CN114770163A - Fastening mechanism and method for turbine disc blade of aircraft engine - Google Patents
Fastening mechanism and method for turbine disc blade of aircraft engine Download PDFInfo
- Publication number
- CN114770163A CN114770163A CN202210461064.6A CN202210461064A CN114770163A CN 114770163 A CN114770163 A CN 114770163A CN 202210461064 A CN202210461064 A CN 202210461064A CN 114770163 A CN114770163 A CN 114770163A
- Authority
- CN
- China
- Prior art keywords
- plate
- limiting
- clamping
- blade
- wall
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 230000007246 mechanism Effects 0.000 title claims abstract description 89
- 238000000034 method Methods 0.000 title claims abstract description 16
- 238000003825 pressing Methods 0.000 claims description 10
- 238000012545 processing Methods 0.000 claims description 9
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 206010044565 Tremor Diseases 0.000 abstract 1
- 238000003754 machining Methods 0.000 abstract 1
- 244000145845 chattering Species 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000004891 communication Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q3/00—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine
- B23Q3/02—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine for mounting on a work-table, tool-slide, or analogous part
- B23Q3/06—Work-clamping means
- B23Q3/062—Work-clamping means adapted for holding workpieces having a special form or being made from a special material
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Connection Of Plates (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a fastening mechanism and a fastening method for turbine disc blades of an aircraft engine, and particularly relates to the field of aircraft parts. The first clamping mechanism is used for fixing the blade tip part of the turbine disc blade, the second clamping mechanism is used for fixing the tenon part of the turbine disc blade, and the two ends of the turbine blade are respectively clamped, so that the situation that the blade is deformed due to trembling generated in subsequent machining is avoided.
Description
Technical Field
The invention relates to the technical field of aviation parts, in particular to a fastening mechanism and a fastening method for blades of a turbine disk of an aero-engine.
Background
Turbine blades are important components of the turbine section of gas turbine engines, where metal fatigue of the blades is the leading cause of engine failure. Strong vibration or resonance can cause metal fatigue.
In the production and processing process of the blades of the turbine disc of the aero-engine, the blades are likely to deform due to strong vibration or resonance, particularly, the blades with the special-shaped blade crown are processed, and due to the fact that the blades belong to cantilever processing of slender thin-wall parts, processing vibration and deformation are prone to occurring, and accordingly the reject ratio is high, and therefore the problems are solved through the fastening mechanism and the method for the blades of the turbine disc of the aero-engine.
Disclosure of Invention
In order to overcome the above defects in the prior art, embodiments of the present invention provide a fastening mechanism and a method for fastening a blade of a turbine disk of an aircraft engine, in which a first clamping mechanism and a second clamping mechanism are provided to clamp two ends of a turbine blade, respectively, so as to solve the above problems in the background art.
In order to achieve the above object, one object of the present invention is to provide the following technical solutions:
a fastening mechanism for a turbine disc blade of an aircraft engine comprises a first clamping mechanism, wherein a second clamping mechanism is arranged at the bottom of the first clamping mechanism, and vertical center lines of the first clamping mechanism and the second clamping mechanism are arranged on the same plane;
the first clamping mechanism comprises a first bearing plate, one side of the first bearing plate is rotatably connected with two supporting frames, positioning plates are arranged at the tops of the two supporting frames and fixed through a first positioning screw rod, a pressing plate arranged in an inclined manner is assembled at one side of the supporting frame, a limiting convex block and a limiting concave block are fixedly mounted at one side of the pressing plate, and the limiting convex block and the limiting concave block are tightly attached together and arranged in a hump shape;
the turbine disc blade fastening mechanism further comprises a first driving mechanism, and the first driving mechanism drives the supporting frame to deflect to the surface of the accessory;
the second clamping mechanism comprises two third clamping plates, limiting teeth are fixedly arranged on one side of each third clamping plate, a limiting seat is hinged between the two third clamping plates, and the limiting seat and the two third clamping plates are assembled together to form a V shape;
the turbine disk blade fastening mechanism further includes a second drive mechanism that drives the second adapter plate and the cable spring to deflect toward the fitting surface.
In a preferred embodiment, the pressing plate is assembled on one side of the support frame in an inclined state, a second bracket is fixedly installed on one side of the pressing plate, and a wave spring connected with the support frame is fixedly installed on one side of the second bracket.
In a preferred embodiment, the first driving mechanism comprises a second connector tile, the second connector tile is hinged at two sides thereof to a first connector tile and a third connector tile connected to the support frame, the third connector tile is hinged at the top thereof to a fourth connector tile connected to the first support panel, the second connector tile is driven to rotate by external power, and the support frame is pushed to deflect by the first connector tile, the third connector tile and the fourth connector tile.
