CN117848709B - Device and method for testing turbine rotor over-rotation of ultra-high revolution aero-engine - Google Patents
Device and method for testing turbine rotor over-rotation of ultra-high revolution aero-engine Download PDFInfo
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- CN117848709B CN117848709B CN202410265164.0A CN202410265164A CN117848709B CN 117848709 B CN117848709 B CN 117848709B CN 202410265164 A CN202410265164 A CN 202410265164A CN 117848709 B CN117848709 B CN 117848709B
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- 238000012360 testing method Methods 0.000 title claims abstract description 45
- 238000000034 method Methods 0.000 title claims abstract description 8
- 230000007246 mechanism Effects 0.000 claims description 168
- 238000005520 cutting process Methods 0.000 claims description 92
- 238000010521 absorption reaction Methods 0.000 claims description 68
- 238000002474 experimental method Methods 0.000 claims description 45
- 230000000903 blocking effect Effects 0.000 claims description 14
- 238000005096 rolling process Methods 0.000 claims description 7
- 238000013480 data collection Methods 0.000 claims description 3
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- 230000005540 biological transmission Effects 0.000 description 2
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- 238000010998 test method Methods 0.000 description 2
- 241000883990 Flabellum Species 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
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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
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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Abstract
The invention discloses a turbine rotor overrun testing device and method of an ultra-high revolution aeroengine, and belongs to the technical field of aero experimental equipment. The invention can ensure the stability of the engine rotor after the experimental shaft is cut off, and effectively protects the experimental device.
Description
Technical Field
The invention belongs to the technical field of aviation experiment equipment, and particularly relates to a device and a method for testing the over-rotation of a turbine rotor of an ultra-high-revolution aero-engine.
Background
An ultra high revolution aeroengine turbine rotor refers to a turbine component for an aeroengine having a very high rotational speed. Turbine rotors are a key component in aircraft engines, in which they are subjected to greater centrifugal forces and vibrations, and therefore, higher demands are placed on material strength, dynamic balance, aerodynamic properties, etc. In order to improve the power and the efficiency of the engine, the design of the turbine rotor of the ultra-high-revolution aeroengine becomes a development trend. The design and manufacture of ultra-high revolution aero-engine turbine rotors requires the use of advanced materials, machining techniques and simulation analysis methods to ensure stable and reliable operation at high rotational speeds. Meanwhile, the over-rotation test of the turbine rotor is an important means for verifying the performance and safety of the turbine rotor, and important parameters can be provided for the optimal design and use of the engine.
The turbine rotor of an ultra-high revolution aeroengine is subjected to greater centrifugal forces and vibrations during operation, which may cause the turbine rotor to crack or separate if the rotational speed exceeds a certain range. If the non-containment situation occurs, high-speed and high-energy fragments fly out through the casing, so that a cabin, an oil tank, a hydraulic pipeline, a control circuit and the like of an airplane can be damaged, the cabin is out of pressure, the oil tank leaks and fires, the control failure and other secondary damages are caused, the flight safety is seriously endangered, in order to avoid the occurrence of flight safety accidents, whether the oversteer protection function of a control system of the engine meets the design requirement is verified under the condition that the engine needs to truly oversteer, and meanwhile, the containment of the engine when the protection function is invalid is verified. In the traditional test, the output transmission shaft of the engine is usually directly cut off to simulate the real over-rotation condition of the engine, and as the rotating speed of the rotor is very fast during cutting, the mode can cause overlarge swinging of the rotor after the output shaft is cut off, the engine and experimental devices can be damaged, the experimental risk is very high, a transmission shaft is required to be cut off in each experiment, and the experimental cost is too high.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide a device and a method for testing the over-rotation of the turbine rotor of the ultra-high-revolution aeroengine.
The technical scheme adopted for solving the technical problems is as follows: the utility model provides an ultra-high revolution aeroengine turbine rotor overstroke testing arrangement, includes experiment platform, aeroengine, experimental axle, power absorption mechanism, collection fan mechanism, shutdown mechanism, first supporting part and second supporting part, the experiment platform is fixed to be set up subaerial, aeroengine is fixed to be set up in experiment platform one end, power absorption mechanism sliding connection is at the experiment platform other end, experimental axle one end and engine rotor fixed connection, experimental axle other end and power absorption mechanism pivot fixed connection, collection fan mechanism is fixed to be set up in power absorption mechanism front side, shutdown mechanism is fixed to be set up in collection fan mechanism front side, first supporting part is fixed to be set up on experiment platform, second supporting part is fixed to be set up in collection fan mechanism;
the aeroengine is provided with a data collection component;
the wind collecting mechanism is sleeved on the experimental shaft, and the two cutting mechanisms are symmetrically arranged above and below the experimental shaft;
the first supporting component and the second supporting component are sleeved on the experimental shaft.
