CN111604734A - Aeroengine compressor rotor grinding apex location aligning device - Google Patents
Aeroengine compressor rotor grinding apex location aligning device Download PDFInfo
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- CN111604734A CN111604734A CN202010359949.6A CN202010359949A CN111604734A CN 111604734 A CN111604734 A CN 111604734A CN 202010359949 A CN202010359949 A CN 202010359949A CN 111604734 A CN111604734 A CN 111604734A
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- compressor rotor
- engine compressor
- hole
- cylindrical surface
- fixture body
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B5/00—Machines or devices designed for grinding surfaces of revolution on work, including those which also grind adjacent plane surfaces; Accessories therefor
- B24B5/36—Single-purpose machines or devices
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B41/00—Component parts such as frames, beds, carriages, headstocks
- B24B41/06—Work supports, e.g. adjustable steadies
- B24B41/061—Work supports, e.g. adjustable steadies axially supporting turning workpieces, e.g. magnetically, pneumatically
- B24B41/062—Work supports, e.g. adjustable steadies axially supporting turning workpieces, e.g. magnetically, pneumatically between centres; Dogs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B55/00—Safety devices for grinding or polishing machines; Accessories fitted to grinding or polishing machines for keeping tools or parts of the machine in good working condition
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Abstract
The invention discloses a positioning and aligning device for a grinding blade tip of a rotor of an aircraft engine compressor, which comprises: the front end fixture comprises a columnar front end fixture body, one end of the front end fixture body is provided with a threaded hole matched with the external thread of the engine compressor rotor, the other end of the front end fixture body is provided with a first center hole, and the cylindrical surface of the front end fixture body is uniformly provided with a plurality of first fine adjustment devices along the circumferential direction; the rear end fixture comprises a columnar rear end fixture body, one end of the rear end fixture body is provided with a bushing mounting hole, and a slotted bushing in clearance fit with the outer peripheral wall of the spline end of the engine compressor rotor is arranged in the bushing mounting hole; the other end is provided with a second center hole, and the cylindrical surface of the rear end clamp body is uniformly provided with a plurality of second fine adjustment devices along the circumferential direction. The invention can eliminate the unbalance loading influence and the machining error of the outer diameter of the spline shaft caused by the gravity of the rotor in the clamping process, and ensure the grinding accuracy of the rotor.
Description
Technical Field
The invention relates to a positioning and aligning device, in particular to a positioning and aligning device for a grinding blade tip of a rotor of an aircraft engine compressor.
Background
The function of a certain turboprop type aircraft engine air compressor is to utilize the output work of a turbine to suck and compress outside air, improve the air pressure and temperature and form continuous high-pressure flowing air from front to back. In order to obtain higher compressor efficiency, the radial clearance between the working blade and the working ring is required to be as small as possible, which puts higher requirements on the excircle size of the rotor tip of the compressor.
The weight of a certain turboprop type aircraft engine compressor rotor exceeds 100Kg, and the certain turboprop type aircraft engine compressor rotor consists of ten-stage blades, and as splines, central threaded holes or unthreaded holes are arranged at one end of shafts at two ends of the rotor, external threads are arranged at the other end of the shaft, and both ends of the shaft are not provided with tip holes. In order to grind the rotor blade tip on a precise excircle machine tool, a set of clamp with a tip hole is designed for the rotor blade tip, and the tip pushes the clamp to grind on the machine tool. However, the eccentric load influence is generated by the gravity of the compressor rotor in the clamping process, so that the axis of the rotor deviates from the rotation axis of a machine tool, and the accuracy of the size of the outer circle of the ground rotor is influenced.
Disclosure of Invention
The invention provides a positioning and aligning device for a grinding blade tip of an aircraft engine compressor rotor, which aims to solve the technical problem that the outer circle size of the compressor rotor after grinding is not up to standard due to the unbalance loading influence of the gravity of the compressor rotor in the clamping process.
