distribution diagram display interface and the pressure distribution diagram display interface, and are compared with the analysis design value of the tail jet lobe, so that the reasonability of the tail jet lobe structure is further judged;
when the relevant components are detected in the test process, the gas component indicating mark lamp is lightened, and the concentration value is displayed in the gas component content measurer, so that the components of the tail-injected gas can be monitored in real time, the combustion degree of fuel oil is analyzed, and data support is provided for improving the performance of the combustion chamber of the aero-engine.
Compared with the prior art, the invention has the following beneficial effects:
1. the measuring system for the temperature flow field outside the tail jet lobe of the aero-engine, provided by the invention, has the advantages of simple structure, low manufacturing cost, capability of real-time acquisition, wide applicability, strong operability, good portability and high precision, can simulate various flow field tests outside the tail jet lobe of the aero-engine, is suitable for the flow field test tests of different tail jet lobe structures of aero-engines with different specifications and models, and ensures the effectiveness and the comprehensiveness of the test process.
2. The aeroengine tail jet lobe outer temperature flow field measuring system provided by the invention has test conditions for measuring aeroengine tail jet lobe flow field, can provide a real-time temperature distribution analysis chart and a pressure distribution analysis chart, compares the real-time temperature distribution analysis chart and the pressure distribution analysis chart with design values, meets the controllability requirement of the aeroengine tail jet lobe flow field test measuring process, and meets the requirements of analyzing the combustion degree of a combustion chamber and improving the structure of the combustion chamber.
3. The system for measuring the temperature flow field outside the tail jet lobe of the aero-engine can measure the distribution states of the temperature flow field and the pressure flow field of the tail jet lobe of the engine at various working rotating speeds in real time, detect the components and the content of tail jet gas in a multi-level mode, store measurement data, generate a visual temperature distribution diagram, a pressure distribution diagram, a gas component and content diagram, compare simulation design values of the tail jet lobe flow field of the aero-engine and verify whether the structure performance of the tail jet lobe of the aero-engine is reasonable or not.
4. The temperature and pressure measurement time of the temperature flow field measurement system outside the jet lobe of the aircraft engine provided by the invention is controllable, and the test time of the aircraft engine can be fully utilized; the utilization rate of the sensor can be improved by adopting a rotary measurement mode, and the performance of the sensor can be fully exerted; the cross-shaped measurement mode can mutually avoid the mutual interference between the temperature arrangement harrow and the pressure arrangement harrow, thereby improving the measurement precision; the system for measuring the temperature flow field outside the tail jet lobe of the aero-engine can also be used for rapidly detecting the components and the content of tail jet fuel gas, analyzing the fuel combustion degree and providing a basis for improving the combustion performance of a combustion chamber.
Drawings
FIG. 1 is a schematic structural diagram of a tail jet lobe flow field measuring device provided by the invention;
FIG. 2 is a schematic structural diagram of a system for measuring the temperature and flow field outside a tail jet lobe of an aircraft engine provided by the invention;
FIG. 3 is a schematic structural diagram of a gear fixing and moving frame in a tail jet lobe flow field measurement device of the aircraft engine of FIG. 1;
FIG. 4 is an analysis diagram of a flow field distribution state of a tail jet lobe measured by a system for measuring the temperature flow field outside the tail jet lobe of the aircraft engine provided by the invention;
1-tail jet lobe flow field measuring device, 1-1-stepping motor, 1-2-left limit sensor, 1-3-right limit sensor, 1-4-start position sensor, 1-5-movable transmission shaft, 1-6-mounting frame, 1-7-sliding rail, 1-8-gear fixed movable frame, 1-8-1-movable rod, 1-8-2-two supporting rods, 1-8-3-connecting block, 1-9-servo motor, 1-10-bevel gear transmission structure, 1-11-temperature arrangement rake, 1-12-pressure arrangement rake, 1-13-rotary transmission shaft, 1-14-gas collection probe, 1-3-gas collection probe, 2-motor controller, 3-signal collector, 4-exchanger, 5-PC control analysis system.
Detailed Description
The invention is described in detail below by way of exemplary embodiments. It should be understood, however, that elements, structures and features of one embodiment may be beneficially incorporated in other embodiments without further recitation.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "bottom", "inner", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are only for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "connected" and "connected" are to be interpreted broadly, e.g., as being fixed or detachable or integrally connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In order to more clearly describe the aeroengine tail jet lobe outer temperature flow field measuring system and the control method thereof provided by the embodiment of the invention in detail, the following description is combined with specific embodiments.
