CN113280979A - Sudden-load unbalance applying device for simulating blade flying off - Google Patents
Sudden-load unbalance applying device for simulating blade flying off Download PDFInfo
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- CN113280979A CN113280979A CN202110686247.3A CN202110686247A CN113280979A CN 113280979 A CN113280979 A CN 113280979A CN 202110686247 A CN202110686247 A CN 202110686247A CN 113280979 A CN113280979 A CN 113280979A
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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
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/14—Determining imbalance
- G01M1/16—Determining imbalance by oscillating or rotating the body to be tested
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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
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/02—Details of balancing machines or devices
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Abstract
The invention relates to a sudden unbalance applying device for simulating blade flying, wherein a flying blade and a counterweight blade are arranged on an integral fixing system through a blade clamping system, and the counterweight blade and the flying blade can be ensured to rotate along with the integral fixing system; the control driving system is arranged on the integral fixing system and can control the mortise state of the flying-off blade of the blade clamping system, so that the flying-off of the blade is controlled. The fir-type blade root is fixed by using the fir-type mortise, the fixing mode of the aviation aircraft engine blade is simulated, and the stability is high; the prepressing spring is used as a driving device, after the forked slide block moves for a certain distance, the prepressing driving spring quickly releases elasticity along the direction of the guide rail, so that the mortise of the blade is quickly opened, and the quick control of the flying-off of the blade is realized; the parts have no strong collision or plastic deformation in the opening process of the blade mortise, and the nondestructive repeated experiment of the sudden-adding unbalance device can be realized.
Description
Technical Field
The invention belongs to the field of aero-engines, relates to a turbofan engine fan blade and an aero-engine rotor blade sudden unbalance experimental device, and particularly relates to a sudden unbalance applying device for simulating blade flying off.
Background
In recent years, with the continuous progress of modern technology, the aviation industry is rapidly developed. For an aviation aircraft, safety is an important index for measuring the value of the aircraft, and an aero-engine serving as an important composition structure of a modern aviation aircraft plays a role of a power driving source in the process of aviation, so that the safety problem is inevitably emphasized.
When the engine with the large bypass ratio in civil aviation is used, if the engine is impacted by foreign objects (bird strike, stone, ice blocks and the like), the Fan blades or the rotor blades of the engine are broken, and the Fan blades of the engine are broken and fly Off (Fan Blade Off) or the rotor blades are broken and fly Off, an engine receiver uncontained event can be caused, and the airplane flight safety is threatened fatally. Therefore, it is important to provide a controllable sudden unbalance application device which simulates the flying-off of the blade and has good simulation effect.
Heretofore, there have been various sudden unbalanced loading arrangements for the blades. In the paper "Mechanical and experimental excitation on the sacrificial area and rub-impact in rotor system used by blade off" (Mechanical Systems and Signal Processing 76-77(2016)111-135), the method of applying a sudden imbalance is to extend a spring hammer in the rotational path of the fly-off blade to break the fly-off blade. The device has large influence on experimental results and poor repeatability; in the thesis of the dynamic response experiment of the rotor under the flying and falling of the blade (the report of the aeronautical dynamics, 2019, 34 (05): 1010-1019), the flying and falling of the blade is realized by deforming the elastic clamp by using the centrifugal force, and the rotating speed of the blade during the action can not be accurately controlled.
Disclosure of Invention
The invention aims to overcome the defects of poor controllability, poor repeatability and low precision in the prior art, and provides a loading device for experimental sudden unbalance of an aircraft engine.
The technical problem to be solved by the invention is realized by the following technical scheme:
a sudden unbalance applying device for simulating blade flying is characterized in that: the blade clamping device comprises an integral fixing unit, a control driving unit and a blade clamping unit, wherein the control driving unit and the blade clamping unit are arranged on the integral fixing unit and can rotate along with the integral fixing unit; the control driving unit is connected to the blade clamping unit and can control the size of the fir-tree-shaped mortise at the position of the flying-off blade in the blade clamping unit.
Moreover, the integral fixing unit comprises a bottom plate and a top cover, wherein the bottom plate is of a cylindrical structure, and the top cover is of a bowl-shaped structure; the top cover is connected with the bottom plate through a flange.