In a preferred embodiment the retaining plate is fixedly mounted on top of the second connector tiles and the bottom of the second connector tiles is provided with a first bracket connected to the first support plate.
In a preferred embodiment, a pivot post connected to the first connector tile is rotatably connected to an inner portion of the support frame, and a rope spring connected to the third connector tile is fitted to an outer wall of the pivot post.
In a preferred embodiment, the second driving mechanism includes a second positioning screw rod disposed at the bottom of the limiting seat, a second bearing plate is sleeved on an outer wall of the second positioning screw rod, two first clamping plates symmetrically disposed are fixedly mounted on an outer surface of the second bearing plate, a second clamping plate connected with a third clamping plate is hinged to the top of the first clamping plate, a handle is fixedly connected to the bottom of the second positioning screw rod, and the handle drives the second positioning screw rod to rotate through external power.
In a preferable embodiment, the second clamping plates are arranged in a shape like a Chinese character '7', the number of the second clamping plates is two, the two second clamping plates are arranged in mirror symmetry with respect to a vertical center line of the second bearing plate, and one side of each second clamping plate is hinged with an auxiliary block.
In a preferred embodiment, the number of the second supporting plates is at least two, gear discs are fixedly mounted at the bottoms of the two second supporting plates, and the outer walls of the gear discs arranged on the two second supporting plates are engaged with the conveyor belt.
In a preferred embodiment, the supporting mechanism comprises a base, the base is fixedly connected with the second bearing plate, a slide bar and a limiting plate are fixedly mounted at the top of the base, and a first slide block connected with the first bearing plate is slidably mounted on the outer wall of the limiting plate;
two limiting sliding grooves are formed in the inner wall of the first sliding block, two limiting sliding strips are fixedly mounted on the outer wall of the sliding rod, and the limiting sliding strips slide in the inner cavities of the limiting sliding grooves formed in the inner wall of the first sliding block.
In a preferred embodiment, a second slider connected with the first slider is sleeved on the outer wall of the limiting plate, a moving groove is formed in the limiting plate in a penetrating manner, a positioning rod is inserted into the second slider, penetrates through the limiting plate and the inner cavity of the second slider, and is attached to the outer surface of the sliding rod;
a plurality of fixed slots have been seted up to the outer wall of slide bar equidistance in proper order, the locating lever orders about the inner chamber of grafting at the slide bar through external force.
In a preferred embodiment, another object of the present invention is to provide a fastening method of the fastening mechanism for the blade of the turbine disk of the aircraft engine, which adopts the following technical solutions:
a fastening method of an aircraft engine turbine disk blade fastening mechanism comprises the following steps:
the method comprises the following steps that firstly, a tenon position of a turbine disc blade is placed between a third clamping plate and a limiting seat, and the angle between the third clamping plate and the third clamping plate is adjusted, so that the third clamping plate is tightly attached to the outer wall of the tenon position of the turbine disc blade;
secondly, adjusting the position of the first sliding block according to the length of the turbine disc blade, and further adjusting the first supporting plate to be close to the height of the tip part of the turbine disc blade;
and thirdly, after the height is adjusted, placing the blade tip part of the turbine disc blade between the two first bearing plates, and simultaneously deflecting and adjusting the two first bearing plates to enable the limiting convex block and the limiting concave block to be attached to the outer wall of the blade tip, so that the turbine disc blade can be fastened and installed for subsequent processing and use.
The invention has the technical effects and advantages that:
according to the invention, the angle between the two support frames is adjusted according to different blade surfaces of the twisted surface, so that the support frames and the first bearing plate are in a vertical state, and the convex peak of the limiting convex block is simultaneously pressed against the blade tip surface to form clamping, so that the twisted surface-smoother turbine disc blade fixing device is suitable for fixing the twisted surface-smoother turbine disc blade, or the two support frames are parallel or supported relative to the first bearing plate, so that the limiting convex block and the limiting concave block are mutually staggered and pressed against the surface of the blade to clamp the blade, so that the twisted surface-smoother turbine disc blade fixing device is suitable for fixing the twisted surface-smoother turbine disc blade, and meanwhile, the third clamping plate is combined to be pressed against the outer wall of the rabbet part of the turbine disc blade to respectively clamp two ends of the turbine blade, so that the blade is prevented from being deformed due to chatter generated in subsequent processing.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention.
Fig. 2 is a schematic overall structure diagram of the first clamping mechanism of the present invention.
FIG. 3 is an enlarged view of the portion A of FIG. 2 according to the present invention.
FIG. 4 is an enlarged view of the portion B of FIG. 2 according to the present invention.