The technical scheme adopted by the invention is as follows:
the utility model provides an aeroengine compressor rotor grinding apex location aligning device, includes:
the front end fixture comprises a columnar front end fixture body, one end of the front end fixture body is provided with a threaded hole coaxial with the axis of the front end fixture body, the threaded hole is matched with the external thread of the engine compressor rotor according to corresponding tightness, the other end of the front end fixture body is provided with a first tip hole coaxial with the axis of the front end fixture body, and the cylindrical surface of the front end fixture body is uniformly provided with a plurality of first fine adjustment devices for adjusting the position of the axis of the engine compressor rotor along the circumferential direction;
the rear end fixture comprises a columnar rear end fixture body, one end of the rear end fixture body is provided with a bushing mounting hole coaxial with the axis of the rear end fixture body, and a slotted bushing in clearance fit with the outer peripheral wall of the splined end of the rotor of the engine compressor is arranged in the bushing mounting hole; the other end of the rear end clamp body is provided with a second center hole coaxial with the axis of the rear end clamp body, and the cylindrical surface of the rear end clamp body is uniformly provided with a plurality of second fine adjustment devices used for adjusting the position of the axis of the rotor of the engine compressor along the circumferential direction.
Further, the major diameter of the threaded hole is larger than or equal to the upper limit value of the major diameter of the external thread of the engine compressor rotor, the sizes of the middle diameters of the threaded holes are divided into two groups, when the measured major diameter of the external thread of the engine compressor rotor is larger than or equal to a preset value, the middle diameter of the threaded hole is selected to be larger, otherwise, the middle diameter of the threaded hole is selected to be smaller; the preset value is the middle value of the major diameter of the external thread of the engine compressor rotor within the tolerance range of the major diameter.
Further, the minor group of dimensions is a middle value of the pitch diameter of the external thread of the engine compressor rotor within the tolerance range; the larger group size is the sum of the upper limit value of the pitch diameter of the external thread of the engine compressor rotor within the tolerance range and 0.02-0.08 mm.
Further, the pitch of screw hole is unanimous with the external screw thread pitch and the profile of tooth of engine compressor rotor, and slot between the adjacent profile of tooth includes the isosceles trapezoid slot, establishes the isosceles triangle slot on isosceles trapezoid slot top, the contained angle c on two inclined planes of isosceles trapezoid slot with the external screw thread profile of engine compressor rotor angle is unanimous, two inclined plane contained angles of isosceles triangle slot are less than the contained angle on two inclined planes of isosceles trapezoid slot, the maximum distance of isosceles trapezoid slot and isosceles triangle slot junction and screw thread slot line of symmetry is one tenth of pitch.
Furthermore, a notch and a plurality of grooves which are parallel to the axis of the slotted bush are uniformly arranged on the cylindrical surface of the slotted bush along the circumferential direction, the width of each groove is consistent with that of the notch, and the depth of each groove is smaller than the wall thickness of the slotted bush.
Further, the width of the notch is 2-3 mm, and the gap between the inner hole of the slotted bushing and the outer peripheral wall of the spline end of the engine compressor rotor is 0.18-0.35 mm; and the clearance between the outer diameter of the slotted bushing and the bushing mounting hole is 0.5-1.0 mm.
Furthermore, the first fine-tuning device comprises first adjusting screws, a plurality of first adjusting screw holes which radially penetrate through the threaded holes are distributed on the cylindrical surface of the front-end clamp body along the circumferential direction, and the first adjusting screws are screwed into the first adjusting screw holes; the second fine adjustment device comprises a second adjustment screw, a plurality of second adjustment screw holes which radially penetrate through the bushing mounting hole are distributed in the circumferential direction on the cylindrical surface of the rear-end clamp body, and the second adjustment screw is screwed into the second adjustment screw holes.
Furthermore, the front ends of the first adjusting screw and the second adjusting screw are respectively and fixedly provided with an external thread with hardness lower than that of the engine compressor rotor and a propping part of the slotted bushing.
Further, a columnar boss is arranged in the middle of the bushing mounting hole in a protruding mode, when the spline end of the engine compressor rotor is provided with a central unthreaded hole, the cylindrical surface of the columnar boss is in clearance fit with the central unthreaded hole, or when the spline end of the engine compressor rotor is provided with a central threaded hole, the cylindrical surface of the columnar boss is provided with an external thread matched with the central threaded hole.
Furthermore, a plurality of first transmission rod mounting holes are uniformly formed in the cylindrical surface of the front-end clamp body along the circumferential direction;
and a plurality of second dowel bar mounting holes are uniformly formed in the cylindrical surface of the rear-end clamp body along the circumferential direction.
