CN117109929B - Ground test run system of aero-engine - Google Patents
Ground test run system of aero-engine Download PDFInfo
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- CN117109929B CN117109929B CN202311371116.1A CN202311371116A CN117109929B CN 117109929 B CN117109929 B CN 117109929B CN 202311371116 A CN202311371116 A CN 202311371116A CN 117109929 B CN117109929 B CN 117109929B
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- 238000012360 testing method Methods 0.000 title claims abstract description 201
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 52
- 230000007246 mechanism Effects 0.000 claims abstract description 41
- 238000001816 cooling Methods 0.000 claims description 14
- 230000001360 synchronised effect Effects 0.000 claims description 12
- 238000005266 casting Methods 0.000 claims description 9
- 238000007789 sealing Methods 0.000 claims description 3
- 241000883990 Flabellum Species 0.000 claims 1
- 238000009825 accumulation Methods 0.000 abstract description 4
- 238000003825 pressing Methods 0.000 description 20
- 238000000034 method Methods 0.000 description 12
- 230000008569 process Effects 0.000 description 12
- 230000000694 effects Effects 0.000 description 10
- 230000009471 action Effects 0.000 description 5
- 238000007664 blowing Methods 0.000 description 4
- 230000000149 penetrating effect Effects 0.000 description 3
- GUIJLPKNGJMXKV-AZUAARDMSA-N rod-188 Chemical compound C1=CC(C)=CC=C1S(=O)(=O)N1[C@@H]([C@H]2OC(=O)CC2)C2=CC=CC=C2CC1 GUIJLPKNGJMXKV-AZUAARDMSA-N 0.000 description 3
- 238000007599 discharging Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
Classifications
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/20009—Modifications to facilitate cooling, ventilating, or heating using a gaseous coolant in electronic enclosures
- H05K7/20136—Forced ventilation, e.g. by fans
- H05K7/20172—Fan mounting or fan specifications
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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
-
- 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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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/20009—Modifications to facilitate cooling, ventilating, or heating using a gaseous coolant in electronic enclosures
- H05K7/20136—Forced ventilation, e.g. by fans
- H05K7/20145—Means for directing air flow, e.g. ducts, deflectors, plenum or guides
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/20218—Modifications to facilitate cooling, ventilating, or heating using a liquid coolant without phase change in electronic enclosures
- H05K7/20272—Accessories for moving fluid, for expanding fluid, for connecting fluid conduits, for distributing fluid, for removing gas or for preventing leakage, e.g. pumps, tanks or manifolds
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- Engineering & Computer Science (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Testing Of Engines (AREA)
Abstract
The invention discloses an aeroengine ground test run system, in particular to the field of aeroengine test run, which comprises a test room, wherein a test run table is connected in the test room in a sliding manner, one side of the test run table is provided with a pressure sensor, the pressure sensor is fixedly connected in the test room, the top of the test run table is provided with a trolley, the top of the trolley is rotationally connected with a rotating plate, one side of the test room is fixedly connected with an air inlet mechanism, the other side of the test room is fixedly connected with an exhaust mechanism, the top of the test room is fixedly connected with a flow guide mechanism, and the bottom of the test room is provided with a water storage pool. According to the invention, the trolley and the test bed are arranged, so that the quick connection of the aero-engine is completed, and the high-temperature gas in the test workshop is quickly discharged through the arrangement of the air inlet mechanism, the exhaust mechanism, the diversion mechanism and the water storage tank, so that the accumulation of the high-temperature gas in the test workshop is avoided.
Description
Technical Field
The invention relates to the technical field of aeroengine test run, in particular to an aeroengine ground test run system.
Background
Aeroengine test run refers to an experiment for checking the performance, reliability and durability of an engine by using special test and test equipment, wherein the aeroengine test run is divided into ground test equipment, high-altitude simulation test equipment and flight test equipment, and the test run process of the aeroengine generally comprises the following steps: cold running, slow running, take-off state, maximum continuous power state, slow running, stopping and cooling, and the primary test time is different from 20 minutes to 8 hours according to the different test purposes.
Chinese patent CN202211388397.7 discloses a multifunctional bench for an aeroengine test bed, comprising: the frame body structure comprises a fixed frame, a movable frame, an upper hanging frame and a supporting preassembled underframe which are sequentially connected from top to bottom, wherein the fixed frame is assembled on a test bed, and a tested engine is arranged in the supporting preassembled underframe; an exhaust diffuser hanging frame is arranged on the fixed frame, and an exhaust diffuser is detachably arranged on the exhaust diffuser hanging frame; a flow tube hanging frame is fixed on the upper hanging frame, and a flow tube is arranged on the flow tube hanging frame; the supporting preassembly underframe is provided with a main fulcrum and an auxiliary fulcrum, and the main fulcrum and the auxiliary fulcrum are used for installing and fixing the tested engine. The multifunctional bench designed by the invention can effectively improve the mounting efficiency of the engine on the bench, lighten the labor intensity, reduce the time of the engine occupied by the bench and has important significance for improving the service efficiency of the test bed.
However, when the aero-engine performs ground test, the surface temperature of the aero-engine is increased, so that the gas temperature in the test room is increased, the gas cannot be discharged out quickly and effectively, high-temperature gas is accumulated in the test room, and the test of the aero-engine can be influenced for a long time, so that how to design an aero-engine ground test system for avoiding the accumulation of the high-temperature gas in the test room is a problem which needs to be solved currently.