Fig. 5 is a schematic view of the overall structure of the second clamping mechanism of the present invention.
Fig. 6 is a schematic back structure of the present invention.
FIG. 7 is an enlarged view of the structure of the portion C of FIG. 6 according to the present invention.
The reference signs are: the device comprises a supporting mechanism 1, a base 101, a sliding rod 102, a limiting plate 103, a first sliding block 104, a second sliding block 105, a moving groove 106, a positioning rod 107, a fixing groove 108, a limiting slide bar 109, a first clamping mechanism 2, a first bearing plate 21, a supporting frame 22, a rotating column 23, a first connecting plate 24, a second connecting plate 25, a third connecting plate 26, a rope spring 27, a pressing plate 28, a limiting convex block 29, a limiting concave block 210, a fourth connecting plate 211, a positioning plate 212, a first positioning screw 213, a first bracket 214, a second bracket 215, a wave spring 216, a second clamping mechanism 3, a second bearing plate 31, a second positioning screw 32, a first clamping plate 33, a second clamping plate 34, a third clamping plate 35, a limiting seat 36, a limiting tooth 37, an auxiliary block 38, a gear plate 39, a conveying belt 310 and a handle 311.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to the attached drawings 1 to 7 in the specification, the fastening mechanism for turbine disc blades of an aircraft engine according to an embodiment of the present invention includes a supporting mechanism 1, a first clamping mechanism 2 and a second clamping mechanism 3, the first clamping mechanism 2 is configured to fix a blade tip portion of a turbine disc blade, the second clamping mechanism 3 is configured to fix a rabbet portion of the turbine disc blade, and the supporting mechanism 1 is configured to adjust a distance between the first clamping mechanism 2 and the second clamping mechanism 3 to be suitable for fixing blades of different lengths, where, as shown in fig. 6, the supporting mechanism 1 includes a base 101, a slide bar 102 and a limit plate 103 are fixedly installed on a top of the base 101, a first slider 104 is slidably installed on an outer wall of the limit plate 103, and, as shown in fig. 7, two limit chutes are formed on an inner wall of the first slider 104, two limit sliders 109 are fixedly installed on an outer wall of the slide bar 102, the limit sliders 109 slide in a limit chute inner cavity formed on an inner wall of the first slider 104, the limiting sliding strips 109 and the limiting sliding grooves on the inner wall of the first sliding block 104 are symmetrically arranged to prevent the first sliding block 104 from deflecting in the sliding process of the outer wall of the sliding rod 102, meanwhile, the outer wall of the limiting plate 103 is sleeved with a second sliding block 105 connected with the first sliding block 104, in order to fix the position of the first sliding block 104 conveniently, a moving groove 106 is arranged on the limiting plate 103 in a penetrating manner, a positioning rod 107 is inserted into the second sliding block 105, the positioning rod 107 penetrates through the inner cavities of the limiting plate 103 and the second sliding block 105 and is attached to the outer surface of the sliding rod 102, a plurality of fixing grooves 108 are arranged on the outer wall of the sliding rod 102 at equal intervals in sequence, the positioning rod 107 is driven to be inserted into the inner cavity of the sliding rod 102 through external force, under normal conditions, the first sliding block 104 slides on the outer wall of the sliding rod 102, the second sliding block 105 slides on the outer wall of the limiting plate 103, and the positioning rod 107 slides in the inner cavity of the moving groove 106, and one end of the positioning rod 107 is attached to the outer wall of the sliding rod 102 to move, and when the position of the first slider 104 needs to be fixed, the positioning rod 107 is pressed towards the direction of the sliding rod 102, so that the positioning rod 107 is inserted into the inner cavity of the fixing groove 108, and the second slider 105 and the first slider 104 can be fixed on the limiting plate 103 and the outer wall of the sliding rod 102 respectively.
In this embodiment, the turbine disk blade fastening mechanism further includes a first clamping mechanism 2 for fixing the turbine blade, a second clamping mechanism 3, a first driving mechanism and a second driving mechanism, as shown in fig. 2, the vertical center lines of the first clamping mechanism 2 and the second clamping mechanism 3 are disposed on the same plane, the first clamping mechanism 2 and the second clamping mechanism 3 are both connected to the supporting mechanism 1, the first driving mechanism drives the first clamping mechanism 2 to deflect to the tip part surface of the turbine disk blade and clamp and fix the tip part surface, and the second driving mechanism drives the second clamping mechanism 3 to clamp and fix the tip part of the turbine disk blade, so as to avoid the blade from deforming due to chattering generated during subsequent processing.