Through the technical scheme, the aero-engine can be fixedly arranged on the experimental platform, the engine rotor can be connected with the power absorption mechanism through the experimental shaft, the power absorption mechanism is slidably connected on the experimental platform, the cutting mechanism can cut off the experimental shaft and simulate the real over-rotation condition of the engine rotor, the power absorption mechanism can slide towards the direction away from the aero-engine after the experimental shaft is cut off, the testing devices such as the power absorption mechanism are effectively protected, meanwhile, the power absorption mechanism is far away from the testing device to vacate the position for the aero-engine, the air inflow of the aero-engine is increased, the over-rotation of the engine rotor is fully ensured, the experimental accuracy is improved, the cut-off experimental shaft is supported by the first supporting component and the second supporting component, the engine rotor and the power absorption mechanism are fully protected, the swing of the engine rotor is prevented, and the aero-engine is protected under the condition of ensuring the experimental accuracy.
Further, the experiment axle includes power output shaft, first connecting axle, cuts off axle, second connecting axle, power output shaft one end and engine rotor fixed connection, the power output shaft other end and first connecting axle fixed connection, first connecting axle one end and power output shaft fixed connection, the first connecting axle other end and cut off axle fixed connection, cut off axle one end and first connecting axle fixed connection, the cut off axle other end and second connecting axle fixed connection, second connecting axle one end and cut off axle fixed connection, the second connecting axle other end and power absorption mechanism pivot fixed connection.
Through above-mentioned technical scheme, because power take off shaft one end and engine rotor fixed connection, the power take off shaft other end and first connecting axle fixed connection, first connecting axle one end and power take off shaft fixed connection, the first connecting axle other end and the axle fixed connection that cuts off, it is fixed connection with first connecting axle to cut off axle one end, it is fixed connection with the second connecting axle to cut off the axle other end, second connecting axle one end and cutting off axle fixed connection, the second connecting axle other end and power absorption mechanism pivot fixed connection, make experimental axle and engine rotor and power absorption mechanism be connected conveniently, and during the test, only need cut off the axle and can simulate real engine rotor and surpass the condition, it can conveniently change to cut off the axle, effectively reduce experimental cost.
Further, the first connecting shaft is rotationally connected with the first supporting component, the second connecting shaft is rotationally connected with the second supporting component, and the cutting mechanism is symmetrically arranged above and below the cutting shaft.
Further, the wind collecting mechanism comprises a wind collecting cover, an electric push-pull rod, a connecting plate and a plugging plate, an air inlet is formed in one side, close to the power absorbing mechanism, of the wind collecting cover, an air outlet is formed in one side, far away from the power absorbing mechanism, of the wind collecting cover, the electric push-pull rod is symmetrically and fixedly connected to the top and the bottom of the wind collecting cover, the plugging plate is in interference fit with the air outlet, the connecting plate is fixedly connected to one side, close to the power absorbing mechanism, of the wind collecting cover, the wind collecting cover is fixedly connected with the power absorbing mechanism through the connecting plate, a second connecting shaft is rotatably connected in the wind collecting cover, a plurality of fan blades are symmetrically and fixedly connected to one side, close to the air inlet, of the second connecting shaft, and the second supporting part is fixedly connected to one side, close to the air outlet, of the wind collecting cover.
Through above-mentioned technical scheme, because second connecting axle is close to air intake one side symmetry fixedly connected with a plurality of flabellums for during the test, the second connecting axle can be rotatory at a high speed along with engine rotor, can blow air for the air collecting mechanism.
Further, the front end of the electric push-pull rod is fixedly connected with a first inclined block, and the rear side of the first inclined block on the electric push-pull rod is fixedly connected with a push rod.
Further, the top and the bottom of the plugging plate are fixedly provided with pushing plates, clamping holes are formed in the pushing plates, and the pushing rods can be clamped in the clamping holes.
Through the technical scheme, since the electric push-pull rods are symmetrically and fixedly connected to the top and the bottom of the wind collecting cover, the push rods are fixedly connected to the rear sides of the first inclined blocks on the electric push-pull rods, the blocking plates are in interference fit with the air outlets, the push plates are fixedly arranged on the top and the bottom of the blocking plates, the blocking holes are formed in the push plates, the push rods can be blocked in the blocking holes, when the electric push-pull rods are pushed forwards, the blocking plates can be pulled out, the air outlets on the wind collecting cover are exposed, and air in the wind collecting cover is sprayed out from the air outlets.
Further, the cutting mechanism comprises a cutter seat, a cutter and a limiting spring, wherein the cutter seat is symmetrically and fixedly connected to the front side of the wind collecting cover, the cutter is slidably connected to the cutter seat, the top of the cutter is fixedly connected with a second inclined block, the cutter is sleeved with the limiting spring, the bottom of the limiting spring is fixedly connected with the cutter, and the top of the limiting spring is fixedly connected with the top of the cutter seat.