Disclosure of Invention
In order to overcome the defects in the prior art, the embodiment of the invention provides an aeroengine ground test system, which is provided with a pressing piece and a stop block, wherein the aeroengine is firstly fixed on a rotating plate of a cart and pushed into a test workshop, the stop block is finally used for fixing a test bed and the cart, and the stop block is used for fixing the cart and the rotating plate, so that the problems in the background art are solved.
In order to achieve the above purpose, the present invention provides the following technical solutions: the utility model provides an aeroengine ground test system, includes the test room, the inside sliding connection of test room has the test room, one side of test room is provided with pressure sensor, pressure sensor fixed connection is in the inside of test room, the top of test room is provided with the shallow, the top of shallow is rotated and is connected with the revolving board, the top fixedly connected with aeroengine of revolving board, the inside sliding connection of shallow has the casting die, the bottom of casting die is provided with the fixture block, fixture block sliding connection is in the inside of shallow, the first spring of outer wall fixedly connected with of fixture block, first spring fixedly connected in the inside of shallow, the outer wall hinge of casting die has the flexible connecting rod, the one end hinge of casting die has the briquetting, briquetting sliding connection is in the inside of shallow, the top fixedly connected with second spring of briquetting, the top fixedly connected with dog, the outer wall fixedly connected with connecting rod of dog, the bottom of shallow be provided with runner, the outer wall of shallow is provided with the recess, the recess is provided with the fixture block, the air inlet guide mechanism is equipped with the test floor, the air guide mechanism is equipped with the test room, the air guide mechanism is equipped with the test floor.
In a preferred embodiment, the air inlet mechanism comprises an outer air inlet pipe, one end of the outer air inlet pipe is fixedly connected with the outer wall of the test room, an inner air inlet pipe is arranged in the outer air inlet pipe, one end of the inner air inlet pipe is fixedly connected with the outer wall of the test room and is communicated with the inside of the test room, and the other end of the inner air inlet pipe is rotationally connected with a second double-sided gear.
In a preferred embodiment, the outer wall of the inner air inlet pipe is rotationally connected with a centrifugal fan, the inner wall of the centrifugal fan is provided with an inner gear and is meshed with the outer teeth of the second double-sided gear, the inner wall of the outer air inlet pipe is fixedly connected with a second fixing plate, the bottom of the second fixing plate is rotationally connected with a second movable rod in a penetrating mode, one end of the second movable rod is fixedly connected with a second fan blade, the other end of the second movable rod is fixedly connected with a second gear, and the second gear is meshed with the inner teeth of the second double-sided gear.
In a preferred embodiment, the exhaust mechanism comprises an outer exhaust pipe, one end of the outer exhaust pipe is fixedly connected with the outer wall of the test room and extends to the inside of the test room, an inner exhaust pipe is arranged in the outer exhaust pipe, one end of the inner exhaust pipe is fixedly connected with the outer wall of the test room, the inner exhaust pipe is communicated with the test room, and the other end of the inner exhaust pipe is rotationally connected with the first double-sided gear.
In a preferred embodiment, the outer wall of the inner exhaust pipe is rotationally connected with an exhaust fan, the inner wall of the exhaust fan is provided with an inner gear and is meshed with the outer teeth of the first double-sided gear, the inner wall of the inner exhaust pipe is fixedly connected with a first fixing plate, the bottom of the first fixing plate is rotationally connected with a first movable rod, one end of the first movable rod is fixedly connected with a first fan blade, the other end of the first movable rod is fixedly connected with a first gear, the first gear is meshed with the inner teeth of the first double-sided gear, one side outer wall of the test room is provided with a diversion hole, and the diversion hole is arranged between the inner exhaust pipe and the outer exhaust pipe.
In a preferred embodiment, a draft tube is arranged inside the outer wall of the outer air inlet tube, one end of the draft tube is communicated with the test room, the other end of the draft tube is communicated with the inner portion of the outer air inlet tube, the outer wall of the outer air inlet tube is fixedly connected with a draft tube, one end of the draft tube is communicated with the draft tube, and the other end of the draft tube is communicated with the test room.
In a preferred embodiment, a water inlet pipe is arranged on one side of the water storage tank, a water outlet pipe is arranged on the other side of the water storage tank, and the water inlet pipe and the water outlet pipe are communicated with the water storage tank.
In a preferred embodiment, the guiding mechanism comprises a plurality of connecting pieces, the connecting pieces are fixedly connected with the inner wall of the test workshop, the connecting pieces are provided with a plurality of connecting pieces in opposite states, a rotating shaft is connected between the connecting pieces in a rotating mode, a synchronous belt is arranged between the rotating shafts and adjacent to the connecting pieces, a plurality of guiding plates are fixedly connected to the outer wall of the synchronous belt, a third gear is fixedly connected to the two ends of the rotating shaft on one side of the synchronous belt, a rotating rod is connected to the top end of the inner wall of the test workshop in a rotating mode, a fourth gear is fixedly connected to the outer wall of the rotating rod and meshed with the third gear, a third fan blade is fixedly connected to the bottom end of the rotating rod, and the guiding plates are arranged in an arc shape.