In the present embodiment, referring to fig. 3, the first clamping mechanism 2 includes a first supporting plate 21, the first supporting plate 21 is fixedly installed on one side of the first slider 104, the position of the first supporting plate 21 can be synchronously adjusted by adjusting the position of the first slider 104, two supporting frames 22 are rotatably connected to one side of the first supporting plate 21, a pressure plate 28 disposed in an inclined manner is assembled on one side of each supporting frame 22, because the surface shape of the turbine blade is usually designed to be a twisted variable cross-section curved surface and the shape is complicated, a limiting convex block 29 and a limiting concave block 210 are fixedly installed on one side of the pressure plate 28, the surfaces of the limiting convex block 29 and the limiting concave block 210 are both set to be an arc shape capable of adapting to the arc surface of the blade tip, the limiting convex block 29 and the limiting concave block 210 are set in a hump shape when being tightly attached together, and the pressure plate 28 is assembled on one side of the supporting frame 22 in an inclined state, the second bracket 215 is fixedly installed on one side of the pressing plate 28, the wave spring 216 connected with the supporting frames 22 is fixedly installed on one side of the second bracket 215, when the surface of the blade with a relatively flat twisted surface is attached to the limiting convex block 29 and the limiting concave block 210, the two supporting frames 22 are in a vertical state with the first supporting plate 21, the convex peaks of the limiting convex block 29 arranged on the supporting frames 22 simultaneously abut against the surface of the blade tip to form clamping, when the twisted surface is twisted, the two supporting frames 22 deflect relative to the first supporting plate 21, the two supporting frames 22 are parallel or supported relative to the first supporting plate 21 in a relatively inclined state, and at the moment, the limiting convex block 29 and the limiting concave block 210 arranged on the two supporting frames 22 are mutually staggered to abut against the surface of the blade to clamp the blade.
As shown in fig. 2 and 4, the assembly in this embodiment further comprises a first drive mechanism comprising a second connector tile 25, the second connector tile 25 being hinged on either side to first and third connector tiles 24 and 26 respectively connected to the support frame 22, the third connector tile 26 being hinged on top to a fourth connector tile 211 connected to the first support panel 21, the second connector tile 25 being driven to rotate by external power and the support frame 22 being urged to deflect by the first and third connector tiles 24 and 26 and the fourth connector tile 211, and in use the position of the support frame 22 being rapidly adjustable by moving the second connector tile 25 to urge the third and first connector tiles 26 and 24 in combination with the spacing of the fourth connector tile 211 to cause the support frame 22 to deflect about a circular axis about the point of connection with the first support panel 21.
Referring to fig. 3, the second connector tile 25 is provided at the bottom thereof with a first bracket 214 connected to the first support plate 21, the second connector tile 25 is deflectable around the first support plate 21 by the first bracket 214, a pivot post 23 connected to the first connector tile 24 is rotatably connected to the inside of the support frame 22, a rope spring 27 connected to the third connector tile 26 is sleeved on the outer wall of the pivot post 23, the third connector tile 26, the support frame 22 and the first connector tile 24 can be held by the rope spring 27 and the pivot post 23, and the position of the support frame 22 can be adjusted by moving the second connector tile 25 so that the two support frames 22 can be held while holding the blades, the positioning plates 212 are provided at the tops of the two support frames 22, and the two positioning plates 212 are fixed by a first positioning screw 213, the positioning plates 212 are fixedly installed at the top of the second connector tile 25, after the position of the supporting frame 22 is adjusted, the two positioning plates 212 are connected by the first positioning screw 213, and the nut is sleeved on the outer wall of the first positioning screw 213 for fixing, so that the distance between the two positioning plates 212 is fixed.
Referring to fig. 5, the second clamping mechanism 3 includes two third clamping plates 35, a limiting tooth 37 is fixedly mounted on one side of each third clamping plate 35, a limiting seat 36 is hinged between the two third clamping plates 35, the limiting seat 36 and the two third clamping plates 35 are assembled together to form a V-shaped arrangement, when the tenon portion of the turbine disc blade is fixed, the tenon portion of the turbine disc blade is placed on the limiting seat 36, and then the distance between the two third clamping plates 35 is adjusted, so that the second connecting plate 25 and the limiting tooth 37 are attached to the outer wall of the tenon portion of the turbine disc blade.
