CN117367810B - Integrated test bench for aero-engine - Google Patents
Integrated test bench for aero-engine Download PDFInfo
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- CN117367810B CN117367810B CN202311666938.2A CN202311666938A CN117367810B CN 117367810 B CN117367810 B CN 117367810B CN 202311666938 A CN202311666938 A CN 202311666938A CN 117367810 B CN117367810 B CN 117367810B
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- 238000012360 testing method Methods 0.000 title claims abstract description 124
- 238000001514 detection method Methods 0.000 claims abstract description 27
- 230000017525 heat dissipation Effects 0.000 claims abstract description 17
- 238000005192 partition Methods 0.000 claims abstract description 16
- 230000030279 gene silencing Effects 0.000 claims abstract description 4
- 238000004088 simulation Methods 0.000 claims description 9
- 238000009434 installation Methods 0.000 claims description 7
- 238000000034 method Methods 0.000 description 8
- 230000008569 process Effects 0.000 description 6
- 238000001816 cooling Methods 0.000 description 3
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000004200 deflagration Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 150000003839 salts Chemical class 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
Classifications
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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
-
- 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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- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
Abstract
The invention discloses an integrated test bench of an aero-engine, which relates to the technical field of engine testing and comprises a detection chamber, wherein the detection chamber is of an integrated structure and is divided into a silencing chamber, a testing chamber and a circulating air chamber; a test bench is fixedly arranged in the test room, and an aeroengine to be tested is embedded on the test bench; an exhaust pipeline is arranged on the second partition board; a heat dissipation table is arranged in the test room and used for placing the tested aero-engine; the test bench is fixedly provided with an oil way which is communicated with the aero-engine and a test assembly which is used for testing the temperature, the rotating speed and the thrust of the aero-engine. The integrated test machine can perform ground detection on various types of engines, can realize the integral movement of the test chamber, and can be transferred through mobile equipment according to the requirements of the test environment of the engines; and the test function is complete, and the test bench is suitable for most aeroengines, so that the flexibility and the universality of the test bench are obviously improved.
Description
Technical Field
The invention relates to the technical field of engine testing, in particular to an integrated test bench for an aero-engine.
Background
The test is the only method for determining the performance index of the engine and evaluating the reliability and service life of the engine, and is the only means for checking whether the engine can be shaped and accepted. The engine ground test covers the fact that the content is rich, and a test device for measuring the engine performance parameters is called a thrust table or a test machine at present. The test bench is a test device used when the engine is tested on the ground, and mainly completes the measurement of the thrust of the engine and the measurement of related physical parameters (pressure, temperature, flow and the like), and performs corresponding processing according to test data to evaluate the performance of the engine.
The existing test machine is a movable ground test platform, has the advantage of convenient movement, is suitable for most of small aeroengines including turbojet or turbofan engines, and is extremely wide in application; however, the existing test machine also has the corresponding defects that the test item is single or the test item is detected after the replacement of the detection equipment is required, and the engine generates larger noise in the test process, so that the engine cannot be immediately transferred after the test is finished due to higher temperature; and the current test machine is not aimed at high and low temperatures. High salinity and high moisture environment simulation, and detection equipment integrating the test machine with the test machine are not available.
Therefore, it is highly desirable to design an integrated test machine for an aero-engine, which can realize the universality detection of the test machine and solve the noise problem and the ventilation and cooling problem in the engine test process.
Disclosure of Invention
The invention aims to provide an integrated test bench for an aero-engine, which is used for solving the problems in the prior art.
In order to achieve the above object, the present invention provides the following solutions: the invention provides an integrated test bench of an aero-engine, which comprises a detection chamber, wherein the detection chamber is of an integrated structure and is arranged in a building or on mobile equipment; the detection chamber is divided into a silencing chamber, a testing chamber and a circulating air chamber by a first partition plate and a second partition plate; a test bench is fixedly arranged in the test room, and an aeroengine to be tested is embedded on the test bench; an exhaust pipeline is arranged on the second partition plate; the aero-engine is arranged opposite to the exhaust pipeline;
an air inlet pipeline and an exhaust pipeline communicated with the exhaust pipeline are fixedly arranged in the circulating air room;
and the test bench is fixedly provided with an oil way for communicating with the aeroengine and a test assembly for testing the temperature, the rotating speed and the thrust of the aeroengine.
The test bench comprises a supporting bench, the supporting bench is fixedly arranged on the second partition board, the top surface of the supporting bench is fixedly provided with a height-adjusting frame, and the top surface of the height-adjusting frame is detachably provided with a fixing frame; the aero-engine to be tested is arranged in the fixing frame; the aero-engine is opposite to the inlet of the exhaust pipeline.