In a preferred embodiment, one end of the outer exhaust pipe extending to the inside of the test room is arranged in a horn shape, the outer wall of the inner exhaust pipe is provided with a water cooling pipe, the water inlet of the water cooling pipe is connected with a water supply device, and the water outlet of the water cooling pipe is connected with a water inlet pipe.
The invention has the technical effects and advantages that:
1. according to the invention, the pressing piece and the check block are arranged, the aeroengine is firstly fixed on the rotating plate of the trolley and pushed into the test workshop, so that the rotating wheel of the trolley enters the groove of the test bed, then the aeroengine is rotated, the aeroengine drives the rotating plate to rotate, the rotating plate rotates to extrude the clamping block and the telescopic connecting rod through the pressing piece, the clamping block is inserted into the test bed after being extruded, the clamping block is used for fixing the test bed and the trolley, and the check block is finally used for fixing the trolley and the rotating plate after the telescopic connecting rod is extruded, so that the effect of rapidly connecting the aeroengine is achieved.
2. According to the invention, the air inlet mechanism and the exhaust mechanism are arranged, the air inlet of the aero-engine is used for air inlet through the inner air inlet pipe in the test process of the aero-engine, the air inlet air flow enables the centrifugal fan to rotate, the centrifugal fan rotates to enable air to enter the guide pipe under the action of the centrifugal force, and the air is blown into the test room through the guide pipe, meanwhile, the exhaust port of the aero-engine in the test process is used for exhausting through the inner exhaust pipe, the exhaust fan rotates due to the exhaust air flow, the rotating exhaust fan generates the effect of exhausting the air in the test room, and the air blowing of the air inlet mechanism and the air exhausting of the exhaust mechanism are mutually matched, so that the fluidity of the air in the test room in the test process is greatly improved, the discharge speed of the high-temperature air in the test room is accelerated, and the exhaust efficiency is improved.
3. According to the invention, the water storage tank is arranged to cool the test bed, so that the gas temperature at the bottom of the test room is reduced, low-temperature gas is formed, the surface of the engine generates high temperature when the aeroengine is used for testing, so that the gas temperature of the test room is increased, when the high-temperature gas in the test room is discharged outwards, the high-temperature gas is influenced by the gas flow and can be accumulated at the bottom of the test room, the density of the high-temperature gas in the test room is relatively lower than that of the low-temperature gas at the bottom of the test room, so that the high-temperature gas cannot be accumulated at the bottom of the test room, and the cooling effect is improved.
4. According to the invention, the diversion mechanism is arranged, high-temperature gas accumulated at the bottom of the test room is accumulated towards the top of the test room under the action of cooling of the water storage tank and acts on the diversion mechanism, meanwhile, the centrifugal fan rotates to enable external air flow of the test room to pass through the drainage tube and the diversion tube and act on the diversion plate, so that the diversion plate horizontally moves to drive the synchronous belt to rotate together with the rotating shaft, on one hand, the high-temperature gas accumulated at the top of the test room can flow to the right side under the driving of the rotating synchronous belt and the diversion plate, on the other hand, the rotating shaft rotates to enable the third fan blade to rotate, the rotating third fan blade can form a blowing effect on the external exhaust pipe, the arc-shaped diversion plate is matched with the third fan blade, the high-temperature gas accumulated at the top of the test room can be accumulated on one side first and then flows to the external exhaust pipe, and then the high-temperature gas is discharged through the exhaust fan, and the accumulation of the high-temperature gas at the top of the test room is effectively avoided.
Drawings
Fig. 1 is a schematic diagram of the overall structure of the present invention.
Fig. 2 is a cross-sectional view of the cart structure of the present invention.
Fig. 3 is an enlarged view of the structure of the portion a of fig. 2 according to the present invention.
Fig. 4 is a schematic structural view of an exhaust mechanism of the present invention.
Fig. 5 is an enlarged view of the B part structure of fig. 4 according to the present invention.
Fig. 6 is a schematic structural view of an air intake mechanism of the present invention.
Fig. 7 is an enlarged view of the C-section structure of fig. 6 according to the present invention.
Fig. 8 is an enlarged view of the D-section structure of fig. 6 according to the present invention.
Fig. 9 is a cross-sectional view of the overall structure of the present invention.
Fig. 10 is an enlarged view of the E-section structure of fig. 9 according to the present invention.
FIG. 11 is a schematic view of the structure of the outer exhaust pipe of the present invention.
The reference numerals are: 1. a test workshop; 2. a test bed; 3. a pressure sensor; 4. a cart; 5. a rotating plate; 6. an aero-engine; 7. a pressing piece; 8. a clamping block; 9. a first spring; 10. a telescopic connecting rod; 11. briquetting; 12. a second spring; 13. a stop block; 14. a connecting rod; 15. a rotating wheel; 16. a groove; 17. an air inlet mechanism; 171. an outer air inlet pipe; 172. an inner air inlet pipe; 173. a second double-sided gear; 174. a centrifugal fan; 175. a second fixing plate; 176. a second gear; 177. a second fan blade; 178. a second movable rod; 179. a flow guiding pipe; 18. an exhaust mechanism; 181. an outer exhaust pipe; 182. an inner exhaust pipe; 183. a first double-sided gear; 184. an exhaust fan; 185. a first gear; 186. a first fan blade; 187. a first fixing plate; 188. a first movable lever; 189. a deflector aperture; 19. a diversion mechanism; 191. a connecting piece; 192. a rotating shaft; 193. a synchronous belt; 194. a deflector; 195. a third gear; 196. a rotating lever; 197. a third fan blade; 198. a fourth gear; 20. a water storage tank; 201. a water inlet pipe; 202. a water outlet pipe; 203. a sealing plate; 204. a water-cooled tube; 21. a drainage tube.