The invention has the following beneficial effects:
the positioning and aligning device comprises a front end clamp and a rear end clamp, wherein the front end clamp is in threaded connection with a rotor threaded end and is in heavy-load fit with the rotor threaded end, a certain tightness can be controlled according to groups, and alignment and adjustment are carried out by utilizing a first fine adjustment device; the rear end fixture is connected with the spline end of the rotor through the slotted bushing, and the second fine adjustment device is used for alignment adjustment, so that the error caused by unbalance loading influence of the gravity of the rotor in the clamping process and the inconsistency of the machining outer diameter of the spline shaft is eliminated, and the grinding accuracy is ensured.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a front view of a front end fixture according to a preferred embodiment of the present invention; and
FIG. 2 is a schematic sectional view taken along line A-A in FIG. 1.
Fig. 3 is a schematic view of the internal thread profile of the preferred embodiment of the present invention.
Fig. 4 is a schematic view of an adjustment screw according to a preferred embodiment of the present invention.
Fig. 5 is a front view of a rear end clamp of the preferred embodiment of the present invention.
Fig. 6 is a schematic cross-sectional view of a rear end jig of a preferred embodiment of the present invention.
Fig. 7 is a front schematic view of a slotted bushing according to a preferred embodiment of the present invention.
Fig. 8 is a schematic sectional view taken along line B-B in fig. 7.
In the figure: 1. a front end clamp body; 2. a first central aperture; 3. a first adjusting screw; 4. a threaded hole; 5. a first adjusting screw hole; 6. a first apex aperture; 7. a first transfer lever mounting hole; 8. a butting part; 9. a thread groove symmetry line; 10. an isosceles trapezoid groove; 11. an isosceles triangular groove; 12. a rear end clamp body; 13. a second central aperture; 14. a second adjusting screw; 15. a second dowel bar mounting hole; 16. a second apex aperture; 17. a second adjusting screw hole; 18. a bushing mounting hole; 19. a columnar boss; 20. slotting a bushing; 21. cutting; 22. and (4) a groove.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
Referring to fig. 1, 2, 5 and 6, a preferred embodiment of the present invention provides an aeroengine compressor rotor grinding tip positioning and aligning device, including:
the front end fixture comprises a columnar front end fixture body 1 provided with a first center hole 2, one end of the front end fixture body 1 is provided with a threaded hole 4 coaxial with the axis of the front end fixture body 1, the threaded hole 4 is matched with the external thread of an engine compressor rotor according to corresponding tightness, the other end of the front end fixture body is provided with a first tip hole 6 coaxial with the axis of the front end fixture body 1, and the cylindrical surface of the front end fixture body 1 is uniformly provided with a plurality of first fine adjustment devices for adjusting the axis position of the engine compressor rotor along the circumferential direction;
the rear end clamp comprises a columnar rear end clamp body 12 provided with a second central hole 13, a bushing mounting hole 18 coaxial with the axis of the rear end clamp body 12 is formed in one end of the rear end clamp body 12, and a slotted bushing 20 in clearance fit with the outer peripheral wall of the splined end of the engine compressor rotor is arranged in the bushing mounting hole 18; the other end of the rear end clamp body 12 is provided with a second center hole 16 which is coaxial with the axis of the rear end clamp body 12, and the cylindrical surface of the rear end clamp body 12 is uniformly provided with a plurality of second fine adjustment devices for adjusting the position of the axis of the compressor rotor of the engine along the circumferential direction.
In the embodiment, the front end of the engine compressor rotor is provided with an external thread, the connection mode of the engine compressor rotor and the front end clamp body 1 is thread fit (M80 multiplied by 1.5), wherein the tolerance of the middle diameter d2 of the external thread of the engine compressor rotor is (-0.21, 0), the major diameter d is phi 80(-0.24, 0), the thread pitch is 1.5mm, therefore, the upper limit value of the major diameter d of the external thread of the engine compressor rotor is phi 80mm, the lower limit value is phi 79.76mm, the clamping, the adjustment and the alignment of the engine compressor rotor are realized by the matching of the front end clamp and the rear end clamp, wherein, the front end clamp is matched with the external thread of the engine compressor rotor according to corresponding tightness through a threaded hole 4, the adjustment and the alignment are carried out by utilizing a first fine adjustment device, a slotted bush 20 is arranged between the rear end clamp and the spline end of the engine compressor rotor, the slotting bush 20 can eliminate the difficulty in installation caused by machining errors of the outer diameter of the spline shaft of the part, can also adjust and align the rotor of the engine gas compressor through a second fine adjustment device before grinding, eliminates unbalance loading generated by gravity in the process of clamping the rotor of the engine gas compressor, ensures the coaxiality of the axis of the rotor of the engine gas compressor and the main shaft of the machine tool, and improves the machining quality of the rotor of the engine gas compressor.