The assembly in this embodiment further includes a second driving mechanism, the second driving mechanism includes a second positioning screw 32 disposed at the bottom of the limiting seat 36, a second supporting plate 31 is sleeved on an outer wall of the second positioning screw 32, two first clamping plates 33 symmetrically disposed are fixedly mounted on an outer surface of the second supporting plate 31, a second clamping plate 34 connected with a third clamping plate 35 is hinged to a top of the first clamping plate 33, the bottom of the second positioning screw 32 is fixedly connected to rotate to drive the second positioning screw 32 to rotate and when the inner cavity of the second supporting plate 31 moves downward, the second positioning screw 32 moving downward pulls the limiting seat 36 to move downward, the outer side of the third clamping plate 35 abuts against the first clamping plate 33, so that the third clamping plate 35 pulls the second clamping plate 34 to deflect to the central position of the second positioning screw 32, and the third clamping plate 35 is clamped inwards to the outer wall of the tenon part of the turbine disc blade.
Wherein, the second clamping plate 34 is arranged in a shape like a Chinese character '7', the number of the second clamping plates 34 is two, the two second clamping plates 34 are arranged in mirror symmetry about the vertical center line of the second bearing plate 31, one side of the second clamping plate 34 is hinged with an auxiliary block 38, when the third clamping plate 35 pulls the second clamping plate 34 to deflect to the center position of the second positioning screw 32, the second clamping plate 34 deflects inwards at the same time to make the auxiliary block 38 attached to the outer wall of the turbine blade for auxiliary clamping, for being suitable for blades with different sizes, the second bearing plate 31 is at least arranged in two, gear discs 39 are fixedly arranged at the bottoms of the two second bearing plates 31, the outer walls of the gear discs 39 arranged on the two second bearing plates 31 are engaged with a conveyor belt 310, when the tenon position of the turbine blade is larger, the tenon position can be placed between the two turbine blade limit seats 36 through the two second bearing plates 31, so that the plurality of third clamping plates 35 simultaneously carry out the limiting clamping on the outer wall of the tenon.
The invention also aims to provide a fastening method of the fastening mechanism of the turbine disk blade of the aircraft engine, which adopts the following technical scheme:
a fastening method of an aircraft engine turbine disk blade fastening mechanism comprises the following steps:
firstly, placing the tenon part of the turbine disc blade between a third clamping plate 35 and a limiting seat 36, and adjusting the angle between the third clamping plate 35 and the third clamping plate 35 to enable the third clamping plate 35 to be tightly attached to the outer wall of the tenon part of the turbine disc blade;
secondly, adjusting the position of the first sliding block 104 according to the length of the turbine disc blade, and further adjusting the first bearing plate 21 to a height close to the tip of the turbine disc blade;
thirdly, after the height is adjusted, the tip part of the turbine disc blade is placed between the two first supporting plates 21, the two first supporting plates 21 are deflected and adjusted at the same time, and the limiting convex block 29 and the limiting concave block 210 are attached to the outer wall of the tip part, so that the turbine disc blade can be fastened and installed for subsequent processing and use.
The working principle is as follows: when the turbine disk blade tip positioning device is in actual use, firstly, the tenon part of the turbine disk blade is placed between the third clamping plate 35 and the limiting seat 36, the height of the second positioning screw rod 32 in the inner cavity of the second bearing plate 31 is adjusted through rotating the handle 311, the effect of adjusting the angle between the third clamping plate 35 and the third clamping plate 35 is achieved, the third clamping plate 35 is tightly attached to the outer wall of the tenon part of the turbine disk blade, then, the position of the first slider 104 is adjusted according to the length of the turbine disk blade, further, the first bearing plate 21 is adjusted to be close to the height of the blade tip part of the turbine disk blade, then, the part of the turbine disk blade is placed between the two first bearing plates 21, meanwhile, the two first bearing plates 21 are deflected and adjusted, the limiting convex block 29 and the limiting concave block 210 are attached to the outer wall of the blade tip, when the surface of the blade with a smooth twisted curved surface is attached to the limiting convex block 29 and the limiting concave block 210, the two support frames 22 and the first support plate 21 are in a vertical state, at this time, the convex peak of the limiting convex block 29 is simultaneously pressed against the surface of the blade tip to form clamping, when the twisted surface is twisted, the two support frames 22 are either parallel or relatively inclined with respect to the first support plate 21 to support, at this time, the limiting convex block 29 and the limiting concave block 210 arranged on the two support frames 22 are mutually dislocated and pressed against the surface of the blade to clamp the blade, and thus, the blade is prevented from being deformed due to chattering in subsequent processing.
The points to be finally explained are: first, in the description of the present application, it should be noted that, unless otherwise specified and limited, the terms "mounted," "connected," and "connected" should be understood broadly, and may be a mechanical connection or an electrical connection, or a communication between two elements, and may be a direct connection, and "upper," "lower," "left," and "right" are only used to indicate a relative positional relationship, and when the absolute position of the object to be described is changed, the relative positional relationship may be changed;
secondly, the method comprises the following steps: in the drawings of the disclosed embodiments of the invention, only the structures related to the disclosed embodiments are referred to, other structures can refer to common designs, and the same embodiment and different embodiments of the invention can be combined with each other without conflict;
and finally: the above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that are within the spirit and principle of the present invention are intended to be included in the scope of the present invention.
