Aero-engine blade clamp

Abstract

The utility model discloses an aero-engine blade clamp which comprises a clamp base body. The first clamping module is fixedly assembled on the clamp base body, comprises a first clamping jaw module and is used for clamping and positioning one end of an engine blade; the second clamping module is connected to the clamp base body in a sliding mode and arranged opposite to the first clamping module, and a containing space is formed between the second clamping module and the first clamping module; comprising a second clamping jaw module used for clamping and positioning the other end of the engine blade; and the positioning and tensioning assembly is connected between the first clamping module and the second clamping module and used for positioning the second clamping module and the first clamping module after the second clamping module slides and is adjusted in place. According to the aero-engine blade clamp, the aero-engine blade is accurately positioned, and the accuracy of follow-up measurement of the aero-engine blade is guaranteed.

Description

Technical Field

[0001] The utility model belongs to the technical field of aeroengine blade clamps, and in particular relates to an improvement on the structure of an aeroengine blade clamp. Background Art

[0002] Aircraft engine blades are one of the key parts in aircraft engines. They have complex shapes, harsh stress, large size spans, and heavy loads. The geometric dimensions of the blades determine the working performance of the engine. Their shape and position are closely related to the characteristic parameters of the engine, the compression ratio of the compressor, the turbine speed, etc. Their quality and technical level directly affect the performance and life of the engine. Therefore, in the design, manufacturing and testing of blades, advanced testing technologies and management methods need to be adopted to ensure that the quality and performance of the blades are in the best state. Therefore, the geometric detection of engine blades is particularly important.

[0003] With the continuous improvement of aircraft engine performance, new requirements have been put forward for the inspection indicators of blade profiles after processing, especially the requirements for inspection accuracy and inspection efficiency are getting higher and higher. In order to meet these requirements, advanced inspection equipment and technology are needed to accurately measure and evaluate the profile, curvature, surface roughness, etc. of the blade profile.

[0004] The existing inspection of aircraft engine blades mainly relies on traditional measuring tools and techniques, such as calipers, micrometers, microscopes, etc. The inspection method is relatively simple, and the clamping and positioning configuration of aircraft engine blades during blade inspection is also relatively simple. When positioning the engine blades, it is sufficient to use existing fixture structures such as simple positioning clamps to press and position the blades in four directions. The blade positioning accuracy is not high, and the fixture positioning accuracy is poor when measuring the blades, which will also affect the accuracy of blade inspection and measurement.

[0005] The above information disclosed in the background technology is only used to increase the understanding of the background technology of the present application, and therefore, it may include information that does not constitute the prior art known to ordinary technicians in the field. Utility Model Content

[0006] The utility model aims at the above technical problems existing in the prior art and proposes a novel aircraft engine blade fixture, which can accurately position the aircraft engine blade and ensure the accuracy of subsequent measurement of the aircraft engine blade.

[0007] In order to achieve the above utility model / design purpose, the utility model adopts the following technical solutions:

[0008] An aerospace engine blade fixture, comprising:

[0009] A fixture base;

[0010] A first clamping module, fixedly mounted on the fixture base, comprises a first clamping claw module for clamping and positioning one end of the engine blade;

[0011] A second clamping module is slidably connected to the clamp base and is arranged opposite to the first clamping module, with a receiving space formed between the second clamping module and the first clamping module;

[0012] It includes: a second clamping claw module, used for clamping and positioning the other end of the engine blade;

[0013] The positioning and tightening assembly is connected between the first clamping module and the second clamping module, and is used to position the second clamping module and the first clamping module after the second clamping module is slidably adjusted into place.

