CN112129539B - Engine combustion chamber testing and temperature control device based on aero-engine - Google Patents
Engine combustion chamber testing and temperature control device based on aero-engine Download PDFInfo
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- CN112129539B CN112129539B CN202011009649.1A CN202011009649A CN112129539B CN 112129539 B CN112129539 B CN 112129539B CN 202011009649 A CN202011009649 A CN 202011009649A CN 112129539 B CN112129539 B CN 112129539B
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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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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K11/00—Measuring temperature based upon physical or chemical changes not covered by groups G01K3/00, G01K5/00, G01K7/00 or G01K9/00
- G01K11/12—Measuring temperature based upon physical or chemical changes not covered by groups G01K3/00, G01K5/00, G01K7/00 or G01K9/00 using changes in colour, translucency or reflectance
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Abstract
The invention discloses an aero-engine-based engine combustion chamber testing and temperature control device which comprises a testing box body, a liquid storage tank, an equipment support, a lifting box body, a tooth force arm and a third plane gear, wherein a sealing box door is hinged and fixed on the outer side of the testing box body, an exhaust pipeline is welded and fixed on the top of the testing box body, the liquid storage tank is fixedly bonded on the outer side of the testing box body, a liquid injection pipeline is fixedly bonded on the outer side of the liquid storage tank, an operating platform is fixedly welded under the testing box body, a testing base is fixedly welded on the bottom of the operating platform, and a heat insulation cover plate is hinged and fixed on the outer side of the testing base. This engine combustion chamber test and temperature control device based on aeroengine is provided with eccentric wheel and single gear, drives the displacement layer board through the eccentric wheel and carries out the horizontal slip, adjusts the position of control by temperature change box according to the diameter of combustion chamber on the one hand, promotes the flexibility of control by temperature change box internal plant to the combustion chamber inspection.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to an aero-engine-based engine combustion chamber testing and temperature control device.
Background
In order to improve the thrust-weight ratio of a modern aeroengine, the working temperature of the aeroengine is higher and higher, the heat load of parts at the hot end of the aeroengine is larger and larger, engines with different diameters are fixed by an engine combustion chamber testing and temperature control device based on the aeroengine, the intensity of flame combustion is adjusted in the multi-stage control process of the engines, on one hand, redundant fuel oil is sprayed out of the combustion chamber within a certain time, the thrust of the engines cannot be influenced, meanwhile, a large number of resources can be consumed, and on the other hand, when the working temperature of parts inside the aeroengine is exceeded, the damage condition to workpieces inside the aeroengine can be caused;
1. the combustion chamber is a key hot end part of an aircraft engine, the fatigue reliability and the service life of the combustion chamber of the aircraft engine have important influence on the airworthiness operation safety of an aircraft, so that the damage of the hot end part of the aircraft engine is tested and controlled, the conventional temperature control device detects the heat of the combustion chamber through a single structure, when the combustion chamber sprays and burns the aircraft fuel, the combustion temperatures of different parts are different, and the test and the static test of the temperature control device cannot effectively control and test the combustion chamber in multiple angles;
2. when the aero-engine combustion chamber is used, the combustion chamber is locked by the testing and temperature control device, when the temperature of the combustion chamber is too high, partial internal energy of gas expands in the turbine and is converted into mechanical energy to drive the gas compressor to rotate, damage to the gas compressor is caused, high-temperature damage to an engine shell is required to be caused by the device, the device is difficult to cool and adjust the surface of the combustion chamber, the combustion chamber is caused to be damaged by too high temperature in the testing process, and the cost and labor intensity of the combustion chamber of the engine in the testing process are increased.
We have therefore proposed an aircraft engine based engine combustion chamber testing and temperature control apparatus to address the problems set out above.
Disclosure of Invention
The invention aims to provide an aero-engine-based engine combustion chamber testing and temperature control device, and aims to solve the problems that the existing temperature control device detects the heat of the combustion chamber through a single structure, the static test of the testing and temperature control device cannot effectively control and test the temperature of the combustion chamber in multiple angles, the device is difficult to cool and adjust the position of the surface of the combustion chamber, and the monitoring equipment and the engine are damaged by overhigh temperature in the testing process of the combustion chamber in the prior market.