Claims (10)
1. A fastening mechanism for blades of a turbine disc of an aircraft engine comprises a first clamping mechanism (2), wherein a second clamping mechanism (3) is arranged at the bottom of the first clamping mechanism (2), and vertical center lines of the first clamping mechanism (2) and the second clamping mechanism (3) are arranged on the same plane;
the method is characterized in that:
the first clamping mechanism (2) comprises a first bearing plate (21), one side of the first bearing plate (21) is rotatably connected with two supporting frames (22), positioning plates (212) are arranged at the tops of the two supporting frames (22), the two positioning plates (212) are fixed through first positioning screws (213), one side of each supporting frame (22) is provided with a pressing plate (28) which is arranged in an inclined manner, one side of each pressing plate (28) is fixedly provided with a limiting convex block (29) and a limiting concave block (210), and the limiting convex block (29) and the limiting concave block (210) are tightly attached together and arranged in a hump shape;
the turbine disk blade fastening mechanism further comprises a first driving mechanism, and the first driving mechanism drives the supporting frame (22) to deflect to the surface of the accessory;
the second clamping mechanism (3) comprises two third clamping plates (35), a limiting tooth (37) is fixedly mounted on one side of each third clamping plate (35), a limiting seat (36) is hinged between the two third clamping plates (35), and the limiting seat (36) and the two third clamping plates (35) are assembled together to form a V-shaped arrangement;
the turbine disc blade fastening mechanism further comprises a second drive mechanism which drives the second connector plate (25) and the cable spring (27) to deflect to the fitting surface.
2. An aircraft engine turbine disk blade fastening mechanism according to claim 1, wherein: the pressing plate (28) is assembled on one side of the supporting frame (22) in an inclined state, a second bracket (215) is fixedly installed on one side of the pressing plate (28), and a wave spring (216) connected with the supporting frame (22) is fixedly installed on one side of the second bracket (215).
3. An aircraft engine turbine disk blade fastening mechanism according to claim 2, wherein: the first driving mechanism comprises a second connecting plate (25), a first connecting plate (24) and a third connecting plate (26) which are connected with a supporting frame (22) are hinged to two sides of the second connecting plate (25) respectively, a fourth connecting plate (211) which is connected with a first bearing plate (21) is hinged to the top of the third connecting plate (26), the second connecting plate (25) is driven to rotate through external power, and the supporting frame (22) is pushed to deflect through the first connecting plate (24), the third connecting plate (26) and the fourth connecting plate (211).
4. An aircraft engine turbine disk blade fastening mechanism according to claim 3, wherein: the positioning plate (212) is fixedly arranged at the top of the second connecting plate (25), and a first bracket (214) connected with the first bearing plate (21) is arranged at the bottom of the second connecting plate (25).
5. An aircraft engine turbine disk blade fastening mechanism according to claim 4, wherein: the inside of support frame (22) is rotated and is connected with the rotary column (23) that is connected with first linkage plate (24), the outer wall cover of rotary column (23) is equipped with rope spring (27) that are connected with third linkage plate (26).
6. An aircraft engine turbine disk blade fastening mechanism according to claim 1 or 5, wherein: second actuating mechanism is including setting up second positioning screw (32) in spacing seat (36) bottom, the outer wall cover of second positioning screw (32) is equipped with second bearing board (31), the outer fixed surface of second bearing board (31) installs two first splint (33) that are the symmetry and set up, the top of first splint (33) articulates there is second splint (34) that are connected with third splint (35), the bottom fixedly connected with handle (311) of second positioning screw (32), just handle (311) order about second positioning screw (32) through external power and rotate.
7. An aircraft engine turbine disk blade fastening mechanism according to claim 6, wherein: second splint (34) are "7" font setting, just the quantity of second splint (34) sets up to two, two second splint (34) are mirror symmetry setting about the vertical central line to of second bearing board (31), one side of second splint (34) articulates there is supplementary piece (38).
8. An aircraft engine turbine disk blade fastening mechanism according to claim 7, wherein: the number of the second bearing plates (31) is at least two, gear discs (39) are fixedly mounted at the bottoms of the two second bearing plates (31), and the outer walls of the gear discs (39) arranged on the two second bearing plates (31) are meshed with the conveyor belt (310).