The fixing frame comprises a mounting underframe which is fixedly arranged on the top surface of the height-adjusting frame; an arc-shaped mounting groove is formed in the middle of the mounting underframe, a hinging seat and bench clamps are fixedly mounted on the top surface of the mounting underframe, and the hinging seat and the bench clamps are respectively arranged on two sides of the mounting groove; one end of a mounting top frame is arranged in the hinging seat through a rotating shaft; the other end of the mounting top frame is tightly attached to the mounting bottom frame through bench clamps; the middle part of the installation top frame is provided with an installation groove which has the same structure as the installation bottom frame; the aero-engine is arranged in the two mounting grooves.
The test assembly comprises a thrust sensor, a temperature sensor and a rotating speed sensor.
The test bench is also fixedly provided with an air circuit and an electric cabinet; the air circuit and/or the electric cabinet are/is used for starting the aeroengine.
A heat dissipation table is arranged in the test room and is used for placing the tested aeroengine; the top end of the heat dissipation table is open.
The heat dissipation platform comprises an exhaust fan and a heat dissipation pipe arranged on the exhaust fan; one end of the radiating pipe is vertically upwards, and the top opening is gradually enlarged to form an opening; the tested aero-engine is placed at the top end of the radiating pipe; the exhaust fan is also communicated with an exhaust pipeline.
And a temperature control system is also arranged in the test room and is used for adjusting the temperature in the test room to a high-temperature environment or a low-temperature environment.
An environment simulation system is fixedly arranged in the air inlet pipeline; the environment simulation system is used for simulating a high salinity or high moisture test environment.
The invention discloses the following technical effects: the integrated test machine can perform ground detection on various types of engines, the test chamber has complete functions of air exhaust and engine heat dissipation, the overall movement of the test chamber can be realized, and the test chamber is transferred through mobile equipment according to the requirements of the test environment of the engine; and the test function is complete, and the test bench is suitable for most aeroengines, so that the flexibility and the universality of the test bench are obviously improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the drawings that are needed in the embodiments will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a perspective view of the structure of a detection chamber according to the present invention;
FIG. 2 is a schematic view of the internal structure of the detection chamber according to the present invention;
FIG. 3 is a top view showing the internal structure of the detection chamber according to the present invention;
FIG. 4 is a schematic diagram of a test stand and a heat sink;
FIG. 5 is a schematic diagram of a test assembly arrangement;
1, a test bench; 11. a first separator; 12. a second separator; 13. an air draft pipeline; 14. an air inlet pipeline; 15. an exhaust duct; 2. a heat dissipation stage; 3. an oil path; 4. an electric control box; 5. an air path; 111. a support table; 112. a height-adjusting frame; 113. a fixing frame; 114. installing an underframe; 115. a hinge base; 116. installing a top frame; 117. bench clamp; 118. a pedestal; 119. an inner movable block; 120. an outer movable block; 21. an exhaust fan; 22. and a radiating pipe.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
As shown in fig. 1-4, the invention provides an integrated test bench for an aero-engine, which comprises a detection chamber, wherein the detection chamber is of an integrated structure and is arranged in a building or on mobile equipment; the detection chamber is divided into a silencing chamber, a testing chamber and a circulating air chamber by a first partition plate 11 and a second partition plate 12; a test bench 1 is fixedly arranged in the test room, and an aeroengine to be tested is embedded on the test bench 1; the second partition plate 12 is provided with an exhaust pipeline 13; the aero-engine is arranged opposite to the exhaust pipeline 13;
an air inlet pipeline 14 and an exhaust pipeline 15 communicated with the exhaust pipeline 13 are fixedly arranged in the circulating air room;
the test bench 1 is fixedly provided with an oil way 3 which is communicated with the aeroengine and a test assembly which is used for testing the temperature, the rotating speed and the thrust of the aeroengine.
The test bench 1 comprises a support bench 111, wherein the support bench 111 is fixedly arranged on the second partition plate 12, a height-adjusting frame 112 is fixedly arranged on the top surface of the support bench 111, and a fixing frame 113 is detachably arranged on the top surface of the height-adjusting frame 112; an aeroengine to be tested is arranged in the fixed frame 113; the aeroengine is facing the inlet of the suction duct 13.