According to the technical scheme, the cutting mechanism is symmetrically arranged above and below the cutting shaft, the top and the bottom of the wind collecting cover are symmetrically and fixedly connected with the electric push-pull rod, the front end of the electric push-pull rod is fixedly connected with the first inclined block, the cutter is slidably connected in the cutter holder, the top of the cutter is fixedly connected with the second inclined block, the cutter is sleeved with the limiting spring, the bottom of the limiting spring is fixedly connected with the cutter, the top of the limiting spring is fixedly connected with the top of the cutter holder, when the electric push-pull rod is pushed forwards, the first inclined block extrudes the second inclined block, the cutter slides towards the cutting shaft, then the cutter cuts off the cutting shaft, and the engine rotor is disconnected with the power absorbing mechanism, so that the over-rotation condition of the real engine rotor is simulated;
At this moment, the plugging plate is pulled out, the air outlet on the air collecting cover is exposed, air in the air collecting cover is sprayed out from the air outlet, and the power absorption mechanism can slide in the direction away from the aeroengine, so that the air collecting mechanism and the cutting mechanism are driven to be away from the aeroengine, and the test device is effectively protected.
Further, the experiment platform is provided with the slide rail near power absorption mechanism one end, power absorption mechanism bottom is provided with the spout, power absorption mechanism passes through spout and slide rail sliding connection, slide rail top display distributes has a plurality of mounting grooves, the mounting groove swivelling joint has the roller bearing.
Through above-mentioned technical scheme, because experiment platform is close to power absorption mechanism one end and is provided with the slide rail, power absorption mechanism bottom is provided with the spout, and power absorption mechanism passes through spout and slide rail sliding connection, and slide rail top display distribution has a plurality of mounting grooves, and the mounting groove internal rotation is connected with the roller bearing for power absorption mechanism becomes rolling friction with the slide rail on the experiment platform by sliding friction, effectively reduces the frictional force of power absorption mechanism and slide rail, makes things convenient for power absorption mechanism to keep away from aeroengine, effectively protects testing arrangement.
The turbine rotor over-rotation test method of the ultra-high revolution aero-engine comprises the following steps of:
Fixing an aeroengine on an experimental platform, correctly installing an engine rotor in the aeroengine, connecting a data collecting component, starting the data collecting component, and detecting before testing;
Step two, fixedly connecting an engine rotor with a power output shaft, fixedly connecting the power output shaft with a first connecting shaft, fixedly connecting the first connecting shaft with a cutting shaft, and installing the first connecting shaft in a first supporting part;
Pushing the power absorption mechanism in place, enabling the cutting mechanism to be opposite to the cutting shaft, fixedly connecting the cutting shaft with the second connecting shaft, installing the second connecting shaft in the second supporting part, and fixedly connecting the other end of the second connecting shaft with the rotating shaft of the power absorption mechanism;
Resetting the electric push-pull rod, and clamping the plugging plate on an air outlet of the air collecting cover;
step five, starting the aero-engine to drive the engine rotor to rotate;
Step six, gradually increasing the rotating speed of the engine rotor, and continuously recording and monitoring data parameters;
Step seven, the power of the aero-engine is started to the maximum, at the moment, an electric push-pull rod is started, the electric push-pull rod is pushed forward, a cutter on the cutting mechanism is driven to slide towards the cutting shaft, and the cutter cuts off the cutting shaft;
Step eight, the blocking plate is pulled open by the electric push-pull rod at the moment, so that an air outlet on the air collecting cover is exposed, fan blades on the second connecting shaft always rotate at a high speed along with the engine rotor, after the air outlet is exposed, air flow is sprayed out of the air outlet to drive the power absorbing mechanism, the air collecting cover and the cutting mechanism to slide in the direction away from the aeroengine, the engine rotor simulates real over-rotation condition at the moment, test parameter data are analyzed, and over-rotation performance of the engine rotor is estimated.
The beneficial effects of the invention are as follows:
(1) According to the invention, the aeroengine can be fixedly arranged on the experimental platform, the engine rotor can be connected with the power absorption mechanism through the experimental shaft, the power absorption mechanism is slidably connected on the experimental platform, the cutting mechanism can cut off the experimental shaft to simulate the real over-rotation condition of the engine rotor, the power absorption mechanism can slide far away from the aeroengine after the experimental shaft is cut off, test devices such as the power absorption mechanism and the like are effectively protected, meanwhile, the power absorption mechanism can be kept away from the aeroengine to vacate the position, the air inflow of the aeroengine is increased, the over-rotation of the engine rotor is fully ensured, the experimental accuracy is improved, the cut-off experimental shaft is supported by the first supporting component and the second supporting component, the engine rotor and the power absorption mechanism are fully protected, the swing of the engine rotor is prevented, and the aeroengine is protected under the condition of ensuring the experimental accuracy;
(2) According to the invention, the second connecting shaft can rotate at a high speed along with the engine rotor, air can be blown into the air collecting mechanism, the electric push-pull rod is pushed forward, the first inclined block extrudes the second inclined block, so that the cutter slides towards the cutting shaft, the cutting shaft is cut off by the cutter, the engine rotor is disconnected with the power absorbing mechanism, so that the real engine rotor overrun condition is simulated, at the moment, the blocking plate is pulled out along with the pushing of the electric push-pull rod, the air outlet on the air collecting cover is exposed, the air in the air collecting cover is sprayed out from the air outlet, the power absorbing mechanism can slide towards a direction far away from the aeroengine, the air collecting mechanism and the cutting mechanism are driven to be far away from the aeroengine, the effective protection testing device is realized, the cutting mechanism can simulate the real engine rotor overrun condition only by cutting the cutting shaft, the cutting shaft can be replaced conveniently, and the experiment cost is reduced effectively;
(3) According to the invention, the sliding rail is arranged at one end of the experiment platform, which is close to the power absorption mechanism, the sliding groove is arranged at the bottom of the power absorption mechanism, the power absorption mechanism is in sliding connection with the sliding rail through the sliding groove, the plurality of mounting grooves are arranged at the top of the sliding rail in a displaying way, and the rolling shafts are rotationally connected in the mounting grooves, so that the sliding friction between the power absorption mechanism and the sliding rail on the experiment platform is changed into rolling friction, the friction force between the power absorption mechanism and the sliding rail is effectively reduced, the power absorption mechanism is conveniently far away from an aeroengine, and the testing device is effectively protected.