Example 1
As shown in fig. 1-2, the embodiment provides an aircraft engine tail jet lobe external temperature flow field measurement system, which includes a tail jet lobe flow field measurement device 1, a motor controller 2, a signal acquisition instrument 3, a switch 4 and a PC control analysis system 5, where the motor controller 2 is connected to the tail jet lobe flow field measurement device 1, the motor controller 2 is simultaneously connected to the switch 4, the switch 4 is connected to the PC control analysis system 5, and the signal acquisition instrument 3 is simultaneously connected to the tail jet lobe flow field measurement device 1 and the switch 4;
the tail jet lobe flow field measuring device 1 comprises:
the device comprises a mounting frame 1-6, wherein a movable transmission shaft 1-5 is arranged on the mounting frame 1-6 and close to the upper part, a gear fixing and moving frame 1-8 is arranged on the movable transmission shaft 1-5, and a servo motor 1-9 is arranged in front of the gear fixing and moving frame 1-8;
one end of the rotating transmission shaft 1-13 is connected with the output shaft end of the servo motor 1-9, the other end of the rotating transmission shaft 1-13 is connected with a bevel gear transmission structure 1-10, a temperature arrangement rake 1-11 and a pressure arrangement rake 1-12 are fixed on the output shaft of the bevel gear transmission structure 1-10, the temperature arrangement rake 1-11 and the pressure arrangement rake 1-12 are in a cross form, and the servo motor 1-9, the rotating transmission shaft 1-13, the bevel gear transmission structure 1-10, the temperature arrangement rake 1-11 and the pressure arrangement rake 1-12 are all arranged in front of the gear fixing and moving frame 1-8.
In this embodiment, the tail jet lobe flow field measuring device 1 further includes a stepping motor 1-1, the stepping motor 1-1 is connected to the movable transmission shaft 1-5, the stepping motor 1-1 is further connected to the motor controller 2 and the signal acquisition instrument 3, respectively, and the servo motor 1-9 is connected to the motor controller 2.
In this embodiment, a left limit sensor 1-2, a right limit sensor 1-3 and a start position sensor 1-4 are sequentially arranged on the mounting frame 1-6 from right to left near the movable transmission shaft 1-5, a slide rail 1-7 is arranged in the horizontal direction of the lower part of the mounting frame 1-6, the left end and the right end of the slide rail 1-7 are fixed on the mounting frame 1-6, a central mark point of the slide rail 7 is located at the center of a tail nozzle of the engine, and the center is also the rotation center of the temperature distribution rake 11 and the pressure distribution rake 12.
As shown in fig. 3, in this embodiment, the gear fixing and moving frame 1-8 is a triangular bracket, the gear fixing and moving frame 1-8 includes a moving rod 1-8-1, two support rods 1-8-2, and a connecting block 1-8-3, one end of each of the two support rods 1-8-2 is connected to two ends of the moving rod 1-8-1, the other ends of the two support rods 1-8-2 are fixed together by the connecting block 1-8-3, the moving rod 1-8-1 is movably sleeved on a moving transmission shaft 1-5, and the connecting block 1-8-3 is movably sleeved on a sliding rail 1-7. The movable rod 1-8-1 is matched with the left limit sensor 1-2, the right limit sensor 1-3 and the start position sensor 1-4, and the moving position of the movable rod can be adjusted in real time by controlling an analysis system through a PC (personal computer) so as to meet the tail jet lobe forms of engines with different specifications and models; one end of the movable transmission shaft 1-5 is connected with the stepping motor 1-1, the other end of the movable transmission shaft is connected with the supporting structure, and the gear fixing movable frame 1-8 is sleeved on the movable transmission shaft so as to provide a horizontal transverse position of the gear fixing movable frame 1-8.
The back of the gear fixing and moving frame 1-8 is provided with a gas collection probe distribution ring, the center of the gas collection probe distribution ring is arranged on a connecting block 1-8-3 of the gear fixing and moving frame 1-8, and gas collection probes 1-14 are distributed on the gas collection probe distribution ring.
The system for measuring the temperature flow field outside the jet lobe of the aircraft engine provided by the embodiment is characterized in that the stepping motor provides the temperature and the horizontal transverse position change of the pressure arrangement rake fixing device, the servo motor provides the temperature and the rotation angular position change of the pressure arrangement rake fixing device, the temperature arrangement harrow and the pressure probe arrangement harrow respectively measure the change distribution condition of the tail jet lobe flow field, the temperature arrangement harrow and the pressure probe arrangement harrow are distributed in a cross shape, can effectively improve the interference of the temperature arrangement harrow to the pressure arrangement harrow, the measurement mode of the rotating mode can improve the utilization rate of the temperature probe and the pressure probe, improve the measurement progress, save the research and development cost, analyze the components and the content of the fuel gas in real time, the air quality in the closed space test bed can be effectively monitored, the fuel combustion degree is analyzed, and data support is provided for improving the combustion chamber of the aero-engine.
The control method of the system for measuring the temperature flow field outside the jet lobe of the aircraft engine in the embodiment comprises the following steps:
when a test is started, the PC control analysis system 5 sends a stepping motor 1-1/servo motor 1-9 operation command to the tail jet lobe flow field measuring device 1 through the motor controller 2 so that the stepping motor 1-1/servo motor 1-9 operates, the stepping motor 1-1 of the tail jet lobe flow field measuring device 1 moves to an initial position, and the servo motor 1-9 is in an idle running state; when the flow field of the tail jet lobe of the engine needs to be measured, the servo motors 1-9 receive a rotation command, the temperature distribution rakes 1-11 and the pressure distribution rakes 1-12 are driven to perform circumferential rotation actions by controlling the rotation transmission shafts 1-13 and the bevel gear transmission structures 1-10, so that a temperature distribution value and a pressure distribution value are measured, meanwhile, the gas collection probes 1-14 are used for obtaining a gas value through testing, the signal collection instrument 3 is used for obtaining test data such as the temperature distribution value, the pressure distribution value and the gas value, and the test data are transmitted through the switch 4 and input into the PC control analysis system 5.
As shown in fig. 4, the PC control analysis system 5 includes a tail jet lobe flow field analysis interface, the tail jet lobe flow field analysis interface includes a file storage setting panel, a tail jet lobe flow field measurement device setting panel, a temperature distribution diagram display interface, a pressure distribution diagram display interface, a gas component indication mark, and a gas component content measurer, before the test starts, a file storage position is selected through the file storage setting panel, the panel can also return to the initial state after a test is completed, and the tail jet lobe flow field measurement device sets a panel to set the operation parameters of the stepping motor, including a start position, a moving distance, and whether to reach a designated position;
meanwhile, setting servo motor operation parameters including rotation times, rotation angle, action time and whether the servo motor rotates for one circle, wherein the rotation angle is a feedback angle value, and judging whether the servo motor rotates in place;
the temperature distribution and the pressure distribution of the tail jet lobe flow field can be displayed in real time through the temperature distribution diagram display interface and the pressure distribution diagram display interface, and are compared with the analysis design value of the tail jet lobe, so that the reasonability of the tail jet lobe structure is further judged;
when the relevant components are detected in the test process, the gas component indicating mark lamp is lightened, and the concentration value is displayed in the gas component content measurer, so that the components of the tail-injected gas can be monitored in real time, the combustion degree of fuel oil is analyzed, and data support is provided for improving the performance of the combustion chamber of the aero-engine.
Claims (10)
1. The utility model provides an aeroengine tail jet lobe outer temperature flow field measurement system which characterized in that: the device comprises a tail jet lobe flow field measuring device (1), a motor controller (2), a signal acquisition instrument (3), an exchanger (4) and a PC (personal computer) control analysis system (5), wherein the motor controller (2) is connected with the tail jet lobe flow field measuring device (1), the motor controller (2) is simultaneously connected with the exchanger (4), the exchanger (4) is connected with the PC control analysis system (5), and the signal acquisition instrument (3) is simultaneously connected with the tail jet lobe flow field measuring device (1) and the exchanger (4);
the tail jet lobe flow field measuring device (1) comprises:
the device comprises a mounting frame (1-6), wherein a movable transmission shaft (1-5) is arranged on the mounting frame (1-6) close to the upper part, a gear fixing movable frame (1-8) is arranged on the movable transmission shaft (1-5), and a servo motor (1-9) is arranged in front of the gear fixing movable frame (1-8);
one end of the rotary transmission shaft (1-13) is connected with the output shaft end of the servo motor (1-9), the other end of the rotating transmission shaft (1-13) is connected with a bevel gear transmission structure (1-10), an output shaft of the bevel gear transmission structure (1-10) is fixed with a temperature arrangement harrow (1-11) and a pressure arrangement harrow (1-12), the temperature arrangement harrow (1-11) and the pressure arrangement harrow (1-12) are in a cross form, the servo motors (1-9), the rotating transmission shafts (1-13), the bevel gear transmission structures (1-10), the temperature distribution rakes (1-11) and the pressure distribution rakes (1-12) are all arranged in front of the gear fixing and moving frame (1-8).