Moreover, the control driving unit comprises a driving box body, a left inclined triangular guide rail, a right inclined triangular guide rail, a slide block-shaped driving block, a driving combination block, a prepressing driving spring and a flying off triggering module, the front of the driving box body is arranged in a groove arranged on a bottom plate, a left inclined triangular guide rail is arranged on the left side edge inside the driving box body, a right inclined triangular guide rail is arranged on the right side edge inside the driving box body, the bottom of the slide block-shaped driving block is provided with an inclined triangular protrusion which is matched with an inclined triangular guide rail formed by the left inclined triangular guide rail and the right inclined triangular guide rail, the sliding block-shaped driving block is fixedly connected with the driving combination block through a screw, the prepressing driving spring is connected with the driving box body and the sliding block-shaped driving block, after the prepressing driving spring receives a trigger signal, the slide block-shaped driving block can make linear motion along the inclined triangular guide rail formed by the left inclined triangular guide rail and the right inclined triangular guide rail.
The number of the pre-pressure driving springs is three, and the pre-pressure driving springs are kept in a compressed state before flying off.
And the flying-off triggering module comprises a screw rod stepping motor, a power supply ring and a fork-shaped sliding block, wherein the power supply ring is fixed in the bottom plate, the power supply ring is connected to the screw rod stepping motor and supplies power to the screw rod stepping motor, the screw rod stepping motor is fixedly connected with the fork-shaped sliding block through a screw rod, and the screw rod stepping motor provides guide direction displacement for the fork-shaped sliding block.
The blade clamping unit comprises a fixed clamp, a movable clamp, a counterweight blade, a fly-off blade and a bearing, wherein the fixed clamp is fixed with the bottom plate and can rotate along with the bottom plate; the fir-tree-shaped mortise formed by the fixed clamp and the movable clamp is matched with the fir-tree-shaped tenon of the flying blade, and the flying blade can rotate along with the bottom plate before flying; the upper part of the sliding block-shaped driving block is provided with two cylinders, the movable clamp is inserted into the cylinders through the arranged flat key-shaped grooves, and the driving combination block drives the movable clamp to rotate around the bearing.
The invention has the advantages and beneficial effects that:
1. the sudden unbalance applying device for simulating the flying-off of the blade, disclosed by the invention, has the advantages that the fir-shaped tenon and the mortise of the flying-off blade are mutually coupled, the working environment of a real blade is simulated, and the flying-off blade is only acted by centrifugal force during flying-off and does not introduce extra kinetic energy, so that the flying posture and the flying track of the flying-off blade are not influenced and are closer to the real situation.
2. The sudden unbalance applying device for simulating the flying of the blade monitors the rotating speed of the flying blade to accurately control the flying time of the blade, when the rotating speed of the blade reaches a preset rotating speed, the lead screw stepping motor guides the fork-shaped slide block to move along the chord direction relative to the bottom plate, after the fork-shaped slide block moves for a certain distance, the prepressing driving spring quickly releases the elastic force along the direction of the guide rail, and drives the slide block-shaped driving block to drive the movable clamp to rotate around the fixed fulcrum appropriately, so that the mortise of the blade is opened quickly, the blade flies out under the action of centrifugal force, and the initial speed of the blade during flying is finally accurately controllable.
3. According to the sudden unbalance applying device for simulating blade flying off, the motion transmission of the blade mortise driving device is stable in the loading process of the sudden unbalance applying device, and the influence of other factors except inertia on the blade is eliminated; and no strong collision or plastic deformation exists among parts in the opening process of the blade mortise, so that the aim of repeated experiments without damage of the sudden unbalance device can be fulfilled.
Drawings
FIG. 1 is a front view of the present invention (without the top cover);
FIG. 2 is a schematic structural view of the present invention;
FIG. 3 is a schematic diagram of the state of the control drive system and the position of the fork slide before the flying off occurs according to the present invention;
FIG. 4 is a schematic diagram of the state of the control drive system and the position of the fork-shaped slider when a flying off occurs according to the present invention.
Detailed Description
The present invention is further illustrated by the following specific examples, which are intended to be illustrative, not limiting and are not intended to limit the scope of the invention.
A sudden unbalance applying device for simulating blade flying is characterized in that: the device comprises an integral fixing system 1, a control driving system 2 and a blade clamping system 3, wherein the control driving system 2 and the blade clamping system 3 are arranged on the integral fixing system 1 and can rotate together with the integral fixing system 1; the control driving system 2 is connected with the blade clamping system 3 and can control the size of a mortise at the position of the flying-off blade 18 of the blade clamping system, so that the flying-off of the blade is controlled.
The integral fixing system 1 comprises a bottom plate 4 and a top cover 5; the bottom plate 4 is of a cylindrical structure; the top cover 5 is of a bowl-shaped structure; the top cover 5 is connected with the bottom plate 4 through a flange edge.
The control driving system 2 comprises a driving box body 6, a left inclined triangular guide rail 7, a right inclined triangular guide rail 8, a slider-shaped driving block 9, a driving combination block 10, a prepressing driving spring 11 and a flying off triggering module; the driving box body 6 is embedded into a groove arranged on the bottom plate 4, the left inclined triangular guide rail 7 is arranged at the left side edge inside the driving box body 6, and the right inclined triangular guide rail 8 is arranged at the right side edge inside the driving box body 6; the bottom of the sliding block-shaped driving block 9 is provided with an inclined triangular protrusion which is matched with an inclined triangular guide rail formed by the left inclined triangular guide rail 7 and the right inclined triangular guide rail 8; the upper part of the slide block-shaped driving block 9 is provided with two small cylinders which can be inserted into two flat key-shaped grooves of the movable clamp 16 and then fixed together with the driving combination block 10 through screws to play a role in driving the movable clamp 16. The pre-pressing driving spring 11 keeps a compressed state before the blade flies off; the number of the prepressing driving springs 11 is three, the prepressing driving springs 11 are connected with the driving box body 6 and the sliding block-shaped driving block 9, and when a trigger signal is received, the sliding block-shaped driving block 9 can linearly move along an inclined triangular guide rail formed by the left inclined triangular guide rail 7 and the right inclined triangular guide rail 8.
The flying off triggering module comprises a screw rod stepping motor 12, a power supply ring 13 and a forked slide block 14; the power supply ring 13 is fixed on the inner ring of the bottom plate 4; the power supply ring 13 is used as a power supply of a control driving system and supplies power to the screw rod stepping motor 12; the lead screw stepping motor 12 is fixedly connected with the fork-shaped sliding block 14 through a lead screw, and the lead screw stepping motor 12 can provide guiding direction displacement for the fork-shaped sliding block 14.
The blade clamping system 3 comprises a fixed clamp 15, a movable clamp 16, a counterweight blade 17, a fly-off blade 18 and a bearing 19; the fixed clamp 15 is fixed with the bottom plate 4 and can rotate along with the bottom plate 4; a fir-shaped mortise formed by the two fixing clamps 15 is matched with a fir-shaped tenon of the counterweight blade 17, so that the counterweight blade 17 can rotate along with the bottom plate 4; the movable clamp 16 is connected with the bottom plate 4 through a bearing 19 and can rotate around the bearing 19; a fir-tree mortise formed by a fixed clamp 15 and a movable clamp 16 is matched with a fir-tree tenon of the fly-off blade 18, and the fly-off blade 18 can rotate along with the bottom plate 4 before flying off; the driving combination block 10 can drive the movable clamp 16 to rotate around the bearing 19, and open the fir-tree-shaped mortise formed by the movable clamp 16 and the fixed clamp 15, so that the fly-off blade 18 flies off under the action of centrifugal force.
The working principle of the invention is as follows:
i, self-locking of a flying-off front device: fig. 3 is a schematic diagram of the state of the pre-flying-off control driving system 2 and the position of the fork-shaped sliding block 14, when the flying-off triggering module of the control driving system 2 does not receive a flying-off starting signal, the fork-shaped sliding block 14 and the driving box 6 form two strip-shaped grooves, the front end of the sliding block-shaped driving block 9 is clamped in the grooves, so that the sliding block-shaped driving block 9 is prevented from moving, the movable clamp is fixed, and the flying-off blade 18 cannot fly off;
II, starting the device when the flying off occurs: fig. 4 is a schematic diagram of the state of the control drive system 2 and the position of the fork-shaped slider 14 when the flying-off occurs, when the flying-off trigger module of the control drive system 2 receives a flying-off start signal, the fork-shaped slider 14 moves away from the drive box under the action of the lead screw stepping motor 12, and finally the limitation of the fork-shaped slider 14 on the slider-shaped drive block 9 is removed, and the slider-shaped drive block 9 moves away from the flying-off blade along the guide rail under the action of the pre-pressing drive spring 11, so as to drive the movable clamp 16 to move, and further the flying-off blade 18 flies off under the action of centrifugal force.
Although the embodiments of the present invention and the accompanying drawings are disclosed for illustrative purposes, those skilled in the art will appreciate that: various substitutions, changes and modifications are possible without departing from the spirit and scope of the invention and the appended claims, and therefore the scope of the invention is not limited to the disclosure of the embodiments and the accompanying drawings.
Claims (6)
1. A sudden unbalance applying device for simulating blade flying is characterized in that: the blade clamping device comprises an integral fixing unit (1), a control driving unit (2) and a blade clamping unit (3), wherein the control driving unit (2) and the blade clamping unit (3) are arranged on the integral fixing unit (1) and can rotate along with the integral fixing unit (1); the control driving unit (2) is connected to the blade clamping unit (3) and can control the size of a fir-shaped mortise at a flying-off blade (18) in the blade clamping unit.
2. The sudden unbalance applying apparatus for simulating blade fly-off according to claim 1, wherein: the integral fixing unit (1) comprises a bottom plate (4) and a top cover (5), wherein the bottom plate (4) is of a cylindrical structure, and the top cover (5) is of a bowl-shaped structure; the top cover (5) is connected with the bottom plate (4) through a flange.
3. The sudden unbalance applying apparatus for simulating blade fly-off according to claim 1, wherein: the control driving unit (2) comprises a driving box body (6), a left inclined triangular guide rail (7), a right inclined triangular guide rail (8), a slider-shaped driving block (9), a driving combination block (10), a pre-pressing driving spring (11) and a flying off trigger module, wherein the driving box body (6) is filled in a groove formed in the bottom plate (4) in front, the left inclined triangular guide rail (7) is installed at the left side edge inside the driving box body (6), the right inclined triangular guide rail (8) is installed at the right side edge inside the driving box body (6), an inclined triangular protrusion is arranged at the bottom of the slider-shaped driving block (9) and is matched with the inclined triangular guide rail formed by the left inclined triangular guide rail (7) and the right inclined triangular guide rail (8), the slider-shaped driving block (9) is fixedly connected with the driving combination block (10) through screws, the pre-pressing driving spring (11) is connected with the driving box body (6) and the slider-shaped driving block (9), after the pre-pressing driving spring receives a trigger signal, the sliding block-shaped driving block (9) can make linear motion along an inclined triangular guide rail formed by the left inclined triangular guide rail (7) and the right inclined triangular guide rail (8).
4. The sudden unbalance applying apparatus for simulating blade fly-off according to claim 3, wherein: the number of the pre-pressing driving springs is three, and the pre-pressing driving springs are kept in a compressed state before flying off.
5. The sudden unbalance applying apparatus for simulating blade fly-off according to claim 3, wherein: the flying-off triggering module comprises a screw rod stepping motor (12), a power supply ring (13) and a fork-shaped sliding block (14), the power supply ring (13) is fixed in the bottom plate (4), the power supply ring (13) is connected to the screw rod stepping motor (12) and supplies power to the screw rod stepping motor, the screw rod stepping motor (12) is fixedly connected with the fork-shaped sliding block (14) through a screw rod, and the screw rod stepping motor (12) provides guide direction displacement for the fork-shaped sliding block (14).