Drawings
FIG. 1 is a schematic view of a first view angle structure of a turbine rotor over-rotation testing device for an ultra-high revolution aeroengine according to the present invention;
FIG. 2 is a schematic view of a turbine rotor overstroke testing apparatus for an ultra-high revolution aircraft engine according to a second perspective of the present invention;
FIG. 3 is a schematic structural view of an experimental shaft of an ultra-high revolution aero-engine turbine rotor over-rotation testing device of the present invention;
FIG. 4 is a schematic view of a first view angle configuration of a wind collecting mechanism and a cutoff mechanism of an ultra-high revolution aero-engine turbine rotor over-rotation testing device of the present invention;
FIG. 5 is a schematic view of a second view of the wind collecting mechanism and cutoff mechanism of the ultra-high revolution aero-engine turbine rotor over-rotation testing device of the present invention;
FIG. 6 is a schematic structural view of a shutoff plate of an ultra-high revolution aero-engine turbine rotor over-rotation testing device of the present invention;
FIG. 7 is a schematic diagram of an exploded construction of a cutoff mechanism of an ultra-high revolution aero-engine turbine rotor over-rotation testing device of the present invention;
FIG. 8 is an enlarged view of a portion of the ultra-high revolution aero-engine turbine rotor over-rotation test apparatus of the present invention at A in FIG. 1;
FIG. 9 is a schematic structural view of an experimental platform of an ultra-high revolution aero-engine turbine rotor over-rotation testing device of the present invention;
FIG. 10 is an enlarged view of a portion of the ultra-high revolution aero-engine turbine rotor over-rotation testing apparatus of the present invention at B in FIG. 9.
Reference numerals: 1. an experiment platform; 2. an aero-engine; 3. an experimental shaft; 4. a power absorbing mechanism; 5. a wind collecting mechanism; 6. a cutting mechanism; 7. a first support member; 8. a second support member; 11. a slide rail; 111. a roller; 31. a power output shaft; 32. a first connecting shaft; 33. cutting off the shaft; 34. a second connecting shaft; 341. a fan blade; 51. a wind collecting hood; 52. an electric push-pull rod; 53. an air inlet; 54. a connecting plate; 55. an air outlet; 56. a plugging plate; 521. a first sloping block; 522. a push rod; 561. a push plate; 61. a tool apron; 62. a cutter; 63. a limit spring; 621. and a second sloping block.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
In the description of the present invention, it should be noted that the positional or positional relationship indicated by the terms such as "upper", "lower", "inner", "outer", "top/bottom", etc. are based on the positional or positional relationship shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
1-2 And 5, the ultra-high revolution aero-engine turbine rotor over-rotation testing device comprises an experiment platform 1, an aero-engine 2, an experiment shaft 3, a power absorption mechanism 4, a wind collecting mechanism 5, a cutting mechanism 6, a first supporting component 7 and a second supporting component 8, wherein the experiment platform 1 is fixedly arranged on the ground, the aero-engine 2 is fixedly arranged at one end of the experiment platform 1, the power absorption mechanism 4 is slidably connected at the other end of the experiment platform 1, one end of the experiment shaft 3 is fixedly connected with an engine rotor, the other end of the experiment shaft 3 is fixedly connected with a rotating shaft of the power absorption mechanism 4, the wind collecting mechanism 5 is fixedly arranged at the front side of the power absorption mechanism 4, the cutting mechanism 6 is fixedly arranged at the front side of the wind collecting mechanism 5, the first supporting component 7 is fixedly arranged on the experiment platform 1, and the second supporting component 8 is fixedly arranged in the wind collecting mechanism 5;
The aeroengine 2 is provided with a data collection component;
the wind collecting mechanism 5 is sleeved on the experiment shaft 3, and the cutting mechanism 6 is symmetrically arranged above and below the experiment shaft 3;
The first support part 7 and the second support part 8 are sleeved on the experiment shaft 3.
In this embodiment, the aero-engine 2 can be fixedly installed on the experiment platform 1, the engine rotor can be connected with the power absorbing mechanism 4 through the experiment shaft 3, and the power absorbing mechanism 4 is slidably connected on the experiment platform 1, the cutting mechanism 6 can cut off the experiment shaft 3, simulate the real over-rotation condition of the engine rotor, and the power absorbing mechanism 4 can slide towards the direction far away from the aero-engine 2 after the experiment shaft 3 is cut off, so that the testing devices such as the power absorbing mechanism 4 are effectively protected, meanwhile, the power absorbing mechanism 4 is far away from the aero-engine 2 to vacate the position, the air inflow of the aero-engine 2 is increased, the over-rotation of the engine rotor is fully ensured, the accuracy of the experiment is improved, and the cut-off experiment shaft 3 is supported by the first supporting component 7 and the second supporting component 8, so that the engine rotor and the power absorbing mechanism 4 are fully protected, the swing of the engine rotor is prevented, and the aero-engine 2 is protected under the condition of ensuring the experimental accuracy.
As shown in fig. 3, the experimental shaft 3 includes a power output shaft 31, a first connecting shaft 32, a cutting shaft 33, and a second connecting shaft 34, one end of the power output shaft 31 is fixedly connected with the engine rotor, the other end of the power output shaft 31 is fixedly connected with the first connecting shaft 32, one end of the first connecting shaft 32 is fixedly connected with the power output shaft 31, the other end of the first connecting shaft 32 is fixedly connected with the cutting shaft 33, one end of the cutting shaft 33 is fixedly connected with the first connecting shaft 32, the other end of the cutting shaft 33 is fixedly connected with the second connecting shaft 34, one end of the second connecting shaft 34 is fixedly connected with the cutting shaft 33, and the other end of the second connecting shaft 34 is fixedly connected with the rotating shaft of the power absorbing mechanism 4.
In this embodiment, since one end of the power output shaft 31 is fixedly connected with the engine rotor, the other end of the power output shaft 31 is fixedly connected with the first connecting shaft 32, one end of the first connecting shaft 32 is fixedly connected with the power output shaft 31, the other end of the first connecting shaft 32 is fixedly connected with the cutting shaft 33, one end of the cutting shaft 33 is fixedly connected with the first connecting shaft 32, the other end of the cutting shaft 33 is fixedly connected with the second connecting shaft 34, one end of the second connecting shaft 34 is fixedly connected with the cutting shaft 33, and the other end of the second connecting shaft 34 is fixedly connected with the rotating shaft of the power absorption mechanism 4, so that the experimental shaft 3 is conveniently connected with the engine rotor and the power absorption mechanism 4, and during testing, the actual over-rotation condition of the engine rotor can be simulated only by cutting the cutting shaft 33, the cutting shaft 33 can be conveniently replaced, and the experimental cost is effectively reduced.
As shown in fig. 1 to 8, the first connecting shaft 32 is rotatably connected to the first supporting member 7, the second connecting shaft 34 is rotatably connected to the second supporting member 8, and the cutting mechanism 6 is symmetrically disposed above and below the cutting shaft 33;
The wind collecting mechanism 5 comprises a wind collecting cover 51, an electric push-pull rod 52, a connecting plate 54 and a blocking plate 56, an air inlet 53 is formed in one side, close to the power absorbing mechanism 4, of the wind collecting cover 51, an air outlet 55 is formed in one side, far away from the power absorbing mechanism 4, of the wind collecting cover 51, the electric push-pull rod 52 is symmetrically and fixedly connected to the top and the bottom of the wind collecting cover 51, the blocking plate 56 is in interference fit with the air outlet 55, a connecting plate 54 is fixedly connected to one side, close to the power absorbing mechanism 4, of the wind collecting cover 51, the wind collecting cover 51 is fixedly connected with the power absorbing mechanism 4 through the connecting plate 54, a second connecting shaft 34 is rotatably connected in the wind collecting cover 51, a plurality of fan blades 341 are symmetrically and fixedly connected to one side, close to the air inlet 53, of the second supporting part 8 is fixedly connected to one side, close to the air outlet 55, of the wind collecting cover 51;
the front end of the electric push-pull rod 52 is fixedly connected with a first inclined block 521, and the rear side of the first inclined block 521 on the electric push-pull rod 52 is fixedly connected with a push rod 522;
push plates 561 are fixedly arranged at the top and the bottom of the plugging plate 56, clamping holes are formed in the push plates 561, and push rods 522 can be clamped in the clamping holes;
the cutting mechanism 6 comprises a cutter seat 61, a cutter 62 and a limiting spring 63, wherein the cutter seat 61 is symmetrically and fixedly connected to the front side of the wind collecting cover 51, the cutter 62 is slidably connected in the cutter seat 61, the top of the cutter 62 is fixedly connected with a second inclined block 621, the cutter 62 is sleeved with the limiting spring 63, the bottom of the limiting spring 63 is fixedly connected with the cutter 62, and the top of the limiting spring 63 is fixedly connected with the top of the cutter seat 61.