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.
Example 1
Referring to the accompanying drawings 1-3 of the specification, an aeroengine ground test system of an embodiment of the invention comprises a test room 1, wherein a test bed 2 is slidingly connected in the test room 1, one side of the test bed 2 is provided with a pressure sensor 3, the pressure sensor 3 is fixedly connected in the test room 1, the top of the test bed 2 is provided with a trolley 4, the top of the trolley 4 is rotationally connected with a rotating plate 5, the top of the rotating plate 5 is fixedly connected with an aeroengine 6, the inside of the trolley 4 is slidingly connected with a pressing piece 7, the bottom of the pressing piece 7 is provided with a clamping block 8, the clamping block 8 is slidingly connected in the trolley 4, the outer wall of the clamping block 8 is fixedly connected with a first spring 9, the first spring 9 is fixedly connected in the trolley 4, the outer wall of the pressing piece 7 is hinged with a telescopic connecting rod 10, one end of the telescopic connecting rod 10 away from the pressing piece 7 is hinged with a pressing block 11, the pressing block 11 is slidingly connected in the trolley 4, the top of the pressing block 11 is fixedly connected with a second spring 12, the second spring 12 is guided through the arrangement of a guide rod in the second spring 12, the second spring 12 is prevented from being bent and inserted into the pressing block 11 and the inside of the check block 13, the top of the second spring 12 is fixedly connected with the check block 13, the number of the check blocks 13 is multiple, the spacing between the check blocks 13 is the same as the width of the rotating plate 5, after the rotating plate 5 rotates ninety degrees, the check block 13 can limit and fix the rotating plate 5, the check block 13 is inserted into the inside of the trolley 4, the outer wall of the check block 13 is fixedly connected with a connecting rod 14, the bottom of the trolley 4 is provided with a rotating wheel 15, the outer wall of the rotating wheel 15 is provided with a groove 16, the length of a horizontal straight line in the groove 16 is the same as the distance between the center lines of the two rotating wheels 15 in the same horizontal line, after the cart 4 is driven to enter the groove 16 by the rotating wheel 15, the groove 16 automatically stops the cart 4 at a proper position by the rotating wheel 15, and the stopping position of the cart 4 is not manually adjusted by a worker, so that the groove 16 is formed in the test bed 2.
It should be noted that, firstly, after fixing the aeroengine 6 on the rotating plate 5 of the cart 4, pushing the cart 4 into the test shop 1, making the rotating wheel 15 of the cart 4 enter the groove 16 of the test bed 2, then rotating the aeroengine 6, making the aeroengine 6 drive the rotating plate 5 to rotate, the rotating plate 5 rotates and presses the pressing piece 7 to descend along the interior of the cart 4, the pressing piece 7 descends and presses the clamping block 8 and the telescopic connecting rod 10, the clamping block 8 is inserted into the interior of the test bed 2 and presses the first spring 9 to shrink after being pressed, so that the clamping block 8 fixes the test bed 2 and the cart 4, preventing the cart 4 from displacing in the groove 16 of the test bed 2, the telescopic connecting rod 10 is pressed and drives the pressing block 11 to ascend along the inner wall of the cart 4 and press the second spring 12 to shrink, when the aeroengine 6 rotates ninety degrees, the air inlet and the air outlet of the aero-engine 6 are respectively aligned with the air inlet mechanism 17 and the air outlet mechanism 18, meanwhile, the aero-engine 6 rotates ninety degrees to drive the rotating plate 5 to stop limiting the stop block 13, so that the second spring 12 can extend to push the stop block 13 to rise, the stop block 13 is used for fixing between the cart 4 and the rotating plate 5 and driving the connecting rod 14 to rise, the rising of the connecting rod 14 is clamped at the bottom of the rotating plate 5 rotating ninety degrees to secondarily limit the rotating plate 5, the effect of completing quick connection of the aero-engine 6 is achieved, and the aero-engine 6 can be started to work when the aero-engine 6 is adjusted to complete test, so that the aero-engine 6 transmits thrust to the test bed 2 through the rotating plate 5 and the cart 4, the test bed 2 is used for extruding the pressure sensor 3, the pressure sensor 3 is made to measure the thrust of the aeroengine 6.
When the fixing of the test bed 2 to the cart 4 and the fixing of the cart 4 to the rotating plate 5 are required to be stopped, the connecting rod 14 can be pressed, so that the connecting rod 14 is separated from the groove at the bottom of the rotating plate 5 and drives the stop block 13 to descend, the stop block 13 descends to press the second spring 12 to shrink and stop limiting of the rotating plate 5, the rotating plate 5 can be rotationally reset, after the rotating plate 5 rotates ninety degrees to reset, the second spring 12 stretches to push the pressing block 11 to descend along the interior of the cart 4, the pressing block 11 pushes the pressing block 7 to ascend through the telescopic connecting rod 10, the pressing piece 7 stops pressing the clamping block 8, the first spring 9 stretches to push the clamping block 8 to be separated from the interior of the test bed 2, the fixing between the test bed 2 and the cart 4 is released, and the cart 4 and the rotating plate 5 are reset, so that the fixing effect is quickly removed.