Specifically, in a preferred embodiment of the present invention, the major diameter D of the threaded hole 4 is greater than or equal to the upper limit value phi 80mm of the major diameter D of the external thread of the engine compressor rotor, the size of the pitch diameter D2 of the threaded hole 4 is divided into two groups, which can be selected according to the size of the major diameter D of the external thread of the engine compressor rotor: when the size of the major diameter D of the external thread of the compressor rotor of the engine to be measured is larger than or equal to a preset value, the major diameter D2 of the threaded hole 4 is selected to be larger in group size, otherwise, the minor group size is selected; wherein the preset value is a middle value of the major diameter D of the external thread of the engine compressor rotor within the tolerance range, namely the preset value is phi 79.88mm, therefore, when the measured major diameter D of the external thread of the engine compressor rotor is more than or equal to phi 79.88mm, the major diameter D2 of the threaded hole 4 is selected to be a larger group size, otherwise, the minor group size is selected, so that the major diameter D2 of the selected threaded hole 4 can be determined according to the actually measured major diameter D of the external thread of the engine compressor rotor, the proper fit tightness between the external thread of the engine compressor rotor and the threaded hole 4 is ensured, if the fit tightness is not enough, the fit clearance between the external thread of the engine compressor rotor and the threaded hole 4 is too large, the accuracy and the stability of the position of the engine compressor rotor during subsequent adjustment and grinding processing are difficult to ensure, and the processing quality of the engine compressor rotor is influenced, of course, too high tightness also affects the clamping efficiency and the adjustment margin, and even damages the external thread of the engine compressor rotor.
Specifically, in a preferred embodiment of the invention, the minor dimension is specifically the median value of the external thread pitch diameter d2 of the engine compressor rotor within the tolerance range thereof; in the embodiment, by referring to a relevant thread standard manual, the middle value of the external thread middle diameter D2 of the engine compressor rotor in the tolerance range is phi 78.916mm, namely the smaller group size is phi 78.916mm, when the large diameter D of the external thread of the engine compressor rotor is less than phi 79.88mm, the middle diameter D2 of the threaded hole 4 is phi 78.916mm, and the upper value of the external thread middle diameter D2 of the engine compressor rotor in the tolerance range is phi 79.026mm, plus 0.02-0.08 mm, wherein in the embodiment, 0.05mm is selected plus, the larger group size is phi 79.076mm, namely when the large diameter D of the external thread of the engine compressor rotor is greater than or equal to phi 79.88mm, the middle diameter D2 of the threaded hole 4 is phi 79.076 mm. Practical operation shows that the selection process of the pitch diameter D2 of the threaded hole 4 can ensure that the external thread of the compressor rotor of the engine and the threaded hole 4 always have proper fit tightness, and meanwhile, the grouped calculation results ensure the standardized unification of the grouped sizes of the pitch diameters D2 of the threaded holes 4 on the basis of the standard data of relevant thread standard manuals.
Specifically, as shown in fig. 3, in a preferred embodiment of the present invention, a pitch e of the threaded hole 4 is consistent with a thread pitch and a thread form of an engine compressor rotor, grooves between adjacent thread forms include an isosceles trapezoid groove 10 and an isosceles triangle groove 11 disposed at a top end of the isosceles trapezoid groove 10, an included angle c between two inclined planes of the isosceles trapezoid groove 10 is consistent with an angle of the thread form of the engine compressor rotor, an included angle b between two inclined planes of the isosceles triangle groove 11 is smaller than an included angle c between two inclined planes of the isosceles trapezoid groove 10, and a maximum distance a between a connection of the isosceles trapezoid groove 10 and the isosceles triangle groove 11 and a thread groove symmetry line 9 is one tenth of the pitch e.