In this embodiment, since the second connecting shaft 34 is symmetrically and fixedly connected with the plurality of fan blades 341 near the air inlet 53, the second connecting shaft 34 can rotate with the rotor of the engine at a high speed during testing, and can blow air into the air collecting mechanism 5;
Because the cutting mechanism 6 is symmetrically arranged above and below the cutting shaft 33, the top and the bottom of the wind collecting cover 51 are symmetrically and fixedly connected with the electric push-pull rod 52, the front end of the electric push-pull rod 52 is fixedly connected with the first inclined block 521, the cutter 62 is slidingly connected in the cutter seat 61, the top of the cutter 62 is fixedly connected with the second inclined block 621, the cutter 62 is sleeved with the limiting spring 63, the bottom of the limiting spring 63 is fixedly connected with the cutter 62, and the top of the limiting spring 63 is fixedly connected with the top of the cutter seat 61, so that when the electric push-pull rod 52 is pushed forwards, the first inclined block 521 presses the second inclined block 621, the cutter 62 slides towards the cutting shaft 33, and then the cutter 62 cuts off the cutting shaft 33, and the engine rotor is disconnected with the power absorbing mechanism 4, so that the actual over-rotation condition of the engine rotor is simulated;
At this time, since the electric push-pull rod 52 is symmetrically and fixedly connected to the top and the bottom of the wind collecting cover 51, the push rod 522 is fixedly connected to the rear side of the first inclined block 521 on the electric push-pull rod 52, the plugging plate 56 is in interference fit with the air outlet 55, the push plates 561 are fixedly arranged at the top and the bottom of the plugging plate 56, the push plates 561 are provided with clamping holes, and the push rods 522 can be clamped in the clamping holes, so that when the electric push-pull rod 52 is pushed forward, the plugging plate 56 can be pulled out to expose the air outlet 55 on the wind collecting cover 51, air in the wind collecting cover 51 is sprayed out from the air outlet 55, and the power absorbing mechanism 4 can slide in the direction away from the aeroengine 2, thereby driving the wind collecting mechanism 5 and the cutting mechanism 6 to be away from the aeroengine 2, and the effective protection testing device.
As shown in fig. 9-10, a sliding rail 11 is arranged at one end of the experiment platform 1, which is close to the power absorption mechanism 4, a sliding groove is arranged at the bottom of the power absorption mechanism 4, the power absorption mechanism 4 is in sliding connection with the sliding rail 11 through the sliding groove, a plurality of mounting grooves are arranged at the top of the sliding rail 11 in a displaying and distributing manner, and a rolling shaft 111 is rotationally connected in the mounting grooves.
In this embodiment, because experiment platform 1 is close to power absorption mechanism 4 one end and is provided with slide rail 11, power absorption mechanism 4 bottom is provided with the spout, power absorption mechanism 4 passes through spout and slide rail 11 sliding connection, slide rail 11 top display distribution has a plurality of mounting grooves, the mounting groove internal rotation is connected with roller bearing 111 for power absorption mechanism 4 becomes rolling friction with slide rail 11 on the experiment platform 1 by sliding friction, effectively reduces the frictional force of power absorption mechanism 4 and slide rail 11, makes things convenient for power absorption mechanism 4 to keep away from aeroengine 2, effectively protects testing arrangement.
The turbine rotor over-rotation test method of the ultra-high revolution aero-engine comprises the following steps of:
Fixing an aeroengine 2 on an experimental platform 1, correctly installing an engine rotor in the aeroengine 2, connecting a data collecting component, starting the data collecting component, and detecting before testing;
Step two, fixedly connecting an engine rotor with a power output shaft 31, fixedly connecting the power output shaft 31 with a first connecting shaft 32, fixedly connecting the first connecting shaft 32 with a cutting shaft 33, and installing the first connecting shaft 32 in the first supporting part 7;
Thirdly, pushing the power absorption mechanism 4 in place, enabling the cutting mechanism 6 to be opposite to the cutting shaft 33, fixedly connecting the cutting shaft 33 with the second connecting shaft 34, installing the second connecting shaft 34 in the second supporting part 8, and fixedly connecting the other end of the second connecting shaft 34 with the rotating shaft of the power absorption mechanism 4;
Resetting the electric push-pull rod 52, and clamping the blocking plate 56 on the air outlet 55 of the air collecting cover 51;
step five, starting the aero-engine 2 to drive the engine rotor to rotate;
Step six, gradually increasing the rotating speed of the engine rotor, and continuously recording and monitoring data parameters;
Step seven, the power of the aero-engine 2 is started to the maximum, at the moment, the electric push-pull rod 52 is started, the electric push-pull rod 52 is pushed forward, the cutter 62 on the cutting mechanism 6 is driven to slide towards the cutting shaft 33, and the cutter 62 cuts off the cutting shaft 33;
Step eight, the blocking plate 56 is pulled open by the electric push-pull rod 52 at the moment, so that the air outlet 55 on the air collecting cover 51 is exposed, the fan blades 341 on the second connecting shaft 34 always rotate at a high speed along with the engine rotor, after the air outlet 55 is exposed, air flow is sprayed out from the air outlet 55 to drive the power absorbing mechanism 4, the air collecting cover 51 and the cutting mechanism 6 to slide in the direction away from the aeroengine 2, the engine rotor simulates the real over-rotation condition at the moment, test parameter data are analyzed, and the over-rotation performance of the engine rotor is estimated.
Working principle:
During operation, the aero-engine 2 is fixed on the experiment platform 1, the engine rotor is accurately installed in the aero-engine 2, the engine rotor is fixedly connected with the power output shaft 31, the power output shaft 31 is fixedly connected with the first connecting shaft 32, the first connecting shaft 32 is fixedly connected with the cutting shaft 33, the first connecting shaft 32 is installed in the first supporting part 7, the cutting shaft 33 is fixedly connected with the second connecting shaft 34, the second connecting shaft 34 is installed in the second supporting part 8, the other end of the second connecting shaft 34 is fixedly connected with the rotating shaft of the power absorbing mechanism 4, the blocking plate 56 is clamped on the air outlet 55 of the air collecting cover 51, and at the moment, the cutting mechanism 6 is opposite to the cutting shaft 33, so that the test can be started;
Starting the aero-engine 2 to drive the engine rotor to rotate, wherein the second connecting shaft 34 can rotate along with the engine rotor at a high speed and can blow air into the air collecting mechanism 5;
The electric push-pull rod 52 is pushed forward, the first inclined block 521 presses the second inclined block 621, so that the cutter 62 slides towards the cutting shaft 33, and then the cutter 62 cuts off the cutting shaft 33, the engine rotor is disconnected with the power absorption mechanism 4, and the actual over-rotation condition of the engine rotor is simulated;
the cutting mechanism 6 can simulate the over-rotation condition of a real engine rotor only by cutting the cutting shaft 33, the cutting shaft 33 can be replaced conveniently, and the experimental cost is reduced effectively;
at this time, the plugging plate 56 is pulled out along with the pushing of the electric push-pull rod 52, so that the air outlet 55 on the air collecting cover 51 is exposed, and the air in the air collecting cover 51 is sprayed out from the air outlet 55, so that the power absorbing mechanism 4 slides in the direction away from the aeroengine 2, and the air collecting mechanism 5 and the cutting mechanism 6 are driven to be away from the aeroengine 2, thereby protecting the testing device effectively;
The sliding friction between the power absorption mechanism 4 and the sliding rail 11 on the experiment platform 1 is changed into rolling friction, so that the friction force between the power absorption mechanism 4 and the sliding rail 11 is effectively reduced, and the power absorption mechanism 4 is convenient to be far away from the aeroengine 2.
The foregoing description is only of the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention.
Claims (3)
1. The utility model provides an ultra-high revolution aeroengine turbine rotor overstroke testing arrangement, includes experiment platform (1), aeroengine (2), experimental axle (3), power absorption mechanism (4), collection fan mechanism (5), shutdown mechanism (6), first supporting part (7) and second supporting part (8), its characterized in that, experiment platform (1) is fixed to be set up subaerial, aeroengine (2) is fixed to be set up in experiment platform (1) one end, power absorption mechanism (4) sliding connection is at experiment platform (1) other end, experimental axle (3) one end and engine rotor fixed connection, experimental axle (3) other end and power absorption mechanism (4) pivot fixed connection, collection fan mechanism (5) is fixed to be set up in power absorption mechanism (4) front side, shutdown mechanism (6) is fixed to be set up in collection fan mechanism (5) front side, first supporting part (7) is fixed to be set up on experiment platform (1), second supporting part (8) is fixed to be set up in collection fan mechanism (5).
The aero-engine (2) is provided with a data collection component;
the wind collecting mechanism (5) is sleeved on the experimental shaft (3), and the cutting mechanism (6) is symmetrically arranged above and below the experimental shaft (3);
The first supporting component (7) and the second supporting component (8) are sleeved on the experiment shaft (3);
The experimental shaft (3) comprises a power output shaft (31), a first connecting shaft (32), a cutting shaft (33) and a second connecting shaft (34), one end of the power output shaft (31) is fixedly connected with an engine rotor, the other end of the power output shaft (31) is fixedly connected with the first connecting shaft (32), one end of the first connecting shaft (32) is fixedly connected with the power output shaft (31), the other end of the first connecting shaft (32) is fixedly connected with the cutting shaft (33), one end of the cutting shaft (33) is fixedly connected with the first connecting shaft (32), the other end of the cutting shaft (33) is fixedly connected with the second connecting shaft (34), one end of the second connecting shaft (34) is fixedly connected with the cutting shaft (33), and the other end of the second connecting shaft (34) is fixedly connected with a rotating shaft of the power absorbing mechanism (4);
The first connecting shaft (32) is rotationally connected with the first supporting component (7), the second connecting shaft (34) is rotationally connected with the second supporting component (8), and the cutting mechanism (6) is symmetrically arranged above and below the cutting shaft (33);
The wind collecting mechanism (5) comprises a wind collecting cover (51), an electric push-pull rod (52), a connecting plate (54) and a blocking plate (56), an air inlet (53) is formed in one side, close to the power absorbing mechanism (4), of the wind collecting cover (51), an air outlet (55) is formed in one side, far away from the power absorbing mechanism (4), of the wind collecting cover (51), the electric push-pull rod (52) is symmetrically and fixedly connected to the top and the bottom of the wind collecting cover (51), the blocking plate (56) is in interference fit with the air outlet (55), the connecting plate (54) is fixedly connected to one side, close to the power absorbing mechanism (4), of the wind collecting cover (51), the wind collecting cover (51) is fixedly connected with the power absorbing mechanism (4) through the connecting plate (54), the second connecting shaft (34) is rotationally connected in the wind collecting cover (51), a plurality of fan blades (341) are symmetrically and fixedly connected to one side, close to the air inlet (53), of the second supporting part (8) is fixedly connected to one side, close to the air outlet (55), of the wind collecting cover (51).