Example 2
In the process of aeroengine test run, the surface of the engine generates high temperature, so that the gas temperature of a test workshop is increased, and the high-temperature gas of the test workshop cannot be quickly and effectively discharged outside in the process of aeroengine test run.
Referring to fig. 1-9 of the specification and fig. 11, based on embodiment 1, an aeroengine ground test run system of this embodiment, the air intake mechanism 17 includes an outer air intake pipe 171, one end of the outer air intake pipe 171 is fixedly connected with the outer wall of the test room 1, an inner air intake pipe 172 is arranged inside the outer air intake pipe 171, one end of the inner air intake pipe 172 is fixedly connected with the outer wall of the test room 1 and is communicated with the interior of the test room 1, the other end of the inner air intake pipe 172 is rotationally connected with a second double-sided gear 173, the outer wall of the inner air intake pipe 172 is rotationally connected with a centrifugal fan 174, the inner wall of the centrifugal fan 174 is arranged as an inner gear and is meshed with the outer teeth of the second double-sided gear 173, the inner wall of the outer air intake pipe 171 is fixedly connected with a second fixing plate 175, the bottom of the second fixing plate 175 is rotationally connected with a second movable rod 178 in a penetrating and penetrating manner, one end of the second movable rod 178 is fixedly connected with a second fan 177, and the other end of the second movable rod 178 is fixedly connected with a second gear 176, the second gear 176 is engaged with the inner teeth of the second double-sided gear 173, the exhaust mechanism 18 comprises an outer exhaust pipe 181, one end of the outer exhaust pipe 181 is fixedly connected with the outer wall of the test workshop 1 and extends into the test workshop 1, an inner exhaust pipe 182 is arranged in the outer exhaust pipe 181, one end of the inner exhaust pipe 182 is fixedly connected with the outer wall of the test workshop 1, the inner exhaust pipe 182 is communicated with the test workshop 1, the other end of the inner exhaust pipe 182 is rotationally connected with a first double-sided gear 183, the outer wall of the inner exhaust pipe 182 is rotationally connected with an exhaust fan 184, the inner wall of the exhaust fan 184 is internally provided with an inner gear and is engaged with the outer teeth of the first double-sided gear 183, the inner wall of the inner exhaust pipe 182 is fixedly connected with a first fixed plate 187, the bottom of the first fixed plate 187 is rotationally connected with a first movable rod 188, one end of the first movable rod 188 is fixedly connected with a first fan blade 186, the other end of the first movable rod 188 is fixedly connected with a first gear 185, the first gear 185 is engaged with the inner teeth of the first double-sided gear 183, a diversion hole 189 is formed in the outer wall of one side of the test room 1, the diversion hole 189 is arranged between the inner exhaust pipe 182 and the outer exhaust pipe 181, a diversion pipe 179 is arranged in the outer wall of the outer air inlet pipe 171, one end of the diversion pipe 179 is communicated with the test room 1, the other end of the diversion pipe 179 is communicated with the inner part of the outer air inlet pipe 171, a drainage pipe 21 is fixedly connected with the outer wall of the outer air inlet pipe 171, one end of the drainage pipe 21 is communicated with the diversion pipe 179, the other end of the drainage pipe 21 is communicated with the test room 1, and one end of the outer exhaust pipe 181 extending to the inner part of the test room 1 is in a horn shape.
It should be noted that, during the test and the retry of the aero-engine, the surface of the engine generates high temperature, so that the gas in the test room 1 is warmed up, meanwhile, the air inlet of the aero-engine 6 is introduced through the inner air inlet pipe 172, the air flow of the introduced air makes the second fan blade 177 rotate, the rotating second fan blade 177 can drive the second gear 176 to rotate with the second double-sided gear 173, thereby making the centrifugal fan 174 rotate, the centrifugal fan 174 rotates to drive the air flow, so that the air flow enters the guide pipe 179 under the action of the centrifugal force, and blows the air in the test room 1 through the guide pipe 179, so that the high temperature gas in the test room 1 flows to the exhaust mechanism 18, meanwhile, the exhaust port of the aero-engine 6 in the test room is exhausted through the inner exhaust pipe 182, the first fan blade 186 is enabled to rotate by the exhaust air flow, the first fan blade 186 can drive the first gear 185 to rotate together with the first double-sided gear 183, so that the exhaust fan 184 rotates, the rotating exhaust fan 184 generates an effect of exhausting air from the inside of the test room 1, and further the high-temperature air of the test room 1, which is close to the exhaust mechanism 18, can be rapidly and effectively exhausted outwards, the air blowing of the air inlet mechanism 17 and the air exhausting of the exhaust mechanism 18 are mutually matched, the flowability of the air in the test room 1 in the test process is greatly improved, the efficiency of exhausting the high-temperature air in the test room 1 to the outside is improved, one end of the outer exhaust pipe 181 in the test room 1 is in a horn shape, and the air exhausting range of the exhaust mechanism 18 is improved.