The fixed frame 113 comprises a mounting underframe 114, and the mounting underframe 114 is fixedly arranged on the top surface of the height-adjusting frame 112; an arc-shaped mounting groove is formed in the middle of the mounting underframe 114, a hinge seat 115 and a pair of bench clamps 117 are fixedly arranged on the top surface of the mounting underframe 114, and the hinge seat 115 and the pair of bench clamps 117 are respectively arranged on two sides of the mounting groove; one end of a mounting top frame 116 is arranged in the hinging seat 115 through a rotating shaft; the other end of the mounting top frame 116 is tightly attached to the mounting bottom frame 114 through a bench clamp 117; a mounting groove which has the same structure as the mounting underframe 114 is formed in the middle of the mounting top frame 116; the aero-engine is arranged in the two mounting grooves.
The test assembly comprises a thrust sensor, a temperature sensor and a rotating speed sensor.
The test bench 1 is also fixedly provided with an air passage 5 and an electric cabinet 4; the air circuit 5 and/or the electric cabinet 4 start the test aeroengine.
A heat dissipation table 2 is arranged in the test room, and the heat dissipation table 2 is used for placing the tested aero-engine; the top end of the heat dissipation table 2 is open.
The heat dissipation platform 2 comprises an exhaust fan 21 and a heat dissipation pipe 22 arranged on the exhaust fan 21; one end of the radiating pipe 22 is vertically upwards, and the top opening is gradually enlarged to form an opening; the tested aero-engine is placed at the top end of the radiating pipe 22; the suction fan 21 is also in communication with the exhaust duct 15.
And a temperature control system is also arranged in the test room and is used for adjusting the temperature in the test room to a high-temperature environment or a low-temperature environment.
An environment simulation system is fixedly arranged in the air inlet pipeline 14; the environment simulation system is used for simulating a high salinity or high moisture test environment.
In one embodiment of the invention, the detection chamber is integrated equipment, can be matched with mobile equipment, can be installed indoors, and can be used for switching and selecting the actual environment according to the test environment requirement of the engine.
Further, the detection chamber is fixedly arranged in the chamber, an exhaust pipeline 13 in the circulating air room is communicated with the top of the detection chamber, and an air inlet pipeline 14 is conveyed to the top of the test room along the top of the circulating air room; a top partition board is fixedly arranged at the top of the test room, and an air inlet cavity communicated with the air inlet pipeline 14 is formed between the top partition board and the top surface of the test room; the first partition 11 is provided with a communication door and a transparent observation window.
In one embodiment of the invention, the detection chamber can be integrated on a conveying vehicle, and the detection chamber can be conveyed to a high altitude through the conveying vehicle due to various detection environments of the aero-engine, and the environment with high negative pressure is detected for the engine. And the process does not need to assemble a test bench, and is convenient to use.
Furthermore, when the aero-engine is required to be simulated in a high-temperature or low-temperature environment, the detection chamber can be matched and moved to a high negative pressure environment, a temperature control system arranged in the test room is started, and the high-temperature environment or the high-altitude environment of the aero-engine is simulated.
Furthermore, when the aeroengine is required to be placed in a salt fog environment, the detection chamber can be matched and moved to the coastal position, sea fog air is directly inhaled for engine test simulation, and the environment simulation system can be opened to regulate the temperature and the humidity of the inhaled air so as to achieve the aim of simulating the sea environment.
In one embodiment of the present invention, the oil path 3 includes an oil tank fixedly installed below the test stand 1, and two oil pipes connected to the oil tank through an oil pump, the two oil pipes being fixedly installed on the support stand 111.
In one embodiment of the present invention, the bench clamp 117 includes a pedestal 118, and an inner movable block 119 and an outer movable block 120 are rotatably mounted on the pedestal 118; the end part of the inner movable block 119 is also fixedly connected with a pressing block; the pressing block is abutted with the fixing pin; the fixed pins are disposed through the mounting top frame 116 and the mounting bottom frame 114.
Further, the outer movable block 120 is rotated to drive the inner movable block 119 to move, so that the position of the pressing block is adjusted.
In one embodiment of the present invention, the fixing frame 113 may be adjusted according to the type of the engine so that the engine to be tested is fixed in the installation groove space.
In one embodiment of the present invention, a telescopic rod may be installed in the middle of the top and bottom mounting frames 116 and 114, so that the length of the mounting slot is adjustable, and the mounting slot is suitable for various aeroengine models.
In one embodiment of the invention, the glass fiber is arranged inside the exhaust pipeline for sound insulation and insulation purposes.
In one embodiment of the invention, a central control box is also arranged in the test room and is used for displaying test assembly data, gas circuit 5 data and environmental devices (humidity, salinity, temperature and the like) in the test room.
In one embodiment of the invention, a camera or a camera is also installed in the test room for recording the experimental process
In one embodiment of the present invention, as shown in FIG. 5, the thrust sensor is fixedly mounted on the bottom of the elevation frame 112.