The front end of the electric push-pull rod (52) is fixedly connected with a first inclined block (521), and the rear side of the first inclined block (521) on the electric push-pull rod (52) is fixedly connected with a push rod (522);
Push plates (561) are fixedly arranged at the top and the bottom of the plugging plate (56), clamping holes are formed in the push plates (561), and the push rods (522) can be clamped in the clamping holes;
The cutting mechanism (6) comprises a cutter holder (61), a cutter (62) and a limiting spring (63), wherein the cutter holder (61) is symmetrically and fixedly connected to the front side of the wind collecting cover (51), the cutter (62) is slidably connected in the cutter holder (61), the top of the cutter (62) is fixedly connected with a second inclined block (621), the cutter (62) is sleeved with the limiting spring (63), the bottom of the limiting spring (63) is fixedly connected with the cutter (62), and the top of the limiting spring (63) is fixedly connected with the top of the cutter holder (61);
When the electric push-pull rod (52) is pushed forwards, the first inclined block (521) presses the second inclined block (621) so that the cutter (62) slides towards the cutting shaft (33), and then the cutter (62) cuts off the cutting shaft (33), and the engine rotor is disconnected with the power absorption mechanism (4).
2. The ultra-high revolution aeroengine turbine rotor overstroke testing device according to claim 1, wherein a sliding rail (11) is arranged at one end of the experiment platform (1) close to the power absorption mechanism (4), a sliding groove is arranged at the bottom of the power absorption mechanism (4), the power absorption mechanism (4) is in sliding connection with the sliding rail (11) through the sliding groove, a plurality of mounting grooves are arranged at the top of the sliding rail (11) in a displaying mode, and a rolling shaft (111) is connected in a rotating mode in the mounting grooves.
3. A method for testing a turbine rotor overrun testing apparatus of an ultra high revolution aero-engine according to any one of claims 1-2, said method comprising the steps of:
Fixing an aeroengine (2) on an experimental platform (1), correctly installing an engine rotor in the aeroengine (2), connecting a data collecting component, starting the data collecting component, and detecting before testing;
Step two, fixedly connecting an engine rotor with a power output shaft (31), fixedly connecting the power output shaft (31) with a first connecting shaft (32), fixedly connecting the first connecting shaft (32) with a cutting shaft (33), and installing the first connecting shaft (32) in a first supporting part (7);
pushing the power absorption mechanism (4) in place, enabling the cutting mechanism (6) to be opposite to the cutting shaft (33), fixedly connecting the cutting shaft (33) with the second connecting shaft (34), installing the second connecting shaft (34) in the second supporting part (8), and fixedly connecting the other end of the second connecting shaft (34) with the rotating shaft of the power absorption mechanism (4);
Resetting the electric push-pull rod (52), and clamping the plugging plate (56) on an air outlet (55) of the air collecting cover (51);
Step five, starting the aero-engine (2) to drive the engine rotor to rotate;
Step six, gradually increasing the rotating speed of the engine rotor, and continuously recording and monitoring data parameters;
Step seven, the power of the aero-engine (2) is started to the maximum, at the moment, an electric push-pull rod (52) is started, the electric push-pull rod (52) is pushed forwards, a cutter (62) on a cutting mechanism (6) is driven to slide towards a cutting shaft (33), and the cutter (62) cuts off the cutting shaft (33);
Step eight, the electric push-pull rod (52) pulls open the plugging plate (56) at the moment, so that an air outlet (55) on the air collecting cover (51) is exposed, fan blades (341) on the second connecting shaft (34) always rotate at a high speed along with the engine rotor, after the air outlet (55) is exposed, air flow is sprayed out of the air outlet (55) to drive the power absorbing mechanism (4), the air collecting cover (51) and the cutting mechanism (6) to slide in the direction away from the aeroengine (2), the engine rotor simulates real over-rotation conditions at the moment, test parameter data are analyzed, and the over-rotation performance of the engine rotor is estimated.
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