Example 3
Because the surface of the engine generates high temperature in the process of test run of the aeroengine, the gas temperature of the test workshop is increased, and the high-temperature gas in the test workshop is influenced by the air flow in the process of discharging the high-temperature gas outside, so that the high-temperature gas can be accumulated at the bottom in the test run room.
Referring to fig. 1-9 of the specification, on the basis of the above embodiment, a water storage tank 20 is arranged at the bottom of the test workshop 1, the water storage tank 20 can enable the test bench 2 to be cooled, a sealing plate 203 is fixedly connected to the top end of the water storage tank 20, a water inlet pipe 201 is arranged on one side of the water storage tank 20, a water outlet pipe 202 is arranged on the other side of the water storage tank 20, the water inlet pipe 201 and the water outlet pipe 202 are communicated with the water storage tank 20, a water cooling pipe 204 is arranged on the outer wall of the inner exhaust pipe 182, a water inlet of the water cooling pipe 204 is connected with a water supply device, and a water outlet of the water cooling pipe 204 is connected with the water inlet pipe 201.
It should be noted that, the water feeder supplies water to the water-cooled tube 204 and the tank 20, in the process of taking a test by the aero-engine 6, the water-cooled tube 204 cools the inner exhaust pipe 182, the service life of the inner exhaust pipe 182 is prolonged, the tank 20 cools the test bed 2, the gas temperature at the bottom of the test room 1 is reduced, low-temperature gas is formed, and simultaneously, the aero-engine 6 is taking a test, the surface of the engine generates high temperature, the gas temperature in the test room 1 is increased, when the high-temperature gas in the test room 1 is discharged outwards, the high-temperature gas is influenced by the air flow, the density of the high-temperature gas in the test room 1 is relatively lower than the density of the low-temperature gas at the bottom of the test room 1, so that the high-temperature gas cannot form accumulation at the bottom of the test room 1, and the cooling effect is further improved.
Example 4
However, in the process of aeroengine test run, the surface of the engine generates high temperature, so that the gas temperature of the test workshop is increased, the high-temperature gas of the test workshop is influenced by the gas flow in the process of discharging the gas outwards, the high-temperature gas can be accumulated at the bottom in the test run, the low-temperature gas influenced by the low-temperature gas can flow upwards when the high-temperature gas is accumulated at the bottom in the test run, and the high-temperature gas is accumulated at the top in the test run.
Referring to fig. 1-10 of the specification, on the basis of the above embodiment, the flow guiding mechanism 19 of the present embodiment includes a plurality of connecting members 191, the connecting members 191 are fixedly connected with the inner wall of the test workshop 1, the connecting members 191 are provided with a plurality of connecting members 191 in opposite states, rotating shafts 192 are rotatably connected between the connecting members 191, synchronous belts 193 are arranged between the adjacent rotating shafts 192, the outer wall of each synchronous belt 193 is fixedly connected with a plurality of flow guiding plates 194, two ends of one side of the rotating shafts 192 are fixedly connected with third gears 195, the top end of the inner wall of the test workshop 1 is rotatably connected with a rotating rod 196, the outer wall of the rotating rod 196 is fixedly connected with a fourth gear 198, the fourth gear 198 is meshed with the third gears 195, the bottom end of the rotating rod 196 is fixedly connected with third fan blades 197, and the flow guiding plates 194 are in an arc shape.
It should be noted that, when the aeroengine 6 performs a test, the high-temperature gas accumulated at the bottom of the test room 1 is accumulated towards the top of the test room 1 under the action of the cooling of the water storage tank 20 and acts on the diversion mechanism 19, meanwhile, during the test, the centrifugal fan 174 rotates to enable the external airflow of the test room 1 to pass through the drainage tube 21 and the diversion tube 179 and act on the diversion plate 194, and then the diversion plate 194 moves horizontally, the diversion plate 194 moves horizontally to drive the synchronous belt 193 and the rotation shaft 192 together, on one hand, the high-temperature gas accumulated at the top of the test room 1 is driven by the synchronous belt 193 and the diversion plate 194 in rotation, the high-temperature gas acting on the diversion mechanism 19 flows rightwards under the action of the arc diversion plate 194, on the other hand, the rotation shaft 192 can drive the third gear 195 to rotate, the third gear 195 to drive the fourth gear 198 to rotate together, so that the third fan 197 rotates, the third fan 197 can generate an air blowing effect, the third fan 197 blows towards the position of the air exhaust pipe 181, and the arc diversion plate 194 cooperates with the third fan 197, so that the high-temperature gas accumulated at the top of the test room 1 is prevented from flowing out of the side of the test room 181, and then the high-temperature gas is prevented from being accumulated at the top of the test room 1.
The foregoing description of the preferred embodiments of the invention is not intended to limit the invention to the precise form disclosed, and any such modifications, equivalents, and alternatives falling within the spirit and principles of the invention are intended to be included within the scope of the invention.