In one embodiment of the invention, the speed sensor is adjustably mounted on the overhead boom 112 and is positioned on the side of the aircraft engine intake duct at a distance of 0.5-1 cm from the aircraft engine.
In one embodiment of the invention, the temperature sensor is disposed aft of the aircraft engine and proximate to the aircraft engine.
In one embodiment of the invention, an exhaust system is arranged in the exhaust pipeline 13, and is started at the beginning of the test, so that the high-temperature gas generated during the test of the aeroengine is guided, the temperature environment between the tests is ensured, and meanwhile, the temperature sensor can accurately measure the actual temperature of the aeroengine.
In one embodiment of the invention, the air circuit 5 comprises an air pump and an air pipe which are arranged at the bottom of the test bench 1; the gas pipe is fixedly installed on the supporting table 111; the method is used for starting the aero-engine.
In one embodiment of the invention, the electric cabinet 4 is used for being connected with a starting motor of the aircraft engine in a circuit connection mode; providing an ignition signal.
In one embodiment of the present invention, the detection method of the present device is: checking whether an oil way is unobstructed, and selecting the starting or electrifying starting of the air way 5 according to the type of the aeroengine; the position of the test assembly is checked to determine if the electric cabinet 4 is within the set voltage range.
Further, the aeroengine to be tested is fixedly clamped on the fixed frame 113, and the height of the height adjusting frame 112 is adjusted to be aligned with the exhaust pipeline 13; adjusting the position of a temperature sensor at the tail part of the engine, and keeping a certain distance from the tail nozzle; and adjusting the position of the rotating speed sensor. Connecting the positive electrode and the negative electrode of a starting power supply;
in one embodiment of the invention, an oil pipe on an aeroengine to be tested is communicated with an oil way 3 for oil supply; the circuit is opened, air is supplied to the front air pressure wheel of the aeroengine to be tested through the air circuit 5, the main shaft of the aeroengine to be tested is provided with ignition, the air pressure wheel pumps air compression ignition into the air pressure wheel, the combustion chamber inside the air pressure wheel begins to deflagrate, the rear turbine is pushed after deflagration, the rear turbine drives the main shaft, the main shaft drives the air pressure wheel to begin combustion, and the aeroengine to be tested is successfully started to finish ignition.
Further, in the starting process of the aero-engine, the thrust sensor and the rotating speed sensor measure the thrust at each rotating speed in the starting process of the engine; and meanwhile, the temperature sensor records jet flow temperature values under various rotating speed conditions of the aero-engine.
In a test embodiment of the invention, a maximum temperature value measured by a temperature sensor is selected as a judgment condition of the air entraining capability boundary of the aeroengine, the aeroengine selects a mode of starting an air path 5, the air entraining flow, the thrust and the temperature are recorded under the condition of recording the rotating speed of the aeroengine, the corresponding temperature value is used as the air entraining characteristic of the rotating speed condition, and if the specification engine is smaller than the air entraining characteristic under the same rotating speed adjustment, the engine still has the air entraining capability; if the jet flow temperature of the engine is equal to the air entraining characteristic, determining that the maximum air entraining capacity boundary of the engine at the rotating speed is reached, and recording the corresponding air entraining mass flow as the maximum air entraining capacity boundary of the engine at the rotating speed; repeating the steps for a plurality of times to obtain the bleed air characteristics of the engine at each rotating speed, the bleed air boundary and the engine thrust under the bleed air condition.
In one test embodiment of the invention, the apparatus is suitable for use with aircraft engines of types below 300 kg, including turbofan engines, turbojet engines, turboshaft engines, turboprop engines, and the like.
Furthermore, the aero-engine selects the selective starting mode of the air circuit 5 or the electric cabinet according to the electric starting and the air starting, and the various starting types of the power supply of the internal starting motor or the external motor.
In one embodiment of the invention, the engine is transferred to the cooling station 2 for rapid cooling after the test is completed.
Furthermore, after the test is completed, the engine is in a high-temperature state, and the air supply to the engine can be rapidly cooled through the air path 5.
In the description of the present invention, it should be understood that the terms "longitudinal," "transverse," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the present invention, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the present invention.
The above embodiments are only illustrative of the preferred embodiments of the present invention and are not intended to limit the scope of the present invention, and various modifications and improvements made by those skilled in the art to the technical solutions of the present invention should fall within the protection scope defined by the claims of the present invention without departing from the design spirit of the present invention.