[0014] Compared with the prior art, the advantages and positive effects of the utility model are:

[0015] The aviation blade engine fixture of the utility model is provided with a first clamping module and a second clamping module docked with the first clamping module. When clamping and positioning the engine blade, the engine blade can be placed in the accommodation space between the first clamping module and the second clamping module, and then one end of the engine blade is clamped and positioned by the first clamping claw module, and the other end of the engine blade is clamped and positioned by the second clamping claw module on the second clamping module, so as to achieve clamping and fixing of the engine blade, achieve accurate clamping and positioning of the engine blade, ensure the positioning effect of the engine blade, and further ensure the subsequent measurement accuracy of the engine blade;

[0016] In addition, the second clamping module can slide relative to the clamp base, so as to adjust the distance between the first clamping modules, so that it can adapt to engine blades of different models, thereby improving the versatility of the entire clamp.

[0017] After reading the specific embodiments of the present invention in conjunction with the accompanying drawings, other features and advantages of the present invention will become more clear. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0019] Figure 1 This is a schematic structural diagram of an engine blade assembled in a fixture in one embodiment of an aircraft engine blade fixture proposed by the utility model;

[0020] Figure 2It is a three-dimensional structure of an embodiment of the aircraft engine blade clamp proposed by the utility model Figure 1 ;

[0021] Figure 3 It is a three-dimensional structure of an embodiment of the aircraft engine blade clamp proposed by the utility model Figure 2 ;

[0022] Figure 4 It is a schematic structural diagram of the cooperation between the first clamping module and the second clamping module of the aero-engine blade clamp proposed by the utility model;

[0023] Figure 5 It is a top view of the aero-engine blade fixture proposed by the utility model;

[0024] Figure 6 yes Figure 5 BB section view;

[0025] Figure 7 yes Figure 5 AA section view;

[0026] Figure 8 The utility model is a schematic diagram of the structure of the positioning and tightening assembly of the aero-engine blade clamp.

[0027] In the figure, 100, clamp base; 110, first clamp base; 111, recessed portion; 120, second clamp base; 121, protruding portion; 130, positioning portion; 140, clamping operation portion; 200, second clamping module; 210, second clamping claw module; 211, first clamping claw portion; 220, second clamping base; 221, horizontal base portion; 222, vertical base portion; 223, supporting portion; 224, first supporting position; 225, first limiting portion; 3 00, first clamping module; 310, first clamping jaw module; 311, second clamping jaw part; 312, third clamping jaw part; 320, first clamping base; 321, protruding part; 322, second supporting position; 323, second limiting part; 400, accommodating space; 500, positioning and tightening assembly; 510, tightening component; 511, threaded screwing part; 520, elastic support member; 610, slider; 620, slide rail; 700, engine blade; 800, locking member. DETAILED DESCRIPTION

[0028] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0029] In the description of the present invention, it should be understood that the terms "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore, should not be understood as a limitation on the present invention.

[0030] In the description of the present utility model, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected" and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection. For ordinary technicians in this field, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances. In the description of the implementation method, specific features, structures, materials or characteristics can be combined in any one or more embodiments or examples in a suitable manner.

[0031] The terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features.

[0032] In the description of the present invention, unless otherwise specified, “plurality” means two or more.

[0033] In some embodiments of the present application, an aircraft engine blade fixture is provided, which is used to clamp and fix the aircraft engine blade to facilitate subsequent inspection and measurement of the aircraft engine blade.

[0034] For the convenience of description, the aircraft engine blade is referred to as engine blade 700 in this embodiment.

[0035] Aircraft engine blade fixture includes:

[0036] The clamp base 100 constitutes the support body of the entire clamp and is used to bear and support the entire clamp.

[0037] In some embodiments of the present application, the fixture base 100 includes:

[0038] A first clamp base 110 , wherein a recessed portion 111 is formed on the first clamp base 110 ;

[0039] and a second clamp base 120 , on which there is a protrusion 121 , which is inserted into the recess 111 through the protrusion 121 ;

[0040] The locking assembly passes through the first clamp base and is locked and fixed on the protrusion 121 to connect the first clamp base 110 and the second clamp base 120 .

[0041] The recessed portion 111 is a recessed groove formed by recessing from the first fixture base 110 .