Claims (10)
1. The utility model provides an aeroengine ground test system, includes the test workshop, its characterized in that, the inside sliding connection of test workshop has the test bench, one side of test bench is provided with pressure sensor, pressure sensor fixed connection is in the inside of test workshop, the top of test bench is provided with the shallow, the top of shallow is rotated and is connected with the revolving board, the top fixedly connected with aeroengine of revolving board, the inside sliding connection of shallow has the casting die, the bottom of casting die is provided with the fixture block, fixture block sliding connection is in the inside of shallow, the outer wall fixedly connected with first spring of fixture block, first spring fixed connection is in the inside of shallow, the outer wall of casting die articulates there is the expansion link, the one end that the casting die was kept away from to the expansion link articulates there is the briquetting, briquetting sliding connection is in the inside of shallow, the top fixedly connected with second spring of briquetting, the top fixedly connected with dog, the outer wall fixedly connected with connecting rod of dog, the bottom of shallow is provided with the casting die, the recess is provided with the air guide mechanism in the inside of test workshop, the air guide mechanism is connected with the inside of test workshop, the air guide mechanism is fixedly connected with the inside the test workshop;
the dog quantity sets up to a plurality of, and the interval between the dog is the same setting with the width of rotating the board, after the rotating board was rotatory ninety degrees, the dog can carry out spacing fixed to the rotating board.
2. An aircraft engine ground test run system according to claim 1, wherein: the air inlet mechanism comprises an outer air inlet pipe, an inner air inlet pipe is arranged inside the outer air inlet pipe, the outer air inlet pipe and the inner air inlet pipe are connected with the outer wall of the test room and are communicated with the inner part of the test room, and the other end of the inner air inlet pipe is rotationally connected with a second double-sided gear.
3. An aircraft engine ground test run system according to claim 2, wherein: the centrifugal fan is connected to the outer wall of the inner air inlet pipe in a rotating mode, the inner wall of the centrifugal fan is provided with an inner gear and meshed with the outer teeth of the second double-sided gear, the inner wall of the outer air inlet pipe is fixedly connected with a second fixing plate, a second movable rod penetrates through the bottom of the second fixing plate and is connected with the bottom of the second fixing plate in a rotating mode, one end of the second movable rod is fixedly connected with a second fan blade, the other end of the second movable rod is fixedly connected with a second gear, and the second gear is meshed with the inner teeth of the second double-sided gear.
4. An aircraft engine ground test run system according to claim 1, wherein: the exhaust mechanism comprises an outer exhaust pipe, one end of the outer exhaust pipe is fixedly connected with the outer wall of the test room and extends to the inside of the test room, an inner exhaust pipe is arranged in the outer exhaust pipe, one end of the inner exhaust pipe is fixedly connected with the outer wall of the test room, the inner exhaust pipe is communicated with the test room, and the other end of the inner exhaust pipe is rotationally connected with a first double-sided gear.
5. An aircraft engine ground test run system according to claim 4, wherein: the inner exhaust pipe outer wall rotates and is connected with the air discharge fan, the inner wall of air discharge fan is the internal gear setting, and with the external tooth meshing of first double-sided gear, the inner wall fixedly connected with first fixed plate of inner exhaust pipe, first fixed plate bottom rotates and is connected with first movable rod, first movable rod one end fixedly connected with first flabellum, first movable rod other end fixedly connected with first gear, first gear and first double-sided gear internal tooth meshing.
6. An aircraft engine ground test run system according to claim 5, wherein: the outer wall of one side of the test workshop is provided with a diversion hole, and the diversion hole is arranged between the inner exhaust pipe and the outer exhaust pipe.
7. An aircraft engine ground test run system according to claim 3, wherein: the outer air inlet pipe outer wall is inside to be equipped with the honeycomb duct, honeycomb duct one end and test room intercommunication, the honeycomb duct other end and the inside intercommunication of outer air inlet pipe, outer air inlet pipe outer wall fixedly connected with drainage tube, drainage tube one end and honeycomb duct intercommunication, the drainage tube other end and test room intercommunication.
8. An aircraft engine ground test run system according to claim 1, wherein: the water storage tank is characterized in that a sealing plate is fixedly connected to the top end of the water storage tank, a water inlet pipe is arranged on one side of the water storage tank, a water outlet pipe is arranged on the other side of the water storage tank, and the water inlet pipe and the water outlet pipe are communicated with the water storage tank.
9. An aircraft engine ground test run system according to claim 1, wherein: the guide mechanism comprises a plurality of connecting pieces, the connecting pieces are fixedly connected with the inner wall of a test workshop, the connecting pieces are provided with a plurality of connecting pieces in opposite states, a rotating shaft is connected between the connecting pieces in a rotating mode, a synchronous belt is arranged between the rotating shafts, a plurality of guide plates are fixedly connected to the outer wall of the synchronous belt, one side of the guide plates is fixedly connected with a third gear at two ends of the rotating shaft, a rotating rod is connected to the top end of the inner wall of the test workshop in a rotating mode, a fourth gear is fixedly connected to the outer wall of the rotating rod, the fourth gear is meshed with the third gear, a third fan blade is fixedly connected to the bottom end of the rotating rod, and the guide plates are in arc-shaped arrangement.
10. An aircraft engine ground test run system according to claim 4, wherein: the one end that outer blast pipe extended to the test room is loudspeaker form setting, interior blast pipe outer wall is equipped with the water-cooling pipe, the water inlet and the water supply ware of water-cooling pipe are connected, the delivery port and the inlet tube connection of water-cooling pipe.