9. An aircraft engine turbine disk blade fastening mechanism according to claim 8, wherein: the supporting mechanism (1) comprises a base (101), the base (101) is fixedly connected with a second bearing plate (31), a sliding rod (102) and a limiting plate (103) are fixedly mounted at the top of the base (101), and a first sliding block (104) connected with a first bearing plate (21) is slidably mounted on the outer wall of the limiting plate (103);
two limiting sliding grooves are formed in the inner wall of the first sliding block (104), two limiting sliding strips (109) are fixedly mounted on the outer wall of the sliding rod (102), and the limiting sliding strips (109) slide in an inner cavity of the limiting sliding grooves formed in the inner wall of the first sliding block (104);
a second sliding block (105) connected with the first sliding block (104) is sleeved on the outer wall of the limiting plate (103), a moving groove (106) is formed in the limiting plate (103) in a penetrating mode, a positioning rod (107) is inserted into the second sliding block (105), and the positioning rod (107) penetrates through the limiting plate (103) and the inner cavity of the second sliding block (105) and is attached to the outer surface of the sliding rod (102);
a plurality of fixing grooves (108) are sequentially formed in the outer wall of the sliding rod (102) at equal intervals, and the positioning rod (107) is driven by external force to be inserted into the inner cavity of the sliding rod (102).
10. A method of fastening an aircraft engine turbine disk blade fastening mechanism according to claim 1, characterised in that:
firstly, placing the tenon part of the turbine disc blade between a third clamping plate (35) and a limiting seat (36), and adjusting the angle between the third clamping plate (35) and the third clamping plate (35) to enable the third clamping plate (35) to be tightly attached to the outer wall of the tenon part of the turbine disc blade;
secondly, adjusting the position of a first sliding block (104) according to the length of the turbine disc blade, and further adjusting a first bearing plate (21) to a height close to the tip part of the turbine disc blade;
and thirdly, after the height adjustment is finished, the blade tip part of the turbine disc blade is placed between the two first bearing plates (21), the two first bearing plates (21) are deflected and adjusted at the same time, and the limiting convex block (29) and the limiting concave block (210) are attached to the outer wall of the blade tip, so that the turbine disc blade can be fastened and installed for subsequent processing and use.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210461064.6A CN114770163B (en) | 2022-04-24 | 2022-04-24 | Turbine disc blade fastening mechanism and method for aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210461064.6A CN114770163B (en) | 2022-04-24 | 2022-04-24 | Turbine disc blade fastening mechanism and method for aero-engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114770163A true CN114770163A (en) | 2022-07-22 |
| CN114770163B CN114770163B (en) | 2024-06-14 |
Family
ID=82434467
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210461064.6A Active CN114770163B (en) | 2022-04-24 | 2022-04-24 | Turbine disc blade fastening mechanism and method for aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114770163B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115184002A (en) * | 2022-08-25 | 2022-10-14 | 芜湖中科飞机制造有限公司 | Clamping device for detecting turbine blade of aero-engine |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040171330A1 (en) * | 2003-02-28 | 2004-09-02 | Whitmarsh Robert Duane | Apparatus and method for consistently retaining a gas turbine engine blade in a predetermined position and orientation |
| CN106514356A (en) * | 2016-12-28 | 2017-03-22 | 无锡透平叶片有限公司 | Universal clamp device for total-length finish milling of turbine blades |
| CN206263806U (en) * | 2016-10-11 | 2017-06-20 | 中国航空工业集团公司北京航空精密机械研究所 | A kind of aero engine turbine blades clean positioning fixture |
| CN112223323A (en) * | 2020-09-27 | 2021-01-15 | 烟台知兴知识产权咨询服务有限公司 | Mechanical grabbing device for underwater robot |
| CN112247618A (en) * | 2020-09-30 | 2021-01-22 | 西安三航动力科技有限公司 | Special fixture and method for machining end face of tenon root of blade of aero-engine |
| CN212526205U (en) * | 2020-07-10 | 2021-02-12 | 江阴市瑞恩工程设备有限公司 | Gantry milling machine with fixing device |
| CN112846306A (en) * | 2020-12-26 | 2021-05-28 | 尹冬岩 | Drilling equipment for machining and using method thereof |
| CN214080378U (en) * | 2020-12-30 | 2021-08-31 | 无锡海法工业测控设备有限公司 | Fixing clamp for machining plate-shaped workpiece |
