CN220259647U - Double-shaft neck blade type face milling fixture of aeroengine - Google Patents

Abstract

The utility model provides a double-shaft-neck blade profile milling clamp of an aeroengine, which comprises a clamp I, a clamp II and a supporting mechanism for supporting the blade profile, wherein the clamp locates a shaft neck first shaft end, the clamp II locates a shaft neck second shaft end, and the supporting structure is detachably connected with the clamp I or the clamp II; the supporting mechanism comprises two semicircular supporting mechanisms which are symmetrically arranged, the blade profile is positioned between the two semicircular supporting mechanisms, and the two semicircular positioning supporting mechanisms support and position the middle part of the blade profile. The utility model has simple structure and wide application range, is convenient to assemble and disassemble, can adapt to blade profiles with different thicknesses, supports the blade profiles through the supporting mechanism, can avoid bending deformation of the blade during processing, improves the processing precision, and saves the manufacturing materials and the production cost of the clamp.

Description

Double-shaft neck blade type face milling fixture of aeroengine

Technical Field

The utility model relates to the technical field of aero-engine blade machining, in particular to a double-shaft-neck blade profile milling fixture of an aero-engine.

Background

Because the adjustable stator blade of the compressed air part of the aeroengine is thinner, if a special fixture is not used when the blade profile is milled on the numerical control machine tool, the profile requirement of the blade profile is difficult to ensure, and tremble is easy to generate during processing, so that the blade profile is easy to deform, the consistency of the profile is poor, and the labor productivity is greatly reduced.

As shown in fig. 1, the aero-engine compressor section adjustable stator vane is a two-shaft journal vane comprising a journal one 101, a journal two 102, and a vane profile 103 located between the journal one 101 and the journal two 102. The traditional milling fixture for the profile of the double-shaft-neck blade generally adopts two end holes to position and jack the shaft necks, and the profile of the blade is processed by taking the shaft necks at the two ends as references. However, because the adjustable stator blade profile of the compressed air part of the aero-engine is thinner, when the blade profile is processed, the blades are easy to bend and deform after the two ends are tightly propped, the processing precision can not meet the requirements, and the waste of processing cost can be caused.

Disclosure of Invention

The utility model aims to provide a double-shaft-neck blade profile milling fixture of an aeroengine, which overcomes the defects in the prior art.

In order to solve the technical problems, the technical scheme of the utility model is as follows: the double-shaft neck blade profile milling clamp of the aeroengine comprises a clamp I, a clamp II and a supporting mechanism for supporting the blade profile, wherein the clamp locates a shaft neck first shaft end, the clamp II locates a shaft neck second shaft end, and the supporting mechanism is detachably connected with the clamp I or the clamp II; the supporting mechanism comprises two semicircular supporting mechanisms which are symmetrically arranged, the blade profile is positioned between the two semicircular supporting mechanisms, and the two semicircular supporting mechanisms support and position the middle part of the blade profile.

Further, the double-shaft-neck blade profile milling clamp of the aeroengine comprises a first transition disc and a first chassis, wherein the first transition disc is connected with a machine tool, the first chassis is connected with the transition disc through a fastener, and a jack for positioning the first shaft neck is arranged on a positioning column at the front end of the first chassis.

Further, the double-shaft-neck blade profile milling clamp of the aeroengine comprises a transition disc and a second chassis, wherein the transition disc is connected with a machine tool, the second chassis is connected with the transition disc through a fastener, and a jack for positioning the second shaft neck is arranged on a positioning column at the front end of the second chassis.

Further, the two semicircular supporting mechanisms are identical in structure and comprise semicircular rings, supporting bars, positioning blocks and positioning bars, the supporting bars are symmetrically arranged on the semicircular rings, the positioning blocks are fixed at the top ends of the supporting bars, the positioning bars are movably connected with the positioning blocks, the two positioning blocks of the semicircular supporting mechanisms are connected through screws, accommodating cavities for accommodating the blade profiles are formed in opposite sides of the two positioning blocks, the two positioning bars of the semicircular supporting mechanisms are oppositely arranged and extend into the accommodating cavities to support the positioning blade profiles, and one ends of the positioning bars, which are in contact with the blade profiles, are round heads.