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Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20090020904A (en) * | 2007-08-24 | 2009-02-27 | 서성은 | Tester jig apparatus of common rail injector for internal combustion engine |
| JP2011080953A (en) * | 2009-10-09 | 2011-04-21 | Ud Trucks Corp | Support device for rotating object |
| CN203606134U (en) * | 2013-10-30 | 2014-05-21 | 中国南方航空工业(集团)有限公司 | Aircraft engine test bed frame |
| CN110320046A (en) * | 2018-12-11 | 2019-10-11 | 中国航空工业集团公司北京长城计量测试技术研究所 | Aircraft engine test stand mock-up and working method |
| CN209606089U (en) * | 2019-05-08 | 2019-11-08 | 山西圣美克科技股份有限公司 | A kind of piston engine ground run auxiliary device |
| CN209820773U (en) * | 2018-12-13 | 2019-12-20 | 中科航空动力(株洲)装备制造研究院有限公司 | Turbojet engine test bed system |
| CN110763472A (en) * | 2019-12-02 | 2020-02-07 | 北京航天三发高科技有限公司 | Engine test bed and test method thereof |
| CN211163589U (en) * | 2019-07-18 | 2020-08-04 | 重庆宗申航空发动机制造有限公司 | Engine transfer device and engine transfer support quick positioning mechanism |
| CN214309486U (en) * | 2021-03-20 | 2021-09-28 | 杭州克罗德机电设备有限公司 | Pressing device of engine quick-mounting trolley |
| CN113686583A (en) * | 2021-10-27 | 2021-11-23 | 南通诺林金属新材料科技有限公司 | Rocket engine thrust measurement rack of high accuracy |
| CN114755018A (en) * | 2022-04-07 | 2022-07-15 | 中国科学院工程热物理研究所 | High-altitude simulation test device and test method for turbojet turbofan engine |
| CN115165247A (en) * | 2022-06-30 | 2022-10-11 | 安徽格楠机械有限公司 | Turbofan engine bearing seal dynamic test bench |
| CN115436065A (en) * | 2022-11-08 | 2022-12-06 | 中国航发四川燃气涡轮研究院 | Multifunctional rack for aircraft engine test bed |
| CN116046402A (en) * | 2023-02-13 | 2023-05-02 | 湖南冬达实验设备有限公司 | Automobile engine operational environment simulation device |
| CN218994731U (en) * | 2022-12-28 | 2023-05-09 | 杭州纳冠华兴自动化科技有限公司 | Power output testing device for assembled engine power assembly |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE60330196D1 (en) * | 2003-12-12 | 2009-12-31 | Hirata Spinning | TEST DEVICE OF MOTOR DRIVE |
-
2023
- 2023-10-23 CN CN202311371116.1A patent/CN117109929B/en active Active
Patent Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20090020904A (en) * | 2007-08-24 | 2009-02-27 | 서성은 | Tester jig apparatus of common rail injector for internal combustion engine |
| JP2011080953A (en) * | 2009-10-09 | 2011-04-21 | Ud Trucks Corp | Support device for rotating object |
| CN203606134U (en) * | 2013-10-30 | 2014-05-21 | 中国南方航空工业(集团)有限公司 | Aircraft engine test bed frame |
| CN110320046A (en) * | 2018-12-11 | 2019-10-11 | 中国航空工业集团公司北京长城计量测试技术研究所 | Aircraft engine test stand mock-up and working method |
| CN209820773U (en) * | 2018-12-13 | 2019-12-20 | 中科航空动力(株洲)装备制造研究院有限公司 | Turbojet engine test bed system |
| CN209606089U (en) * | 2019-05-08 | 2019-11-08 | 山西圣美克科技股份有限公司 | A kind of piston engine ground run auxiliary device |
| CN211163589U (en) * | 2019-07-18 | 2020-08-04 | 重庆宗申航空发动机制造有限公司 | Engine transfer device and engine transfer support quick positioning mechanism |
| CN110763472A (en) * | 2019-12-02 | 2020-02-07 | 北京航天三发高科技有限公司 | Engine test bed and test method thereof |
| CN214309486U (en) * | 2021-03-20 | 2021-09-28 | 杭州克罗德机电设备有限公司 | Pressing device of engine quick-mounting trolley |
| CN113686583A (en) * | 2021-10-27 | 2021-11-23 | 南通诺林金属新材料科技有限公司 | Rocket engine thrust measurement rack of high accuracy |
| CN114755018A (en) * | 2022-04-07 | 2022-07-15 | 中国科学院工程热物理研究所 | High-altitude simulation test device and test method for turbojet turbofan engine |
| CN115165247A (en) * | 2022-06-30 | 2022-10-11 | 安徽格楠机械有限公司 | Turbofan engine bearing seal dynamic test bench |
| CN115436065A (en) * | 2022-11-08 | 2022-12-06 | 中国航发四川燃气涡轮研究院 | Multifunctional rack for aircraft engine test bed |
| CN218994731U (en) * | 2022-12-28 | 2023-05-09 | 杭州纳冠华兴自动化科技有限公司 | Power output testing device for assembled engine power assembly |
| CN116046402A (en) * | 2023-02-13 | 2023-05-02 | 湖南冬达实验设备有限公司 | Automobile engine operational environment simulation device |
Non-Patent Citations (1)
| Title |
|---|
| 航空发动机高转速轴承高效收油环下润滑技术研究;覃经文;中南大学;第61-74页 * |
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