Claims (5)
1. An integrated test bed for an aircraft engine, comprising: the detection chamber is of an integrated structure and is arranged in a building or on mobile equipment; the detection chamber is divided into a silencing room, a testing room and a circulating air room by a first partition board (11) and a second partition board (12); a test table (1) is fixedly arranged in the test room, and an aeroengine to be tested is embedded on the test table (1); an exhaust pipeline (13) is arranged on the second partition board (12); the aero-engine is arranged opposite to the exhaust pipeline (13);
an air inlet pipeline (14) and an air exhaust pipeline (15) communicated with the air exhaust pipeline (13) are fixedly arranged in the circulating air room;
an oil way (3) used for being communicated with the aeroengine and a test assembly used for testing the temperature, the rotating speed and the thrust of the aeroengine are fixedly arranged on the test bench (1); the test bench (1) comprises a supporting bench (111), the supporting bench (111) is fixedly arranged on the second partition board (12), a height-adjusting frame (112) is fixedly arranged on the top surface of the supporting bench (111), and a fixing frame (113) is detachably arranged on the top surface of the height-adjusting frame (112); the aeroengine to be tested is arranged in the fixing frame (113); the aero-engine is opposite to the inlet of the exhaust pipeline (13); the fixing frame (113) comprises a mounting underframe (114), and the mounting underframe (114) is fixedly arranged on the top surface of the height-adjusting frame (112); an arc-shaped mounting groove is formed in the middle of the mounting underframe (114), a hinging seat (115) and a bench clamp (117) are fixedly mounted on the top surface of the mounting underframe (114), and the hinging seat (115) and the bench clamp (117) are respectively arranged on two sides of the mounting groove; one end of a mounting top frame (116) is arranged in the hinging seat (115) through a rotating shaft; the other end of the mounting top frame (116) is tightly attached to the mounting bottom frame (114) through a bench clamp (117); the middle part of the installation top frame (116) is provided with an installation groove which has the same structure as the installation bottom frame (114); the aero-engine is arranged in the two mounting grooves; the test assembly comprises a thrust sensor, a temperature sensor and a rotating speed sensor; an air channel (5) is fixedly arranged on the test bench (1), and the air channel (5) is used for starting the aeroengine; a heat dissipation table (2) is further arranged in the test room, and the heat dissipation table (2) is used for placing the tested aeroengine; the top end of the heat dissipation table (2) is open; the maximum temperature value measured by a temperature sensor is selected as a judgment condition of the air entraining capability boundary of the aero-engine, the aero-engine selects a mode of starting an air circuit 5, the air entraining flow, the thrust and the temperature are recorded under the condition of the rotating speed of the aero-engine, the corresponding temperature value is used as the air entraining characteristic of the rotating speed condition, and if the temperature value is smaller than the air entraining characteristic under the condition of the same rotating speed adjustment of a specification engine, the engine still has the air entraining capability; if the jet flow temperature of the engine is equal to the air entraining characteristic, determining that the maximum air entraining capacity boundary of the engine at the rotating speed is reached, and recording the corresponding air entraining mass flow as the maximum air entraining capacity boundary of the engine at the rotating speed; repeating the steps for a plurality of times to obtain the bleed air characteristics of the engine at each rotating speed, the bleed air boundary and the engine thrust under the bleed air condition.
2. The integrated test bench of an aircraft engine according to claim 1, wherein: an electric cabinet (4) is fixedly arranged on the test bench (1); the electric cabinet (4) is used for starting the aeroengine.
3. The integrated test bench of an aircraft engine according to claim 1, wherein: the heat dissipation platform (2) comprises an exhaust fan (21) and a heat dissipation pipe (22) arranged on the exhaust fan (21); one end of the radiating pipe (22) is vertically upwards, and the top opening is gradually enlarged to form an opening; the tested aero-engine is placed at the top end of the radiating pipe (22); the exhaust fan (21) is also communicated with an exhaust pipeline (15).
4. The integrated test bench of an aircraft engine according to claim 2, wherein: and a temperature control system is also arranged in the test room and is used for adjusting the temperature in the test room to a high-temperature environment or a low-temperature environment.
5. The integrated test bench of an aircraft engine according to claim 2, wherein: an environment simulation system is fixedly arranged in the air inlet pipeline (14); the environment simulation system is used for simulating a high salinity or high moisture test environment.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202311666938.2A CN117367810B (en) | 2023-12-07 | 2023-12-07 | Integrated test bench for aero-engine |
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| CN202311666938.2A CN117367810B (en) | 2023-12-07 | 2023-12-07 | Integrated test bench for aero-engine |
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| CN117367810A CN117367810A (en) | 2024-01-09 |
| CN117367810B true CN117367810B (en) | 2024-03-08 |
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