Further, the double-shaft-neck blade profile milling clamp of the aeroengine is characterized in that a plurality of mounting holes I which are uniformly distributed in the circumference are formed in a transition disc of the clamp I and the clamp II, a plurality of mounting holes II which are uniformly distributed in the circumference are formed in a semicircular ring, and the semicircular ring is sleeved on the outer side of the chassis I or the outer side of the chassis II and fixedly connected with the transition disc through fasteners penetrating through the mounting holes I and the mounting holes II.

Further, the double-shaft-neck blade profile milling clamp of the aeroengine, an adjusting component is further arranged in the positioning block, the adjusting component comprises an adjusting screw, a positioning hole which is correspondingly arranged with the positioning rod is formed in the positioning block, the positioning rod is inserted into the positioning hole and is in sliding connection with the positioning hole, a step is arranged at one end, close to the accommodating cavity, of the positioning rod, a positioning section matched with the step is arranged in the middle of the positioning rod, and the adjusting screw is arranged at one end, far away from the accommodating cavity, of the positioning hole and is in threaded connection with the positioning hole.

Further, the double-shaft-neck blade profile milling clamp of the aeroengine, the adjusting assembly further comprises an adjusting nut and a spring, the adjusting nut is arranged between the positioning section and the adjusting screw, the adjusting nut is in threaded connection with the positioning hole, the spring sleeved outside the positioning rod is arranged between the adjusting nut and the positioning section, and the adjusting nut is sleeved outside the positioning rod and is in sliding connection with the positioning rod.

Furthermore, the double-shaft-neck blade profile milling clamp of the aeroengine is characterized in that one side of the positioning hole is also provided with a limiting hole communicated with the positioning hole, a limiting screw in threaded connection with the limiting hole is arranged in the limiting hole, and the limiting screw is matched with a positioning plane arranged on the positioning section.

Compared with the prior art, the utility model has the beneficial effects that: the novel blade profile support is simple in structure, convenient to manufacture, capable of adapting to blade profiles with different thicknesses, wide in application range, stable in support of the support mechanism, and capable of avoiding damage to the blades during support positioning. When the support mechanism is connected with the clamp I in processing, the blade profile close to one end of the journal II is processed, after the blade profile close to one end of the journal II is processed, the support mechanism is detached from the clamp I to be installed on the clamp II, and the blade profile close to one end of the journal I begins to be processed, so that the assembly and disassembly are convenient and quick, and the time for an operator to calibrate the clamp can be shortened; and the middle position of the profile of the blade is supported by the supporting mechanism, so that the bending deformation of the blade during processing is avoided, the processing precision is improved, and the manufacturing materials and the production cost of the clamp are saved.

Drawings

In order to more clearly illustrate the embodiments of the present utility model or the technical solutions in the prior art, the drawings that are required to be used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments described in the present utility model, and other drawings may be obtained according to the drawings without inventive effort to those skilled in the art.

FIG. 1 is a schematic view of a blade configuration of a dual journal blade face milling fixture of an aircraft engine of the present utility model;

FIG. 2 is a schematic structural view of a dual journal blade profile milling fixture of an aircraft engine of the present utility model;

FIG. 3 is a schematic view of the internal structure of a positioning block of a dual-journal blade profile milling fixture of an aircraft engine;

in the figure: 101. journal one; 102. journal two; 103. blade profile;

1. a first clamp; 11. a transition disc; 111. a first mounting hole; 12. a chassis I;

2. a second clamp; 22. a chassis II;

3. a support mechanism; 31. a semicircular ring; 311. a second mounting hole; 32. a support bar; 33. a positioning block; 331. positioning holes; 332. a limiting hole; 34. a positioning rod; 341. a positioning section; 35. a receiving chamber; 36. an adjusting screw; 37. an adjusting nut; 38. a spring; 39. and (5) limiting screws.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

Example 1

1-3, a double-shaft-neck blade profile milling fixture of an aeroengine comprises a fixture I1, a fixture II 2 and a supporting mechanism 3 for supporting a blade profile 103, wherein the fixture I1 is used for positioning a shaft end of a shaft neck I101, the fixture II 2 is used for positioning a shaft end of a shaft neck II 102, and the supporting mechanism 3 is detachably connected with the fixture I1 or the fixture II 2; the supporting mechanism 3 comprises two semicircular supporting mechanisms which are symmetrically arranged, the blade profile 103 is located between the two semicircular supporting mechanisms, and the two semicircular supporting mechanisms support and position the middle of the blade profile 103. During machining, when the supporting mechanism 3 is connected with the clamp I1, machining the blade profile close to one end of the journal II 102, and after machining the blade profile close to one end of the journal II 2, detaching the supporting mechanism 3 from the clamp I1 to be installed on the clamp II 2, and starting to machine the blade profile close to one end of the journal I1, so that the dismounting is convenient and quick, and the time for an operator to calibrate the clamp can be shortened; and the middle position of the blade profile 103 is supported by the supporting mechanism 3, so that the bending deformation of the blade during processing can be avoided, the processing precision is improved, and the manufacturing materials and the production cost of the clamp are saved.

As shown in fig. 2, the first clamp 1 comprises a transition disc 11 and a first chassis 12, the transition disc 11 is connected with a machine tool, the first chassis 12 is connected with the transition disc 11 through a fastener, and a positioning column at the front end of the first chassis 12 is provided with a jack for positioning the first journal 101. The second clamp 2 comprises a transition disc 11 and a second chassis 22, the transition disc 11 of the second clamp 2 is also connected with a machine tool, the second chassis 22 is connected with the transition disc 11 through a fastener, and a positioning column at the front end of the second chassis 22 is provided with a jack for positioning the second journal 102. The transition disc 11 of the clamp I1 and the transition disc 11 of the clamp II 2 are the same, the insertion holes on the chassis I12 and the chassis II 22 are matched with the outer dimensions of the shaft necks of the blades, and the installation is convenient and quick.

Example 2

Based on the structure of the embodiment, as shown in fig. 2, two semicircular supporting mechanisms have the same structure and comprise a semicircular ring 31, supporting bars 32, positioning blocks 33 and positioning rods 34, wherein the semicircular ring 31 is provided with two supporting bars 32 which are symmetrically arranged, the top ends of the supporting bars 32 are fixedly provided with the positioning blocks 33, the positioning blocks 33 are provided with the positioning rods 34 which are movably connected with the positioning blocks 33, the positioning blocks 33 of the two semicircular supporting mechanisms are connected through screws, the opposite sides of the two positioning blocks 33 are provided with accommodating cavities 35 for accommodating blade profiles 103, the positioning rods 34 of the two semicircular supporting mechanisms are oppositely arranged and extend into the accommodating cavities 35 to support the positioning blade profiles 103, the supporting mechanisms 3 extend from the journal ends to support the blade profiles 103, bending deformation of the middle parts of the blades is avoided, and one ends of the positioning rods 34, which are contacted with the blade profiles 103, are round heads which can reduce damage to the blades when clamping the blade profiles 103. The two semicircular supporting mechanisms have the same structure, so that the supporting mechanism 3 can be conveniently installed without alignment and installation, and the installation is convenient and quick.

In the above structure, as shown in fig. 2, the transition plate 11 of the first clamp 1 and the second clamp 2 is provided with a plurality of mounting holes 111 uniformly distributed on the circumference, the semicircular ring 31 is provided with a plurality of mounting holes 311 uniformly distributed on the circumference, and the semicircular ring 31 is sleeved on the outer side of the first chassis 12 or the second chassis 22 and is fixedly connected with the transition plate 11 through a fastener passing through the mounting holes 111 and 311. The bolts of the positioning block 33 and the semicircular ring 31 are loosened, so that the supporting mechanism 3 can be detached, and the dismounting is quick, convenient and quick.