| CN214230745U (en) * | 2021-01-05 | 2021-09-21 | 邓媛 | Multifunctional mural storage rack for rehabilitation nursing |
| CN113478262A (en) * | 2021-07-20 | 2021-10-08 | 中国航发航空科技股份有限公司 | Turbine blade sealing tooth machining clamp and clamping method thereof |
| CN214734227U (en) * | 2020-12-10 | 2021-11-16 | 海南热带海洋学院 | Commodity circulation fork truck is with preventing goods device of empting |
| CN215659206U (en) * | 2021-01-19 | 2022-01-28 | 无锡市古律特精工机械有限公司 | Automatic loading and unloading device for crankshaft |
-
2022
- 2022-04-24 CN CN202210461064.6A patent/CN114770163B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040171330A1 (en) * | 2003-02-28 | 2004-09-02 | Whitmarsh Robert Duane | Apparatus and method for consistently retaining a gas turbine engine blade in a predetermined position and orientation |
| CN206263806U (en) * | 2016-10-11 | 2017-06-20 | 中国航空工业集团公司北京航空精密机械研究所 | A kind of aero engine turbine blades clean positioning fixture |
| CN106514356A (en) * | 2016-12-28 | 2017-03-22 | 无锡透平叶片有限公司 | Universal clamp device for total-length finish milling of turbine blades |
| CN212526205U (en) * | 2020-07-10 | 2021-02-12 | 江阴市瑞恩工程设备有限公司 | Gantry milling machine with fixing device |
| CN112223323A (en) * | 2020-09-27 | 2021-01-15 | 烟台知兴知识产权咨询服务有限公司 | Mechanical grabbing device for underwater robot |
| CN112247618A (en) * | 2020-09-30 | 2021-01-22 | 西安三航动力科技有限公司 | Special fixture and method for machining end face of tenon root of blade of aero-engine |
| CN214734227U (en) * | 2020-12-10 | 2021-11-16 | 海南热带海洋学院 | Commodity circulation fork truck is with preventing goods device of empting |
| CN112846306A (en) * | 2020-12-26 | 2021-05-28 | 尹冬岩 | Drilling equipment for machining and using method thereof |
| CN214080378U (en) * | 2020-12-30 | 2021-08-31 | 无锡海法工业测控设备有限公司 | Fixing clamp for machining plate-shaped workpiece |
| CN214230745U (en) * | 2021-01-05 | 2021-09-21 | 邓媛 | Multifunctional mural storage rack for rehabilitation nursing |
| CN215659206U (en) * | 2021-01-19 | 2022-01-28 | 无锡市古律特精工机械有限公司 | Automatic loading and unloading device for crankshaft |
| CN113478262A (en) * | 2021-07-20 | 2021-10-08 | 中国航发航空科技股份有限公司 | Turbine blade sealing tooth machining clamp and clamping method thereof |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115184002A (en) * | 2022-08-25 | 2022-10-14 | 芜湖中科飞机制造有限公司 | Clamping device for detecting turbine blade of aero-engine |
| CN115184002B (en) * | 2022-08-25 | 2023-09-05 | 芜湖中科飞机制造有限公司 | Clamping device for detecting turbine blade of aero-engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114770163B (en) | 2024-06-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114770163A (en) | Fastening mechanism and method for turbine disc blade of aircraft engine | |
| CN107685232B (en) | Automatic lock cylinder assembling device for double-blade lock | |
| CN114152398B (en) | Device and method for measuring natural frequency of aircraft engine blade | |
| CN107226217B (en) | A kind of conformal positioning device of wing wallboard | |
| CN116689873B (en) | Contour cutting processing equipment for photovoltaic support section bar | |
| US20050229767A1 (en) | Sheet-cutting apparatus | |
| CN110732873B (en) | Lantern automation line | |
| CN108237494B (en) | Wing root rib positioning device | |
| CN115283898B (en) | Mechanical equipment's maintenance welding set | |
| CN212373023U (en) | Book block casing device for casing machine | |
| CN109592914B (en) | Manufacturing device and manufacturing method of vacuum glass | |
| CN112517705B (en) | Clamp and processing equipment | |
| CN109066488B (en) | High-voltage cable peeling treatment device | |
| CN216990844U (en) | A air jig for space flight work piece processing | |
| CN218806620U (en) | A stringer frock for aircraft manufacturing | |
| CN214643972U (en) | Device is cut to leaded light post multi-angle | |
| CN110814212A (en) | Automatic integrative anchor clamps of foot are cut to curved foot | |
| EP2076341B1 (en) | Apparatus for and method of forming curved panels | |
| CN214644107U (en) | Cylindrical lens cuts with carrying clamping device | |
| CN216266891U (en) | Many knives of roof prism cut forming device | |
| CN219924169U (en) | Building material metal tube shaping mechanism | |
| CN215036706U (en) | Clamp inclined top | |
| CN112743364B (en) | Clamp for machining steam turbine blade steam passage profile | |
| CN115533501B (en) | Automatic pressing device for end cover of starting disc | |
| CN115990768A (en) | Aviation blade processing device with floating support |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant |