CN214952148U - Aircraft engine VBV ball screw actuator test fixture - Google Patents
Aircraft engine VBV ball screw actuator test fixture Download PDFInfo
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- CN214952148U CN214952148U CN202120542627.5U CN202120542627U CN214952148U CN 214952148 U CN214952148 U CN 214952148U CN 202120542627 U CN202120542627 U CN 202120542627U CN 214952148 U CN214952148 U CN 214952148U
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Abstract
The utility model relates to an aircraft engine VBV ball screw actuator test fixture, include: the shaft drag hook is a symmetrical arc-shaped rod, the two bent ends are provided with detachable shafts, and the back surface is provided with a ring; the bracket bottom plate is provided with a round hole in the middle, the rear wall of the round hole is provided with 2 rectangular grooves, threaded holes are distributed on the periphery of the round hole, vertical actuator positioning blocks are arranged on the left side, the right side and the rear side of the round hole, and an angle scale clamping groove block is arranged in front of the round hole; the leakage fixture assembly is in a circular plate shape, the top surface of the leakage fixture assembly is provided with a concentric circular ring, and the plate surface in the circular ring is drilled with an air hole which is provided with an air pipe connector and is also provided with three arc-shaped long grooves; the arc angle measuring tape is inserted into the angle measuring tape clamping groove block on the bottom plate of the bracket. The utility model discloses still relate to aircraft engine VBV ball screw actuator's test method. The utility model discloses a frock is small and exquisite practical, convenient effective, use reliably, and test method can use manpower sparingly, and can test aircraft engine VBV ball screw actuator's function fast by the at utmost.
Description
Technical Field
The utility model relates to an aircraft engine VBV (adjustable bleed valve) ball screw actuator test fixture.
Background
The VBV ball screw actuator of the aircraft engine is an important part of an aircraft air system, and the VBV ball screw actuator of the aircraft engine controls the switch of bleed air of the engine in a flexible shaft linkage switch mode, so that the purpose of adjusting the bleed air switch of the aircraft engine is achieved. When VBV initiative ball screw actuator passes through the flexible axle and drives VBV driven ball screw actuator and rotate, VBV driven ball screw actuator opens and closes and close along with opening of VBV initiative ball screw actuator, has just so reached the purpose that the bleed size adjusted according to engine running state, so the engine can the more efficient operation.
The VBV ball screw actuator of the aircraft engine is an important part of the engine, and when the VBV driving and driven ball screw actuators are closed, a circle of sealing ring surrounding a valve block on the VBV ball screw actuator is matched with the corresponding part to play a sealing role. Because the engine needs the switch bleed air of high frequency, so VBV ball screw actuator's switching frequency is also very high, and the sealing washer on the VBV ball screw actuator valve block also high frequency takes place the friction rather than the fitting surface, and the phenomenon of wearing and tearing will appear in the sealing washer of having of a specified duration. Therefore, the leakage amount of the VBV ball screw actuator in full closing must be checked regularly, and the repairing is carried out regularly according to the requirements of a manual. The dislocation test of the VBV ball screw actuator mainly has four requirements as follows: 1. the drive torque must meet CMM requirements. 2. VBV ball screw actuators do not have significant jamming throughout their stroke (specific data refer to CMM manual). 3. The VBV ball screw actuator should have a certain position margin under the axial moment given by the manual to ensure that the VBV ball screw actuator does not block when contacting with the matching surface. 4. The leakage must be less than the leakage given by the CMM for the VBV ball screw actuator to be fully closed. The existing common tool is difficult to realize the work of fixing, checking and testing the dislocation of the VBV ball screw actuator.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem, provide an aircraft engine VBV ball screw actuator test fixture just, adopt the utility model discloses an aircraft engine VBV ball screw actuator test fixture can realize VBV ball screw actuator off-position fixed, inspection and test work.
Solve above-mentioned technical problem, the utility model discloses the technical scheme who adopts as follows:
the utility model provides an aircraft engine VBV ball screw actuator test fixture which characterized in that includes:
the shaft drag hook 1 is in the shape of an arc rod with two ends bent inwards in the same direction and a middle symmetrical shaft, the two bent ends are provided with coaxial holes and are provided with detachable shafts capable of penetrating through horizontal holes on a valve plate of a VBV ball screw actuator, and the back of the arc rod is provided with a protruding ring or the middle of the arc rod is provided with a hole capable of being matched with a weight hook;
a round hole matched with the outer diameter of a valve plate (with a rubber ring) of an actuator 3 is formed in the middle of the bracket bottom plate 2, 2 symmetrical rectangular grooves matched with bulges on the back of the actuator are formed in the rear wall of the round hole, so that the valve plate of the actuator can be vertically adjusted and moved in the round hole, five threaded holes are distributed on the periphery of the round hole, two threaded holes correspond to two threaded rods on the actuator, and the two threaded holes are connected to fix the actuator; the angle measuring scale is characterized in that actuator positioning blocks which are vertical are arranged on the left side, the right side and the rear side of the round hole, the insides of the positioning blocks are matched with the shapes of the left side, the right side and the rear side of the actuator, an angle measuring scale clamping groove block is arranged in front of the round hole, a vertical arc-shaped clamping groove is formed in the angle measuring scale clamping groove block, a locking screw is arranged beside the clamping groove, and the angle measuring scale can be locked by screwing the locking screw after the position of the scale on the bottom plate of the bracket is adjusted;
the leakage clamp assembly 5 is in a circular plate shape, the top surface of the leakage clamp assembly is provided with a protruding concentric circular ring, the outer diameter of the circular ring is matched with a middle circular hole of the support bottom plate, an air hole is drilled on the surface inside the circular ring and is provided with an air pipe connector, and the surface outside the circular ring is provided with three arc-shaped long grooves corresponding to three threaded holes in the support bottom plate and provided with connecting pieces; the outer surface of the ring of the seepage clamp assembly is matched with the bottom plate of the bracket, and the inner ring is matched with a sealing ring of a VBV ball screw actuator of the aircraft engine (the sealing ring is arranged on the periphery of a valve plate of the actuator and used for realizing sealing with the inner ring of the clamp assembly);
the angle measuring scale 4 is an arc-shaped scale plate with angle scales and can be inserted into the angle measuring scale clamping groove block on the bottom plate of the bracket.
The axle draw hook is used for hooking the ring with actuator matched reuse weight couple and is used for testing the load drive value of the support, the support bottom plate is used for fixing the ball screw actuator on the top surface of the support bottom plate, and the threaded hole in the support bottom plate is connected with the screw rod in the VBV ball screw actuator. The leakage clamp assembly is fixed on the bottom surface of the support bottom plate through a connecting piece, the outer diameter of the circular ring of the leakage clamp assembly is matched with the middle circular hole of the support bottom plate, and the inner ring of the circular ring of the leakage clamp assembly is matched with the sealing ring of the VBV ball screw actuator, so that the leakage amount of the sealing ring of the VBV ball screw actuator is measured. Bleed air may be passed through the leak clamp assembly from one side of the leak clamp assembly air connector to the other side. The angle measuring scale is matched with the angle measuring scale clamping groove block of the support base plate and used for measuring the stroke angle of the VBV ball screw actuator. The detachable shaft penetrates through a horizontal hole of a valve plate of the VBV ball screw actuator and then penetrates into two ends of the arc rod, the protruding ring is arranged on the back surface of the arc rod, and weights are hung on the middle hole of the arc rod to measure torque.
Preferably, the bracket bottom plate corresponding to the arc-shaped slot of the angle measuring tape slot block is provided with a long hole for the angle measuring tape to pass through.
The side surface of the angle measuring scale clamping groove block is provided with a threaded hole communicated with the arc-shaped clamping groove and is provided with a locking screw, and the angle measuring scale can be locked by screwing the locking screw after the position of the scale on the support bottom plate is adjusted.
The test method for testing the VBV ball screw actuator of the aircraft engine by adopting the test tool is characterized by comprising the following steps of:
s1. load test
The detachable shaft of the shaft drag hook is detached, the detachable shaft penetrates through a hole of a valve plate of the VBV ball screw actuator and then is provided with an arc-shaped rod, and a ring is hooked by a weight hook to carry out load test on the VBV ball screw actuator;
s2. Stroke test
Installing and fixing a VBV ball screw actuator assembly on a support base plate, installing an angle measuring scale on the support base plate, adjusting the starting scale of the scale, and driving the VBV ball screw actuator to perform valve stroke test by a torque wrench through a tool;
s3, testing running-in torque of switch sealing ring
Installing and fixing a VBV ball screw actuator assembly on a support base plate, and coating a layer of sealing oil on a valve block sealing ring of a valve assembly; mounting the leakage clamp assembly on the bottom surface of the bracket bottom plate without fixing screws, wherein the outer ring of the raised circular ring of the clamp assembly is matched with the inner ring of the bracket bottom plate; and rotating the VBV ball screw actuator until the valve block sealing ring is stably matched with the inner ring of the leakage clamp assembly, and then tightening the fixing screw between the leakage clamp assembly and the support bottom plate. Therefore, opening and closing moment test and valve plate sealing ring leakage test can be carried out under the conditions of no gas filling and gas filling.
Has the advantages that: the utility model discloses an aircraft engine VBV ball screw actuator test fixture, the small and exquisite practicality of frock, convenient effective, use reliably, test method can use manpower sparingly, and can test aircraft engine VBV ball screw actuator's function fast by the at utmost.
Drawings
The device of the present invention will be further explained with reference to the drawings and the embodiments.
Fig. 1a is a schematic perspective view of an axial hook structure according to an embodiment of the present invention;
FIG. 1b is a perspective view of the axle hook of the embodiment of the present invention when mounted on an actuator for testing;
FIG. 1c is a front view of FIG. 1 b;
FIG. 1d is a right side view of FIG. 1 b;
FIG. 1e is a top view of FIG. 1 b;
fig. 2a is one of the schematic perspective views of the bottom plate of the bracket according to the embodiment of the present invention;
fig. 2b is a second perspective view of the bottom plate of the bracket according to the embodiment of the present invention;
fig. 2c is a third perspective view of the bottom plate of the bracket according to the embodiment of the present invention;
fig. 2d is a fourth schematic perspective view of a bottom plate of the bracket according to the embodiment of the present invention;
FIG. 2e is a front view of FIG. 2 a;
FIG. 2f is a top view of FIG. 2 a;
FIG. 2g is a left side view of FIG. 2 a;
FIG. 2h is a right side view of FIG. 2 a;
FIG. 2i is a bottom view of FIG. 2 a;
fig. 3a is one of the schematic perspective views of a leak clamp assembly according to an embodiment of the present invention;
fig. 3b is a second perspective view of a leak clamp assembly according to an embodiment of the present invention;
FIG. 4 is a perspective view of an angle measuring tape according to an embodiment of the present invention;
FIG. 5a is one of the schematic perspective views of a VBV ball screw actuator of an aircraft engine;
FIG. 5b is a second schematic perspective view of a VBV ball screw actuator of an aircraft engine;
FIG. 5c is a third schematic perspective view of a VBV ball screw actuator of an aircraft engine;
fig. 6a is one of the schematic diagrams of the test actuator according to the embodiment of the test fixture of the present invention;
FIG. 6b is a second schematic diagram illustrating the state of the test actuator according to the embodiment of the test tool of the present invention;
fig. 6c is a third schematic diagram illustrating a state of the testing actuator according to the embodiment of the testing tool of the present invention;
fig. 6d is a fourth schematic diagram illustrating the state of the test actuator according to the embodiment of the test fixture of the present invention;
fig. 6e is a fifth schematic view of the testing tool according to the embodiment of the present invention for testing the state of the actuator.
Reference numerals in the figures refer to: 1-shaft draw hook, 2-bracket bottom plate, 3-VBV valve body component, 4-angle measuring ruler and 5-leakage clamp component.
Detailed Description
As shown in the figure, the utility model discloses an aircraft engine VBV ball screw actuator test fixture embodiment, include:
the axial drag hook 1 is an arc-shaped rod with two ends bent inwards and a middle symmetrical axis, the two bent ends are provided with coaxial holes and are provided with detachable shafts capable of penetrating through holes on the actuator valve plate, and the back of the arc-shaped rod is provided with a protruding ring or the middle of the arc-shaped rod is provided with a hole capable of being matched with a weight hook.
A round hole matched with the outer diameter of a valve plate (with a rubber ring) of an actuator 3 is formed in the middle of a support base plate 2, 2 symmetrical rectangular grooves matched with bulges on the back of the actuator are formed in the rear wall of the round hole, so that the valve plate of the actuator can be adjusted and moved up and down in the round hole, threaded holes are distributed on the periphery of the round hole, some threaded holes correspond to screw rods on the actuator, and the threaded holes are connected with screw rods on the actuator to fix the actuator; actuator positioning blocks which are vertical are arranged on the left, the right and the rear of the round hole, and the inside of each positioning block is matched with the shapes of the left, the right and the rear of the actuator so as to be convenient to position; an angle measuring tape clamping groove block is arranged in front of the round hole, a vertical arc-shaped clamping groove is formed in the angle measuring tape clamping groove block, and a long hole is formed in the support bottom plate corresponding to the arc-shaped clamping groove of the angle measuring tape clamping groove block and can allow an angle measuring tape to pass through; and a locking screw is arranged beside the clamping groove, and the angle measuring scale can be locked by screwing the locking screw after the position of the scale on the bottom plate of the bracket is adjusted.
The leakage clamp assembly 5 is in a circular plate shape, the top surface of the leakage clamp assembly is provided with a protruding concentric circular ring, the outer diameter of the circular ring is matched with a middle circular hole of the support bottom plate, an air hole is drilled on the surface inside the circular ring and is provided with an air pipe connector, and the surface outside the circular ring is provided with three arc-shaped long grooves corresponding to the other three threaded holes on the support bottom plate and is provided with a connecting piece; the outer ring of the seepage clamp assembly is matched with the support bottom plate, and the inner ring of the seepage clamp assembly is matched with a sealing ring of a VBV ball screw actuator of the aircraft engine (the sealing ring is arranged on the periphery of a valve plate of the actuator and used for sealing the inner ring of the clamp assembly).
The angle measuring scale 4 is an arc-shaped scale plate with angle scales, and can be inserted into the angle measuring scale clamping groove block on the bottom plate of the bracket to adjust the measuring range and then fixed by screws.
Claims (4)
1. The utility model provides an aircraft engine VBV ball screw actuator test fixture which characterized in that includes:
the axial drag hook (1) is in the shape of an arc rod with two ends bent inwards in the same direction and a middle symmetrical axis, the two bent ends are provided with coaxial holes and are provided with detachable shafts capable of penetrating through horizontal holes on the actuator valve plate, and the back surface of the arc rod is provided with a protruding ring or the middle of the arc rod is provided with a hole capable of being matched with a weight hook;
the bracket bottom plate (2) is provided with a round hole matched with the outer diameter of the valve plate of the actuator (3) in the middle, the rear wall of the round hole is provided with 2 symmetrical rectangular grooves matched with bulges at the back of the actuator, a plurality of threaded holes are distributed on the periphery of the round hole, some threaded holes correspond to screw rods on the actuator, and the threaded holes are connected with the screw rods to fix the actuator; the actuator positioning blocks which are vertical are arranged on the left, the right and the rear of the round hole; an angle measuring tape clamping groove block is arranged in front of the round hole, and a vertical arc-shaped clamping groove is formed in the angle measuring tape clamping groove block;
the leakage clamp assembly (5) is in a circular plate shape, the top surface of the leakage clamp assembly is provided with a protruding concentric circular ring, the outer diameter of the circular ring is matched with a middle circular hole of the support bottom plate, an air hole is drilled on the plate surface in the circular ring and is provided with an air pipe connector, and the plate surface outside the circular ring is provided with a plurality of arc-shaped long grooves corresponding to threaded holes in the support bottom plate and provided with connecting pieces; the outer plate surface of the ring of the leakage clamp assembly is matched with the bottom plate of the bracket, and the inner ring of the leakage clamp assembly is matched with a sealing ring of a VBV ball screw actuator of an aircraft engine;
the angle measuring scale (4) is an arc-shaped scale plate with angle scales and can be inserted into the angle measuring scale clamping groove block clamping groove on the bottom plate of the bracket.
2. The aircraft engine VBV ball screw actuator testing tool of claim 1, wherein: the inner shapes of the positioning blocks erected on the left, right and rear sides of the circular hole of the leakage clamp assembly (5) are matched with the shapes of the left, right and rear sides of the actuator.
3. The aircraft engine VBV ball screw actuator testing tool of claim 1, wherein: and a support bottom plate corresponding to the arc-shaped clamping groove of the angle measuring tape clamping groove block is provided with a long hole through which an angle measuring tape can pass.
4. The aircraft engine VBV ball screw actuator testing tool of claim 3, wherein: the side surface of the angle measuring tape clamping groove block is provided with a threaded hole communicated with the arc-shaped clamping groove and is provided with a locking screw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120542627.5U CN214952148U (en) | 2021-03-16 | 2021-03-16 | Aircraft engine VBV ball screw actuator test fixture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120542627.5U CN214952148U (en) | 2021-03-16 | 2021-03-16 | Aircraft engine VBV ball screw actuator test fixture |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214952148U true CN214952148U (en) | 2021-11-30 |
Family
ID=79040679
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120542627.5U Active CN214952148U (en) | 2021-03-16 | 2021-03-16 | Aircraft engine VBV ball screw actuator test fixture |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214952148U (en) |
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2021
- 2021-03-16 CN CN202120542627.5U patent/CN214952148U/en active Active
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