6. The sudden unbalance applying apparatus for simulating blade fly-off according to claim 1, wherein: the blade clamping unit (3) comprises fixed clamps (15), a movable clamp (16), a counterweight blade (17), a fly-off blade (18) and a bearing (19), wherein the fixed clamps (15) are fixed with the bottom plate (4) and can rotate along with the bottom plate (4), a fir-tree mortise formed by the two fixed clamps (15) is matched with a fir-tree tenon of the counterweight blade (17) to ensure that the counterweight blade (17) can rotate along with the bottom plate (4), and the movable clamp (16) is connected with the bottom plate (4) through the bearing (19) and can rotate around the bearing (19); the fir-tree-shaped mortise formed by the fixed clamp (15) and the movable clamp (16) is matched with the fir-tree-shaped tenon of the flying blade (18), and the flying blade (18) can rotate along with the bottom plate (4) before flying; the upper part of the sliding block-shaped driving block is provided with two cylinders, the movable clamp is inserted into the cylinders through the arranged flat key-shaped grooves, and the driving combination block (10) drives the movable clamp (16) to rotate around the bearing (19).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110686247.3A CN113280979B (en) | 2021-06-21 | 2021-06-21 | Sudden-load unbalance applying device for simulating blade flying off |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110686247.3A CN113280979B (en) | 2021-06-21 | 2021-06-21 | Sudden-load unbalance applying device for simulating blade flying off |
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| CN113280979A true CN113280979A (en) | 2021-08-20 |
| CN113280979B CN113280979B (en) | 2022-07-22 |
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| CN202110686247.3A Active CN113280979B (en) | 2021-06-21 | 2021-06-21 | Sudden-load unbalance applying device for simulating blade flying off |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114705364A (en) * | 2022-03-04 | 2022-07-05 | 南京航空航天大学 | Laboratory sudden-load unbalance simulation test device and test method thereof |
| FR3132350A1 (en) * | 2022-02-02 | 2023-08-04 | Airbus Helicopters | rotor unbalance simulator and test bench equipped with this simulator |
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| US20150101178A1 (en) * | 2013-10-16 | 2015-04-16 | Kaba Ilco Corp. | Universal clamping assembly for key duplicating machine |
| CN205940943U (en) * | 2016-07-25 | 2017-02-08 | 中国航空动力机械研究所 | Engine blade clamping device |
| CN106611553A (en) * | 2017-03-06 | 2017-05-03 | 西北工业大学 | Loading device for sudden unbalance of aeroengine experimental instrument |
| CN209673370U (en) * | 2019-05-20 | 2019-11-22 | 中国航发商用航空发动机有限责任公司 | Rotating vane falls off experimental rig |
| CN112014109A (en) * | 2020-07-30 | 2020-12-01 | 南京航空航天大学 | Simulation test device for loss of aero-engine rotor blade |
-
2021
- 2021-06-21 CN CN202110686247.3A patent/CN113280979B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150101178A1 (en) * | 2013-10-16 | 2015-04-16 | Kaba Ilco Corp. | Universal clamping assembly for key duplicating machine |
| CN205940943U (en) * | 2016-07-25 | 2017-02-08 | 中国航空动力机械研究所 | Engine blade clamping device |
| CN106611553A (en) * | 2017-03-06 | 2017-05-03 | 西北工业大学 | Loading device for sudden unbalance of aeroengine experimental instrument |
| CN209673370U (en) * | 2019-05-20 | 2019-11-22 | 中国航发商用航空发动机有限责任公司 | Rotating vane falls off experimental rig |
| CN112014109A (en) * | 2020-07-30 | 2020-12-01 | 南京航空航天大学 | Simulation test device for loss of aero-engine rotor blade |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3132350A1 (en) * | 2022-02-02 | 2023-08-04 | Airbus Helicopters | rotor unbalance simulator and test bench equipped with this simulator |
| EP4224133A1 (en) | 2022-02-02 | 2023-08-09 | Airbus Helicopters | Unbalance simulator of a rotor and test bench with this simulator |
| CN114705364A (en) * | 2022-03-04 | 2022-07-05 | 南京航空航天大学 | Laboratory sudden-load unbalance simulation test device and test method thereof |
| CN114705364B (en) * | 2022-03-04 | 2024-02-09 | 南京航空航天大学 | Laboratory simulation sudden-adding unbalance test device and test method thereof |
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| CN113280979B (en) | 2022-07-22 |
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