[0042] The second fixture base 120 is inserted into the recessed groove through the protruding portion 121 to achieve insertion fit with the first fixture base 110 .

[0043] A plurality of threaded holes are provided on the protruding portion 121 .

[0044] The locking assembly includes a plurality of locking bolts or locking screws, which pass through the side wall of the first clamp base 110 and are screwed and fixed in the protrusion 121 to fix the first clamp base 110 and the second clamp base 120 together.

[0045] By configuring the fixture base 100 to be connected in a manner that the first fixture base 110 and the second fixture base 120 cooperate with each other, it is convenient to replace the first fixture base 110 or the second fixture base 120 .

[0046] The first clamping module 300 is fixedly mounted on the clamp base 100 and includes a first clamping claw module 310 for clamping and positioning one end of the engine blade;

[0047] The second clamping module 200 is slidably connected to the clamp base 100 and is disposed opposite to the first clamping module 300. An accommodating space 400 is formed between the second clamping module 200 and the first clamping module 300.

[0048] It includes: a second clamping claw module 210, used for clamping and positioning the other end of the engine blade;

[0049] The second clamping module 200 cooperates with the first clamping module 300 to achieve clamping and positioning of the engine blade.

[0050] The accommodation space 400 formed between the second clamping module 200 and the first clamping module 300 may be used to accommodate an engine blade.

[0051] When clamping and positioning the engine blades, the engine blades can be placed inside the accommodating space 400 between the second clamping module 200 and the first clamping module 300, and then one end of the engine blades is clamped and positioned by the second clamping module 210, and the other end of the engine blades is clamped and positioned by the first clamping module 310 on the first clamping module 300, so as to achieve clamping and fixing of the engine blades, achieve precise clamping and positioning of the engine blades, ensure the positioning effect of the engine blades, and further ensure the subsequent measurement accuracy of the engine blades.

[0052] The second clamping module 200 is slidably connected to the clamp base 100 , and the size of the accommodating space 400 can be changed by sliding the second clamping module 20 relative to the first clamping module 300 .

[0053] When a larger engine blade needs to be clamped and positioned, the second clamping module 200 can be slid outward to increase the distance between the first clamping module 300 and the second clamping module 200 so that the larger engine blade can be clamped and fixed.

[0054] When it is necessary to clamp and position a smaller engine blade, the second clamping module 200 can be slid inward to reduce the distance between the first clamping module 300 and the second clamping module 200, so that the smaller engine blade can be clamped and fixed. The second clamping module 200 can slide to adapt to different engine blades, thereby improving the versatility of the entire clamp.

[0055] The positioning and tightening assembly 500 is connected between the second clamping module 200 and the first clamping module 300, and is used to position the first clamping module 300 and the second clamping module 200 after the second clamping module 200 is slidably adjusted into place.

[0056] The positioning and tightening assembly 500 is mainly used to ensure that the first clamping module 300 can be kept at a sliding adjustment position relative to the second clamping module 200 after sliding into place.

[0057] The positioning and tightening assembly 500 is connected between the second clamping module 200 and the first clamping module 300, and can simultaneously apply a tightening force and a tensioning force to the second clamping module 200 and the first clamping module 300 to keep the second clamping module 200 and the first clamping module 300 at the positioning position for the engine blade.

[0058] In some embodiments, the positioning and tightening assembly 500 includes:

[0059] The tensioning member 510 is screwed into the first clamping module 300 and passes through the first clamping module 300, and a threaded screwing portion 511 is formed at the end thereof and is screwed into the second clamping module 200;

[0060] In some embodiments, the tensioning component 510 is a tensioning screw having a screw head formed at its end. The outer diameter of the screw head is greater than the outer diameter of the screw body. The threaded screwing portion 511 is an external thread segment formed at the end of the tensioning component 510 .

[0061] An inserting groove and a through groove communicating with the inserting groove are provided inside the first clamping module 300 , and the inserting groove is used to accommodate a screw head.

[0062] A connecting groove is provided on one end of the second clamping module 200 opposite to the first clamping module 300 . The connecting groove is arranged opposite to the through groove, and an internal thread is arranged in the connecting groove.

[0063] The tensioning component 510 passes through the insertion slot and the through slot and is screwed into the connecting slot through the threaded screwing portion 511. By continuously screwing the tensioning component 510 into the connecting slot, the second clamping module 200 and the first clamping module 300 can be tightened and connected together.

[0064] The screw head of the tensioning component 510 cooperates with the insertion slot to limit the tensioning component 510 and prevent it from escaping from the first clamping module 300 .

[0065] The elastic support member 520 is sleeved on the tensioning component 510 , with one end abutting against the second clamping module 200 and the other end abutting against the first clamping module 300 .

[0066] In some embodiments of the present application, the elastic support member 520 is a spring or an elastic sheet.

[0067] A first mounting groove is provided on one end of the second clamping module 200 , and a second mounting groove is provided on an end of the first clamping module 300 opposite to the second clamping module 200 .

[0068] The elastic support member 520 is sleeved on the tensioning component 510, partially located in the first installation groove and partially located in the second installation groove, and the two ends are respectively against the second clamping module 200 and the first clamping module 300 to apply a reverse elastic force to the second clamping module 200 and the first clamping module 300 respectively.

[0069] A mutual tensioning force is applied to the second clamping module 200 and the first clamping module 300 through the tensioning component 510, and an elastic outward spreading force is applied to the second clamping module 200 and the first clamping module 300 respectively through the elastic support component 520. The interaction and coordination of the two forces of the tensioning component 510 and the elastic support component 520 ensures that the second clamping module 200 and the first clamping module 300 can be stably maintained at the position for positioning the engine blades, thereby ensuring the firmness and accuracy of the positioning of the engine blades.

[0070] When the model of the engine blade to be clamped needs to be changed, the position of the second clamping module 200 can be adjusted accordingly.

[0071] Slide the second clamping module 200, and after it slides into place, screw the tensioning component 510 into the second clamping module 200 to tighten the two. At the same time, compress the elastic support member 520, and elastically support the second clamping module 200 and the first clamping module 300 through the elastic support member 520, so that the distance between the first clamping module 300 and the second clamping module 200 is adapted to the size of the engine blades.

[0072] In some embodiments, a thread groove is provided on the second clamping base 220, and the thread groove extends from the side of the second clamping base 220 to the connecting groove. A locking member 800 is screwed in the thread groove, which can be screwed on the inner end of the thread groove to abut against the side of the tensioning component 510 to further press and position the tensioning component 510.

[0073] The locking member 800 may be a locking screw or a locking bolt.

[0074] In some embodiments of the present application, the second clamping module 200 includes: a second clamping base 220 including: a transverse base portion 221;

[0075] The transverse base portion 221 is a transverse base plate, arranged horizontally.

[0076] A vertical base portion 222 , a support portion 223 protruding from the vertical base portion 222 , which is vertically arranged, and a first support position 224 is formed at the top of the support portion 223 ;

[0077] The vertical base portion 222 is a vertical base plate, and is disposed perpendicular to the horizontal base portion 221 .

[0078] The support portion 223 is formed by protruding from the side of the vertical base portion 222 and is a supporting boss.

[0079] The support portion 223 is smaller in height than the vertical base portion 222 , and a first limiting portion 225 for limiting the end of the engine blade is formed on the portion of the vertical base portion 222 that is higher than the support portion 223 .

[0080] The first limiting portion 225 is a first limiting section formed on the vertical base portion 222 and higher than the supporting portion 223 .

[0081] The engine blades include: front, rear, and sides.

[0082] The front and rear cross-sectional shapes are wavy.

[0083] When the engine blade is arranged inside the accommodating space 400, the bottom of the engine blade is set on the support part 223, and is supported by the support part 223. At the same time, the first limiting part 225 is used to block and limit the engine blade on its side.

[0084] In some embodiments of the present application, the second gripper module 210 includes:

[0085] There are two first clamping claws 211, which are symmetrically arranged at both sides of the support portion 223. The height of the first clamping claws 211 is higher than the support portion 223. The two first clamping claws 211 are respectively set at both sides of the engine blade to clamp and limit the engine blade.

[0086] The first clamping claw portion 211 is a first clamping claw, which is vertically arranged, and two are arranged, and can be used to clamp and fix the front and rear of the engine blade.

[0087] In order to achieve adaptation with the engine blades and to achieve a firm clamping and positioning of the engine blades, the first clamping jaw is set in a wave shape to match and clamp with the front of the engine blades to ensure the clamping effect of the engine blades.

[0088] In some embodiments, a through hole is provided on the first clamping jaw. When fixing, the first clamping jaw is fixed in the support portion 223 by passing a first locking screw through the through hole.

[0089] In some embodiments of the present application, the first clamping module 300 includes: a first clamping base 320;

[0090] A protrusion 321 is formed on the first clamping base 320 , a second support position 322 is formed on the top of the protrusion 321 , the protrusion 321 is smaller in height than the first clamping base 320 , and a second limiting portion 323 is formed on the first clamping base 320 above the protrusion 121 .

[0091] The first clamping base 320 is a second clamping base plate and is arranged vertically.

[0092] The other end of the engine blade can be supported and fixed by being placed at the second supporting position 322 on the protrusion 321 .

[0093] At the same time, the side surface of the other side of the engine blade is pressed against the second limiting portion 323 and is limited and fixed.

[0094] In some embodiments of the present application, the first clamping jaw module 310 includes: a second clamping jaw portion 311 , arranged at a side position of the protruding portion 321 ;

[0095] The third clamping jaw portion 312 cooperating with the second clamping jaw is extended from the protruding portion 321 , arranged at the other side of the protruding portion 321 , and opposite to the second clamping jaw portion 311 .

[0096] The second clamping claw portion 311 and the third clamping claw portion 312 cooperate to clamp and position the other end of the engine blade.

[0097] In order to achieve adaptation with the engine blade, the second clamping claw portion 311 is correspondingly configured to imitate the front face of the engine blade and is configured to be wavy.

[0098] The third clamping claw portion 312 is also configured to conform to the shape of the engine blade and is configured to be wavy in shape to ensure that the engine blade is firmly clamped.

[0099] In some embodiments of the present application, a sliding component is provided between the second clamping module 200 and the clamp base 100. By arranging the sliding component between the second clamping module 200 and the clamp base 100, it can be ensured that the second clamping module 200 can slide relative to the clamp base 100 to change and adjust the position.

[0100] In some embodiments, the sliding assembly includes a slider 610 and a slide rail 620, wherein the slider 610 is fixed on the second clamping module 200, and the slide rail 620 is fixed on the clamp base 100 and extends from the second clamping module 200 to the position of the first clamping module 300. When sliding, the second clamping module 200 can slide along the slide rail 620 through the slider 610 at the bottom thereof in a direction away from the first clamping module 300 or close to the first clamping module 300.

[0101] In some embodiments of the present application, a positioning portion 130 is formed at the bottom of the clamp base 100 for facilitating placement of the clamp on the clamp frame. A plurality of positioning portions 130 are provided and are evenly arranged at the bottom of the clamp base 100 .

[0102] The positioning portion 130 is a positioning protruding column formed at the bottom of the clamp base 100 . A plurality of positioning protruding columns are provided and are evenly arranged at the bottom of the clamp base 100 .

[0103] Positioning holes are correspondingly arranged on the clamp frame, and the clamp can be directly inserted into the positioning holes on the clamp frame through the positioning portion 130 at the bottom, which is convenient for placing and storing the engine blade clamp.

[0104] In some embodiments of the present application, a clamping operation portion 140 is formed at the bottom of the clamp base 100 for facilitating clamping operations.

[0105] The clamping operation portion 140 is a clamping operation protrusion to facilitate the clamping operation.

[0106] If the engine blades need to be measured through an automatic line, the engine blades may need to be moved. The engine blade clamp that positions the engine blades can facilitate the transfer of the engine blades. The clamping operation part 140 can facilitate the clamping operation of the entire clamp and the blades, thereby facilitating clamping and docking.

[0107] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for a person skilled in the art to modify the technical solutions described in the aforementioned embodiments, or to replace some of the technical features therein by equivalents. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions claimed to be protected by the present invention.

Claims

1. An aircraft engine blade fixture, characterized in that: Included are: A fixture base; A first clamping module, fixedly mounted on the fixture base, comprises a first clamping claw module for clamping and positioning one end of the engine blade; A second clamping module is slidably connected to the clamp base and is arranged opposite to the first clamping module, with a receiving space formed between the second clamping module and the first clamping module; It includes: a second clamping claw module, used for clamping and positioning the other end of the engine blade; The positioning and tightening assembly is connected between the first clamping module and the second clamping module, and is used to position the second clamping module and the first clamping module after the second clamping module is slidably adjusted into place.

2. The aircraft engine blade fixture according to claim 1, characterized in that: The second clamping module comprises: a second clamping base, comprising: a transverse base portion; A vertical base portion, a support portion protruding from the vertical base portion, which is vertically arranged, and a first support position is formed at the top of the support portion; The support portion is smaller in height than the vertical base portion, and a first limiting portion for limiting the end of the engine blade is formed at a portion of the vertical base portion that is higher than the support portion.

3. The aircraft engine blade fixture according to claim 2, characterized in that: The second gripper module includes: There are two first clamping jaws, which are symmetrically arranged at both sides of the support portion. Their height is higher than the support portion. The two first clamping jaws are respectively arranged at both sides of the engine blade to clamp and limit the engine blade.

4. The aircraft engine blade fixture according to claim 1, characterized in that: The first clamping module includes: a first clamping base; A protrusion is formed on the first clamping base, a second support position is formed on the top of the protrusion, the height of the protrusion is smaller than the first clamping base, and a second limiting portion is formed on the first clamping base above the protrusion.

5. The aircraft engine blade fixture according to claim 4, characterized in that: The first clamping claw module includes: a second clamping claw portion, arranged at one side of the protruding portion; And a third clamping jaw part matched with the second clamping jaw is extended from the protruding part, arranged at the other side of the protruding part, and arranged opposite to the second clamping jaw part.

6. The aircraft engine blade fixture according to claim 1, characterized in that: A sliding assembly is provided between the second clamping module and the clamp base; The sliding assembly includes a sliding block and a sliding rail. The sliding block is fixed on the second clamping module. The sliding rail is fixed on the clamp base and extends from the second clamping module to the position of the first clamping module.

7. The aircraft engine blade fixture according to claim 1, characterized in that: The positioning and tightening assembly comprises: A tensioning component is assembled in the first clamping module and passes through the first clamping module, and a threaded screwing portion screwed into the second clamping module is formed at an end thereof; The elastic support member is sleeved on the tensioning component, one end of which abuts against the first clamping module, and the other end of which abuts against the second clamping module.

8. The aircraft engine blade fixture according to claim 1, characterized in that: The fixture base comprises: a first fixture base, wherein a recessed portion is formed on the first fixture base; and a second clamp base, on which there is a protrusion, which is inserted into the recess through the protrusion; The locking assembly passes through the first clamp base and is locked and fixed on the protruding portion to connect the first clamp base and the second clamp base.

9. The aircraft engine blade fixture according to claim 1, characterized in that: A positioning portion is formed at the bottom of the clamp base for facilitating placement of the clamp on the clamp frame. A plurality of positioning portions are provided and are evenly arranged at the bottom of the clamp base.

10. The aircraft engine blade fixture according to claim 1, characterized in that: A clamping operation portion for facilitating clamping operation is formed at the bottom of the clamp base.

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