2. The aero-engine aft jet lobe external temperature flow field measurement system of claim 1, wherein: the tail jet lobe flow field measuring device (1) further comprises a stepping motor (1-1), and the stepping motor (1-1) is connected with the movable transmission shaft (1-5).
3. The aero-engine aft jet lobe external temperature flow field measurement system of claim 2, wherein: the stepping motor (1-1) is further connected with the motor controller (2) and the signal acquisition instrument (3) respectively, and the servo motor (1-9) is connected with the motor controller (2).
4. The aero-engine aft jet lobe external temperature flow field measurement system of claim 1, wherein: a left limit sensor (1-2), a right limit sensor (1-3) and a start position sensor (1-4) are sequentially arranged on the mounting frame (1-6) from right to left and close to the movable transmission shaft (1-5).
5. The aero-engine aft jet lobe external temperature flow field measurement system of claim 1, wherein: the lower part of the mounting frame (1-6) is provided with a sliding rail (1-7) in the horizontal direction, the left end and the right end of the sliding rail (1-7) are fixed on the mounting frame (1-6), a central mark point of the sliding rail (7) is positioned in the center of a tail nozzle of the engine, and the center is also the rotation center of the temperature arrangement rake (11) and the pressure arrangement rake (12).
6. The aero-engine aft jet lobe external temperature flow field measurement system of claim 5, wherein: the gear fixing and moving frame (1-8) is a triangular support, the gear fixing and moving frame (1-8) comprises a moving rod (1-8-1), two supporting rods (1-8-2) and a connecting block (1-8-3), one ends of the two supporting rods (1-8-2) are respectively connected with two ends of the moving rod (1-8-1), and the other ends of the two supporting rods (1-8-2) are fixed together through the connecting block (1-8-3).
7. The aero-engine aft jet lobe external temperature flow field measurement system of claim 6, wherein: the movable rod (1-8-1) can be movably sleeved on the movable transmission shaft (1-5), and the connecting block (1-8-3) can be movably sleeved on the sliding rail (1-7).
8. The aero-engine aft jet lobe external temperature flow field measurement system of claim 1, wherein: the back of the gear fixed moving frame (1-8) is provided with a gas collection probe distribution ring, and the center of the gas collection probe distribution ring is arranged on a connecting block (1-8-3) of the gear fixed moving frame (1-8).
9. The aero-engine aft jet lobe external temperature flow field measurement system of claim 8, wherein: and the gas collecting probes (1-14) are distributed on the gas collecting probe distribution ring.
10. A control method for an aircraft engine tail jet lobe external temperature flow field measurement system as claimed in any one of claims 1 to 9, wherein: the method comprises the following steps:
when a test is started, a PC control analysis system (5) sends a stepping motor (1-1)/servo motor (1-9) operation command to a tail jet lobe flow field measuring device (1) through a motor controller (2) so that the stepping motor (1-1)/the servo motor (1-9) can act, the stepping motor (1-1) of the tail jet lobe flow field measuring device (1) moves to an initial position, and the servo motor (1-9) is in an idle running state; when an engine tail jet lobe flow field needs to be measured, a servo motor (1-9) receives a rotation command, a temperature distribution rake (1-11) and a pressure distribution rake (1-12) are driven to perform circumferential rotation actions by controlling a rotation transmission shaft (1-13) and a bevel gear transmission structure (1-10), so that a temperature distribution value and a pressure distribution value are measured, meanwhile, a gas collection probe (1-14) tests to obtain a gas value, a signal acquisition instrument (3) obtains test data such as the temperature distribution value, the pressure distribution value and the gas value, the test data are transmitted through a switch (4) and input into a PC control analysis system (5).
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| CN112834228A (en) * | 2021-01-28 | 2021-05-25 | 中国人民解放军空军工程大学 | Aeroengine air intake scanning measuring device |
| CN112924178A (en) * | 2021-02-04 | 2021-06-08 | 中国航发沈阳发动机研究所 | Flow field parameter acquisition system |
| CN114459768A (en) * | 2022-02-09 | 2022-05-10 | 绵阳诺达佳工业控制技术有限公司 | Engine ground flow field testing device |
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| CN112834228A (en) * | 2021-01-28 | 2021-05-25 | 中国人民解放军空军工程大学 | Aeroengine air intake scanning measuring device |
| CN112834228B (en) * | 2021-01-28 | 2022-12-13 | 中国人民解放军空军工程大学 | Aeroengine air intake scanning measuring device |
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| CN114459768B (en) * | 2022-02-09 | 2023-11-14 | 绵阳诺达佳工业控制技术有限公司 | Engine ground flow field testing device |
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