In the above-mentioned structure, still be equipped with adjusting part in the locating piece 33, adjusting part includes adjusting screw 36, be equipped with the locating hole 331 that corresponds the setting with locating lever 34 on the locating piece 33, locating lever 34 inserts and establishes in locating hole 331 and with locating hole 331 sliding connection, locating hole 331 is close to the one end that holds chamber 35 and is equipped with the step, locating lever 34 middle part is equipped with and step complex location section 341, can avoid locating lever 34 to slide out from locating hole 331, adjusting screw 36 locates locating hole 331 and keeps away from the one end that holds chamber 35 and with locating hole 331 threaded connection. The distance that the positioning rod 34 stretches into the accommodating cavity 35 is adjusted through the distance that the positioning screw 36 is screwed into the positioning hole 331, so that the processing of the blade profile 103 with different thickness can be adapted, the application range is wide, and the flexibility is good.

In addition, as shown in fig. 2 and 3, the adjusting assembly further includes an adjusting nut 37 and a spring 38, the adjusting nut 37 is disposed between the positioning section 341 and the adjusting screw 36, the adjusting nut 37 is in threaded connection with the positioning hole 331, the spring 38 sleeved outside the positioning rod 34 is disposed between the adjusting nut 37 and the positioning section 341, and the adjusting nut 37 is sleeved outside the positioning rod 34 and is slidably connected with the positioning rod 34. Impact force during processing of the blade profile can be buffered by adjusting the arrangement of the springs 38; the outer end face of the adjusting nut 37 is provided with two adjusting holes, the distance between the adjusting nut 37 and the positioning section 341 can be adjusted through a special tool matched with the adjusting holes, so that the rebound force of the spring 38 can be adjusted, the pressure of the positioning rod 34 for clamping the blade profile 103 can be adjusted, and damage to the blade profile during clamping is avoided.

In addition, as shown in fig. 2 and 3, a limiting hole 332 is further provided on one side of the positioning hole 331, a limiting screw 39 in threaded connection with the limiting hole 332 is provided in the limiting hole 332, and the limiting screw 39 cooperates with a positioning plane provided on the positioning section 341 to limit the rotation of the positioning rod 34, so that the clamping of the positioning rod 34 is more stable.

The working principle of the double-shaft neck blade type face milling clamp of the aeroengine is as follows: when the fixture is used, the center pin holes of the transition discs 11 of the fixtures 1 and 2 are respectively centered with the center positioning holes on the machine tool workbench by using positioning pins, and then are connected to the machine tool by using inner hexagon bolts, and the axle necks at the two ends of the blade are respectively inserted into the fixtures 1 and 2; then the supporting mechanism 3 is arranged on the transition disc 11 of the clamp II 2, the adjusting screw 36 and the limiting screw 39 are unscrewed, the position of the adjusting nut 37 is adjusted, the positioning rod 34 on the positioning block 33 below the blade is adjusted to a proper position according to the thickness of the blade profile 103, then the adjusting screw 36 and the limiting screw 39 on the positioning block 33 are screwed, then the positioning rod 34 on the positioning block 33 above the blade is adjusted to a proper position according to the thickness of the blade profile, and the adjusting screw 36 and the limiting screw 39 on the positioning block 33 are screwed, so that the positioning rod 34 can stably and reliably press the blade profile 103; then machining the portion of the blade profile 103 near one end of journal one 101 (journal one of this embodiment is a small end journal); after the blade profile 103 at one end of the first journal 101 is partially machined, all the adjusting screws 36 and the limit screws 39 are unscrewed, and the two semicircular rings 31 are detached from the transition disc 11 of the second clamp 2 and are mounted on the transition disc 11 of the first clamp 1; similarly, the adjusting screw 36 and the limiting screw 39 are adjusted according to the adjusting mode, so that the positioning rod 34 can stably and reliably press the blade profile 103, and then the blade profile 103 near one end of the journal two 102 (the journal two in the embodiment is a big end journal) is processed, so that the processing of the blade profile is completed.

It will be evident to those skilled in the art that the utility model is not limited to the details of the foregoing illustrative embodiments, and that the present utility model may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, the scope of the utility model being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

Furthermore, it should be understood that although the present disclosure describes embodiments, not every embodiment is provided with a separate embodiment, and that this description is provided for clarity only, and that the disclosure is not limited to the embodiments described in detail below, and that the embodiments described in the examples may be combined as appropriate to form other embodiments that will be apparent to those skilled in the art.

Claims (8)

1. A double-shaft neck blade profile milling fixture of an aeroengine is characterized in that: the support mechanism is detachably connected with the first clamp or the second clamp; the supporting mechanism comprises two semicircular supporting mechanisms which are symmetrically arranged, the blade profile is positioned between the two semicircular supporting mechanisms, and the two semicircular supporting mechanisms support and position the middle part of the blade profile.

2. The dual journal blade profile milling fixture of an aircraft engine of claim 1, wherein: the first clamp comprises a transition disc and a first chassis, the transition disc is connected with a machine tool, the first chassis is connected with the transition disc through a fastener, and a positioning column at the front end of the first chassis is provided with a jack for positioning the first journal.

3. The dual journal blade profile milling fixture of an aircraft engine of claim 2, wherein: the second clamp comprises a transition disc and a second chassis, the transition disc is connected with the machine tool, the second chassis is connected with the transition disc through a fastener, and a jack for positioning the second journal is arranged on a positioning column at the front end of the second chassis.

4. A twin-journal blade profile milling fixture for an aircraft engine according to claim 1 or 3, characterized in that: the two semicircular supporting mechanisms are identical in structure and comprise semicircular rings, supporting bars, positioning blocks and positioning rods, the supporting bars are symmetrically arranged on the semicircular rings, the positioning blocks are fixed at the top ends of the supporting bars, the positioning rods movably connected with the positioning blocks are arranged on the positioning blocks, the two positioning blocks of the semicircular supporting mechanisms are connected through screws, accommodating cavities for accommodating blade profiles are formed in opposite sides of the two positioning blocks, the two positioning rods of the semicircular supporting mechanisms are oppositely arranged and extend into the accommodating cavities to support the positioning blade profiles, and one ends of the positioning rods, which are in contact with the blade profiles, are round heads.

5. The dual journal blade profile milling fixture of an aircraft engine of claim 4, wherein: the transition plate of the clamp I and the clamp II is provided with a plurality of mounting holes I which are uniformly distributed on the circumference, the semicircular ring is provided with a plurality of mounting holes II which are uniformly distributed on the circumference, and the semicircular ring is sleeved on the outer side of the chassis I or the outer side of the chassis II and fixedly connected with the transition plate through fasteners penetrating through the mounting holes I and the mounting holes II.

6. The dual journal blade profile milling fixture of an aircraft engine of claim 4, wherein: still be equipped with adjusting part in the locating piece, adjusting part includes adjusting screw, be equipped with the locating hole that corresponds the setting with the locating lever on the locating piece, the locating lever inserts and establishes in the locating hole and with locating hole sliding connection, the locating hole is close to the one end that holds the chamber and is equipped with the step, the locating lever middle part is equipped with the location section with step complex, adjusting screw locates the locating hole and keeps away from the one end that holds the chamber and with locating hole threaded connection.

7. The dual journal blade profile milling fixture of an aircraft engine of claim 6, wherein: the adjusting assembly further comprises an adjusting nut and a spring, wherein the adjusting nut is arranged between the positioning section and the adjusting screw, the adjusting nut is in threaded connection with the positioning hole, the spring sleeved outside the positioning rod is arranged between the adjusting nut and the positioning section, and the adjusting nut is sleeved outside the positioning rod and is in sliding connection with the positioning rod.

8. The dual journal blade profile milling fixture of an aircraft engine of claim 6, wherein: one side of the positioning hole is also provided with a limiting hole communicated with the positioning hole, a limiting screw in threaded connection with the limiting hole is arranged in the limiting hole, and the limiting screw is matched with a positioning plane arranged on the positioning section.