In order to achieve the purpose, the invention provides the following technical scheme: an engine combustion chamber testing and temperature control device based on an aircraft engine comprises a testing box body, a liquid storage tank, an equipment support, a lifting box body, a tooth force arm and a third plane gear, wherein a sealing box door is fixed on the outer side of the testing box body in a hinged mode, an exhaust pipeline is fixed on the top of the testing box body in a welded mode, the liquid storage tank is fixedly connected with the outer side of the testing box body in a bonded mode, a liquid injection pipeline is fixedly connected on the outer side of the liquid storage tank body in a bonded mode, an operating platform is fixedly welded under the testing box body, a testing base is fixedly welded at the bottom of the operating platform, a heat insulation cover plate is fixedly connected on the outer side of the testing base in a hinged mode, an alloy bolt is connected on the outer side of the heat insulation cover plate in a nested mode, a limiting box body is arranged inside the testing box body, a first plane gear is connected to the outer side of the limiting box body in a shaft, a spraying desktop is arranged on one side of the limiting box body, and the outside threaded connection of spraying desktop has high pressure nozzle, the outside nested connection of spraying desktop has driving motor, and driving motor's output is connected with conical gear, conical gear's outside nested connection has the transmission pivot, and the outside nested connection of transmission pivot has the emission flabellum, the outside welded fastening of spraying desktop has the second guide rail, operation platform's inside nested connection has radiating fin, the outside hub connection of equipment support has auxiliary roller, the rectangle spout has been seted up on the bottom surface of test box.
Preferably, the test box body is parallel to the operating platform, the middle of the operating platform is of a rectangular open structure, and the test box body is connected with the liquid storage water tank through a liquid injection pipeline and a high-pressure sprayer.
Preferably, the inside of test base is including eccentric wheel, displacement layer board, first guide rail, control by temperature change box, scribble the rotary drum, detect the paster, film thermocouple and armor thermocouple, and the eccentric wheel nestification is fixed at the displacement layer board to the bottom of displacement layer board is connected with first guide rail, and displacement layer board top welded fastening has the control by temperature change box in addition, and the top hub connection of displacement layer board has simultaneously scribbled the rotary drum, the detection paster has been placed to the inside of control by temperature change box, and the outside of detecting the paster is connected with the film thermocouple, and the one end electric wire connection of film thermocouple has the armor thermocouple moreover.
Preferably, the displacement supporting plate and the temperature control box body form a sliding structure through an eccentric wheel and a first guide rail, and the height of the temperature control box body is smaller than that of the smearing rotary drum.
Preferably, the equipment support and the lifting box body form a sliding structure through a tooth force arm and a third plane gear, the lifting box body is arranged right above the equipment support, the tooth force arm is fixed to one end of the equipment support in a welded mode, and the top of the tooth force arm is connected with the third plane gear in a meshed mode.
Preferably, the inside of spacing box is including centre gripping paster, direction slide bar, ball, rotation axis, second face gear and single gear, and the outside threaded connection of centre gripping paster has ball to the outside nested connection of centre gripping paster has the direction slide bar, and the outside nested connection of spacing box has the rotation axis moreover, and the outside nested connection of rotation axis has the second face gear simultaneously, one side meshing of second face gear is connected with single gear.
Preferably, the clamping patches form a sliding structure through the guide sliding rods and the ball screws, the width of each clamping patch is smaller than that of the limiting box body, and the limiting box body and the clamping patches are made of aviation aluminum alloy materials.
Preferably, the limiting box body and the clamping patch form a rotating structure through a rotating shaft, a second plane gear and a single gear, and the limiting box body is connected with the lifting box body through a shaft.
Preferably, the discharge fan blades and the driving motor are connected with the transmission rotating shaft through bevel gears, and the number of the bevel gears and the transmission rotating shaft is 2.
Preferably, the radiating fins are symmetrically distributed about the central line of the operating platform, and rectangular sliding grooves are formed in the bottoms of the operating platform and the test box body.
Compared with the prior art, the invention has the beneficial effects that: the test and temperature control device for the combustion chamber of the engine based on the aircraft engine,
1. the temperature control device is provided with an eccentric wheel and a single gear, the eccentric wheel drives a displacement supporting plate to horizontally slide, on one hand, the position of a temperature control box body is adjusted according to the diameter of a combustion chamber, the flexibility of the internal equipment of the temperature control box body for checking the combustion chamber is improved, on the other hand, a rotary drum is coated on the outer side of the combustion chamber, the temperature display of different positions of the combustion chamber through temperature indicating paint is facilitated, the combustion chamber is driven by the single gear to rotate in multiple angles, the angle of the combustion chamber is adjusted according to the detection requirement, operators can observe multiple parts of the combustion chamber conveniently, and the flexibility of temperature control and test is improved;
2. the combustion chamber locking device is provided with a conical gear and a ball screw, a plurality of groups of transmission rotating shafts are driven to rotate through the conical gear, the transmission rotating shafts drive the discharge fan blades and the eccentric wheel to rotate, the stability of the device in the testing and controlling process is improved, the ball screw drives the clamping patches to horizontally slide, and the clamping patches are used for locking and limiting combustion chambers with different diameters, so that the stability of the combustion chambers in the operation and rotation processes is ensured, and the stability of flame operation at the bottom of the combustion chambers is avoided;
3. be provided with the tooth arm of force and rectangle spout, carry out horizontal migration through the tooth arm of force drive lifting box, need adjust its self position according to the detection of lifting the box, and then lift the flexibility of box surface combustion chamber cooling and temperature control with higher speed to carry out spacing fixed to equipment support's bottom through the rectangle spout, avoid equipment support to take place the skew at the slip in-process, and the rectangle open type structure through the bottom is dispelled the heat and is discharged flame.
Drawings
FIG. 1 is a schematic front view of a test chamber according to the present invention;
FIG. 2 is a schematic view of the interior of the test chamber of the present invention;
FIG. 3 is a schematic top view of the spacing box of the present invention;
FIG. 4 is a top view of the spray table of the present invention;
FIG. 5 is a schematic view of the interior of a test base according to the present invention;
FIG. 6 is a schematic top view of a temperature controlled enclosure according to the present invention;
FIG. 7 is a side cross-sectional view of a test housing of the present invention.
In the figure: 1. testing the box body; 2. sealing the box door; 3. an exhaust duct; 4. a liquid storage tank; 5. a liquid injection pipeline; 6. an operating platform; 7. testing the base; 701. an eccentric wheel; 702. a displacement pallet; 703. a first guide rail; 704. a temperature control box body; 705. coating the rotary drum; 706. detecting the patch; 707. a thin film thermocouple; 708. sheathing a thermocouple; 8. a heat insulating cover plate; 9. alloy bolts; 10. an equipment support; 11. lifting the box body; 12. a limiting box body; 1201. clamping the patch; 1202. a guide slide bar; 1203. a ball screw; 1204. a rotating shaft; 1205. a second face gear; 1206. a single gear; 13. a tooth moment arm; 14. a first face gear; 15. spraying the table top; 16. a high pressure spray head; 17. a drive motor; 18. discharging the fan blades; 19. a third face gear; 20. a second guide rail; 21. a bevel gear; 22. a transmission rotating shaft; 23. a heat dissipating fin; 24. an auxiliary roller; 25. a rectangular chute.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-7, the present invention provides a technical solution: an aircraft engine combustion chamber testing and temperature control device comprises a testing box body 1, a sealing box door 2, an exhaust pipeline 3, a liquid storage tank 4, a liquid injection pipeline 5, an operation platform 6, a testing base 7, a heat insulation cover plate 8, an alloy bolt 9, an equipment support 10, a lifting box body 11, a limiting box body 12, a tooth force arm 13, a first plane gear 14, a spraying desktop 15, a high-pressure spray head 16, a driving motor 17, an exhaust fan blade 18, a third plane gear 19, a second guide rail 20, a conical gear 21, a transmission rotating shaft 22, a heat radiation fin 23, an auxiliary roller 24 and a rectangular sliding groove 25, wherein the sealing box door 2 is hinged and fixed on the outer side of the testing box body 1, the exhaust pipeline 3 is fixedly welded on the top of the testing box body 1, the liquid storage tank 4 is fixedly bonded on the outer side of the testing box body 1, and the liquid injection pipeline 5 is fixedly bonded on the outer side of the liquid storage tank 4, an operating platform 6 is fixedly welded right below the test box body 1, a test base 7 is fixedly welded at the bottom of the operating platform 6, a heat insulation cover plate 8 is fixedly hinged at the outer side of the test base 7, an alloy bolt 9 is connected at the outer side of the heat insulation cover plate 8 in a nested manner, a limit box body 12 is arranged inside the test box body 1, a first plane gear 14 is connected at the outer side of the limit box body 12 in a shaft connection manner, a spraying table top 15 is arranged at one side of the limit box body 12, a high-pressure spray nozzle 16 is connected at the outer side of the spraying table top 15 in a threaded manner, a driving motor 17 is connected at the outer side of the spraying table top 15 in a nested manner, the output end of the driving motor 17 is connected with a conical gear 21, a transmission rotating shaft 22 is connected at the outer side of the conical gear 21 in a nested manner, discharge fan blades 18 are connected at the outer side of the transmission rotating shaft 22 in a nested manner, a second guide rail 20 is fixedly welded at the outer side of the spraying table top 15, and radiating fins 23 are connected at the inner side of the operating platform 6 in a nested manner, the outer side of the equipment support 10 is connected with an auxiliary roller 24 through a shaft, and the bottom surface of the test box body 1 is provided with a rectangular sliding groove 25.
The inside of the test base 7 comprises an eccentric wheel 701, a displacement supporting plate 702, a first guide rail 703, a temperature control box 704, a coating drum 705, a detection patch 706, a thin film thermocouple 707 and an armored thermocouple 708, the eccentric wheel 701 is fixed on the displacement supporting plate 702 in a nested manner, the bottom of the displacement supporting plate 702 is connected with the first guide rail 703, the top of the displacement supporting plate 702 is fixedly welded with the temperature control box 704, the top shaft of the displacement supporting plate 702 is connected with the coating drum 705, the detection patch 706 is placed in the temperature control box 704, the outer side of the detection patch 706 is connected with the thin film thermocouple 707, one end of the thin film thermocouple 707 is connected with the armored thermocouple 708 through a wire, the surface of the engine is monitored in a temperature control manner through the thin film thermocouple 707 and the armored thermocouple 708, and the heating efficiency of the combustion chamber of the engine is ensured.
The displacement supporting plate 702 and the temperature control box body 704 form a sliding structure through an eccentric wheel 701 and a first guide rail 703, the height of the temperature control box body 704 is smaller than the height of the smearing rotary drum 705, the temperature control box body 704 is driven to move left and right through the displacement supporting plate 702, temperature indicating paint is further smeared on the surface of the combustion chamber, and different positions of the combustion chamber can be conveniently monitored.
The inside of spacing box 12 is including centre gripping paster 1201, direction slide bar 1202, ball 1203, rotation axis 1204, second plane gear 1205 and single gear 1206, and the outside threaded connection of centre gripping paster 1201 has ball 1203, and the outside nested connection of centre gripping paster 1201 has direction slide bar 1202, and the outside nested connection of spacing box 12 has rotation axis 1204, the outside nested connection of rotation axis 1204 has second plane gear 1205 simultaneously, one side meshing connection of second plane gear 1205 has single gear 1206, centre gripping the both sides of combustion chamber through centre gripping paster 1201, promote the flexibility of combustion chamber in test and angle modulation.
The clamping patches 1201 form a sliding structure through the guide sliding rod 1202 and the ball screw 1203, the width of the clamping patches 1201 is smaller than that of the limiting box body 12, the limiting box body 12 and the clamping patches 1201 are made of aviation aluminum alloy, the distance between the clamping patches 1201 is adjusted according to the diameter of the combustion chamber, and convenience of fixing the clamping patches 1201 to the combustion chamber is improved.
Spacing box 12 and centre gripping paster 1201 constitute rotating-structure through rotation axis 1204, second plane gear 1205 and single gear 1206, and spacing box 12 with lift box 11 and be the hub connection, drive the combustion chamber through centre gripping paster 1201 and carry out multi-angle rotation, make things convenient for operating personnel to diversely observe the combustion chamber.
The discharge fan blades 18 and the driving motor 17 are connected with the transmission rotating shaft 22 through the bevel gears 21, the number of the bevel gears 21 and the transmission rotating shaft 22 is 2, the discharge fan blades 18 and the eccentric wheel 701 rotate through the transmission rotating shaft 22, and the automation degree of operation and control of the device is improved.
Radiating fin 23 is about 6 central lines symmetric distributions of operation platform, and rectangle spout 25 has all been seted up to operation platform 6 and test box 1's bottom, gives off the unnecessary heat of operation through radiating fin 23, promotes the efficiency of combustion chamber cooling.
The working principle of the embodiment is as follows: when the aero-engine-based engine combustion chamber testing and temperature control device is used, as shown in fig. 1, 2, 3 and 7, an operator turns on the driving motor 17, the driving motor 17 drives the third planar gear 19 to rotate, the third planar gear 19 drives the tooth force arm 13 to slide on the outer side of the second guide rail 20, the tooth force arm 13 pushes the lifting box body 11 to move, the lifting box body 11 slides on the outer side of the rectangular sliding groove 25 through the bottom auxiliary roller 24, so that the lifting housing 11 is moved out of the test housing 1, then the combustion chamber and the housing are inserted into the interior of the limit housing 12, then the ball screw 1203 is gripped, the clamping patches 1201 are driven by the ball screw 1203 to slide on the outer side of the guide slide bar 1202, clamping the outer side of the combustion chamber through a clamping patch 1201, and locking the surface of the combustion chamber through a bolt;
according to the drawings of fig. 1, 2, 4 and 5, the operator then turns on the driving motor 17, the driving motor 17 drives the third plane gear 19 to rotate in the opposite direction, the third plane gear 19 drives the tooth force arm 13 to slide on the outer side of the second guide rail 20, the tooth force arm 13 pulls the equipment support 10 and the limiting box 12 into the testing box 1, the third plane gear 19 is detached from the output end of the driving motor 17, then the heat insulation cover plate 8 is opened, temperature indicating paint is led into the smearing rotating drum 705, then the driving motor 17 is started, the driving motor 17 drives the bevel gear 21 to rotate, the bevel gear 21 drives the transmission rotating shaft 22 to rotate, the transmission rotating shaft 22 drives the eccentric wheel 701 to rotate, the eccentric wheel 701 drives the displacement supporting plate 702 and the smearing rotating drum 705 to move, and the displacement supporting plate 702 slides on the outer side of the first guide rail 703;
as shown in fig. 2, 5 and 6, the applicator drum 705 applies a coating to the skin of the aero combustion chamber, and the detection patch 706 is attached to the outside of the combustion chamber so that the outer side of the thin-film thermocouple 707 is attached to the outside of the combustion chamber, the thin-film thermocouple 707 is connected with the armored thermocouple 708, the first plane gear 14 at the output end of the driving motor 17 is in chain connection with the first plane gear 14 on the same side, then a fuel supply valve is opened, fuel is led into the combustion chamber, the combustion chamber sprays and combusts the fuel, the first plane gear 14 drives the single gear 1206 to rotate, the single gear 1206 drives the second plane gear 1205 to rotate, the second plane gear 1205 drives the rotating shaft 1204 and the limiting box 12 to rotate, the limiting box 12 drives the combustion chamber to rotate in multiple angles, and testers can observe temperature indicating paint on the surface of the combustion chamber conveniently;
according to the fig. 1, 2, 5 and 6, the thin film thermocouple 707 directly measures the temperature of the important part of the surface of the combustion chamber, converts the temperature signal into a thermal electromotive force signal, converts the thermal electromotive force signal into the temperature of the measured medium through the electric instrument, collects and transmits the signal through the sheathed thermocouple 708, when the temperature is too high, the liquid storage tank 4 inputs the liquid into the spray table top 15 through the liquid injection pipeline 5, the surface of the combustion chamber is cooled through the high pressure nozzle 16, the water vapor generated by combustion is discharged out of the test box body 1 through the exhaust pipeline 3, the heat dissipation fins 23 absorb the heat generated by operation, the heat discharge speed is accelerated, meanwhile, the operator can reduce the input amount of fuel oil, reduce the intensity of the motion of the aircraft engine, and then open the driving motor 17 to drive the bevel gear 21 to rotate along with gradually closing the motion speed of the combustion chamber, the bevel gear 21 drives the transmission rotating shaft 22 and the discharge fan blade 18 to rotate, the discharge fan blade 18 accelerates the speed of the heat dissipation on the surface of the combustion chamber, and the heat data generated by the operation of the equipment is counted, so that a series of work is completed.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that various changes in the embodiments and/or modifications of the invention can be made, and equivalents and modifications of some features of the invention can be made without departing from the spirit and scope of the invention.
Claims (4)
1. The utility model provides an engine combustion chamber test and temperature control device based on aeroengine, includes test box (1), stock solution tank (4), equipment support (10), lifts box (11), tooth arm of force (13) and third face gear (19), its characterized in that: the test box comprises a test box body (1), a sealing box door (2) is hinged and fixed to the outer side of the test box body (1), an exhaust pipeline (3) is welded and fixed to the top of the test box body (1), a liquid storage tank (4) is fixedly bonded to the outer side of the test box body (1), a liquid injection pipeline (5) is fixedly bonded and fixed to the outer side of the liquid storage tank (4), an operating platform (6) is fixedly welded and fixed to the right below of the test box body (1), a test base (7) is fixedly welded to the bottom of the operating platform (6), a heat insulation cover plate (8) is hinged and fixed to the outer side of the test base (7), an alloy bolt (9) is connected to the outer side of the heat insulation cover plate (8) in an embedded mode, a limiting box body (12) is arranged inside the test box body (1), a first plane gear (14) is connected to the outer side shaft of the limiting box body (12), and a spraying desktop (15) is arranged on one side of the limiting box body (12), the outer side of the spraying table top (15) is in threaded connection with a high-pressure spray head (16), the outer side of the spraying table top (15) is connected with a driving motor (17) in a nested mode, the output end of the driving motor (17) is connected with a bevel gear (21), the outer side of the bevel gear (21) is connected with a transmission rotating shaft (22) in a nested mode, the outer side of the transmission rotating shaft (22) is connected with a discharge fan blade (18) in a nested mode, the outer side of the spraying table top (15) is fixedly welded with a second guide rail (20), the inner portion of the operating platform (6) is connected with a radiating fin (23) in a nested mode, the outer side of the equipment support (10) is connected with an auxiliary roller (24) in a shaft mode, and the bottom surface of the test box body (1) is provided with a rectangular sliding groove (25);
the testing device is characterized in that the testing base (7) comprises an eccentric wheel (701), a displacement supporting plate (702), a first guide rail (703), a temperature control box body (704), a coating rotary drum (705), a detection patch (706), a thin film thermocouple (707) and an armored thermocouple (708) inside, the eccentric wheel (701) is fixed on the displacement supporting plate (702) in a nested manner, the bottom of the displacement supporting plate (702) is connected with the first guide rail (703), the top of the displacement supporting plate (702) is fixedly welded with the temperature control box body (704), the top shaft of the displacement supporting plate (702) is connected with the coating rotary drum (705), the detection patch (706) is placed inside the temperature control box body (704), the thin film thermocouple (707) is connected to the outer side of the detection patch (706), and one end of the thin film thermocouple (707) is connected with the armored thermocouple (708) through a wire;
the displacement supporting plate (702) and the temperature control box body (704) form a sliding structure through an eccentric wheel (701) and a first guide rail (703), and the height of the temperature control box body (704) is smaller than that of the smearing rotary drum (705);
the equipment support (10) and the lifting box body (11) form a sliding structure through a tooth force arm (13) and a third plane gear (19), the lifting box body (11) is arranged right above the equipment support (10), one end of the equipment support (10) is fixedly welded with the tooth force arm (13), and the top of the tooth force arm (13) is connected with the third plane gear (19) in a meshed mode;
the limiting box body (12) is internally provided with a clamping patch (1201), a guide sliding rod (1202), a ball screw (1203), a rotating shaft (1204), a second plane gear (1205) and a single gear (1206), the ball screw (1203) is in threaded connection with the outer side of the clamping patch (1201), the guide sliding rod (1202) is in nested connection with the outer side of the clamping patch (1201), the rotating shaft (1204) is in nested connection with the outer side of the limiting box body (12), the second plane gear (1205) is in nested connection with the outer side of the rotating shaft (1204), and the single gear (1206) is in meshed connection with one side of the second plane gear (1205);
the clamping patches (1201) form a sliding structure through a guide sliding rod (1202) and a ball screw (1203), the width of each clamping patch (1201) is smaller than that of the limiting box body (12), and the limiting box body (12) and the clamping patches (1201) are made of aviation aluminum alloy materials;
the limiting box body (12) and the clamping patches (1201) form a rotating structure through a rotating shaft (1204), a second plane gear (1205) and a single gear (1206), and the limiting box body (12) is connected with the lifting box body (11) through a shaft.
2. The aero-engine based engine combustion chamber testing and temperature control device of claim 1, wherein: the test box body (1) and the operation platform (6) are parallel to each other, the middle of the operation platform (6) is of a rectangular opening type structure, and the test box body (1) is connected with the liquid storage water tank (4) through a liquid injection pipeline (5) and a high-pressure spray head (16).
3. The aero-engine based engine combustion chamber testing and temperature control device of claim 1, wherein: the discharge fan blades (18) and the driving motor (17) are connected with the transmission rotating shaft (22) through the bevel gears (21), and the number of the bevel gears (21) and the transmission rotating shaft (22) is 2.
4. The aero-engine based engine combustion chamber testing and temperature control device of claim 1, wherein: radiating fin (23) are about operation platform (6) central line symmetric distribution, and rectangle spout (25) have all been seted up to operation platform (6) and test box (1) bottom.
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| CN202011009649.1A CN112129539B (en) | 2020-09-23 | 2020-09-23 | Engine combustion chamber testing and temperature control device based on aero-engine |
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| CN202011009649.1A CN112129539B (en) | 2020-09-23 | 2020-09-23 | Engine combustion chamber testing and temperature control device based on aero-engine |
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| CN112129539B true CN112129539B (en) | 2021-10-01 |
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| CN2625876Y (en) * | 2002-12-30 | 2004-07-14 | 沈阳黎明航空发动机(集团)有限责任公司 | Rotary testing apparatus for temperature of engine combustion chamber temperature field |
| CN102175459B (en) * | 2011-01-28 | 2012-11-21 | 南京航空航天大学 | Automatic measurement and control device for test bench of combustion chamber of micro engine |
| CN102507849B (en) * | 2011-10-19 | 2014-06-18 | 清华大学 | Testing device and testing method for stimulaitng dynamic oxidation ablation of engine combustor environment |
| CN105300545A (en) * | 2015-09-25 | 2016-02-03 | 中国航空工业集团公司沈阳发动机设计研究所 | Engine combustion chamber outlet temperature field test device |
| CN207556859U (en) * | 2017-09-25 | 2018-06-29 | 新奥能源动力科技（上海）有限公司 | A kind of combustor test equipment and system |
| CN107588434A (en) * | 2017-09-25 | 2018-01-16 | 上海泛智能源装备有限公司 | A kind of spray cooling structure and combustor test device |
| CN109374308B (en) * | 2018-09-20 | 2020-12-11 | 中国民航大学 | Aeroengine combustion chamber simulation test bed with steady-state temperature field |
| CN109520741A (en) * | 2018-10-29 | 2019-03-26 | 中国航发沈阳发动机研究所 | A kind of aeroengine combustor buring room casing pressure experimental device |
| CN111610028A (en) * | 2020-05-27 | 2020-09-01 | 西北工业大学 | Shifting temperature measuring device suitable for high-temperature high-pressure rectangular test piece |
-
2020
- 2020-09-23 CN CN202011009649.1A patent/CN112129539B/en active Active
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