In this embodiment, the grooves between adjacent tooth forms of the threaded hole 4 include an isosceles trapezoid groove 10, and an isosceles triangle groove 11 disposed at the top end of the isosceles trapezoid groove 10, and the included angle b of the two inclined planes of the isosceles triangle groove 11 is smaller than the included angle c of the two inclined planes of the isosceles trapezoid groove 10, meanwhile, the maximum distance a between the connection part of the isosceles trapezoid groove 10 and the isosceles triangle groove 11 and the thread groove symmetry line 9 is one tenth of the thread pitch e, because the external thread profile of the engine compressor rotor is a triangle of 60 degrees, after the assembly is ensured, the tooth-shaped tip of the external thread of the engine compressor rotor is positioned in the isosceles triangle groove 11, and the tooth-shaped tip end can not be contacted with two inclined planes and vertex angles of the isosceles triangle groove 11, so that the tooth-shaped tip end is prevented from being damaged, and the external thread of the engine compressor rotor is protected.
Specifically, as shown in fig. 7, in a preferred embodiment of the present invention, the cylindrical surface of the slotted liner 20 is uniformly provided with a notch 21 and a plurality of grooves 22 along the circumferential direction, the notch 21 and the grooves 22 are parallel to the axis of the slotted liner 20, the width k of the grooves 22 is consistent with the width i of the notch 21, such as 3mm, and the depth j is smaller than the wall thickness of the slotted liner 20, such as 2 mm.
In this embodiment, the notch 21 is provided to ensure that the slotted bush 20 has a certain elastic change, so as to accurately clamp the spline end of the engine compressor rotor during the clamping and adjusting processes, and meanwhile, by providing the plurality of uniformly distributed grooves 22, the overall elasticity and deformation uniformity of the slotted bush 20 can be improved, the rigidity of the slotted bush 20 during contraction is reduced, so that the force application is more uniform when the slotted bush 20 clamps the outer peripheral wall of the spline end of the engine compressor rotor, thereby ensuring that the slotted bush 20 clamps the spline end of the engine compressor rotor more firmly and reliably, and avoiding the problem of stress concentration.
Specifically, in a preferred embodiment of the present invention, the width of the notch 21 is 3mm, and the gap between the inner hole of the slotted bushing 20 and the outer peripheral wall of the splined end of the engine compressor rotor is 0.18mm to 0.35 mm; the clearance between the outer diameter h of the slotted bushing 20 and the bushing mounting hole 18 is 0.5-1.0 mm.
As shown in fig. 8, in this embodiment, the rear end of the engine compressor rotor is a spline end, the outer diameter of the spline end is phi 72.5mm (-0.3.-0.18), the bush mounting hole 18 of the rear clamp body 12 is nested with the slotted bush 20, the inner diameter g of the slotted bush 20 is phi 72.5mm (0, +0.05), and the slotted bush is in small-gap fit with the outer diameter of the spline shaft, so that the small-gap fit can not only eliminate the installation difficulty caused by the dimension error of the machined outer diameter of the spline end, but also ensure the subsequent positioning accuracy, stability and reliability of the axis of the spline end of the engine compressor rotor; and the outer diameter h of the slotted bush 20 is phi 80mm and the slotted bush 20 is in large clearance fit with the bush mounting hole 18, so that the slotted bush 20 can be easily mounted in the bush mounting hole 18 of the rear-end clamp body 12, and the clamping efficiency is improved.
Specifically, in a preferred embodiment of the present invention, the first fine-tuning device includes first adjusting screws 3, four first adjusting screw holes 5 radially penetrating through the threaded holes 4 are circumferentially distributed on the cylindrical surface of the front end fixture body 1, an included angle between adjacent first adjusting screw holes 5 is ninety degrees, and the first adjusting screws 3 are screwed into the first adjusting screw holes 5; the second fine-adjustment device comprises a second adjusting screw 14, four second adjusting screw holes 17 radially penetrating through the bushing mounting hole 18 are circumferentially distributed in the cylindrical surface of the rear-end clamp body 12, an included angle between every two adjacent second adjusting screw holes 17 is ninety degrees, and the second adjusting screw 14 is screwed into the second adjusting screw holes 17.
In this embodiment, the first fine adjustment device and the second fine adjustment device respectively include four first adjustment screws 3 and four second adjustment screws 14 uniformly distributed along the circumferential direction, the cylindrical surface of the front end fixture body 1 is circumferentially distributed with a plurality of first adjustment screw holes 5 radially penetrating the threaded holes 4, the cylindrical surface of the rear end fixture body 12 is circumferentially distributed with four second adjustment screw holes 17 radially penetrating the bushing mounting holes 18, the screwing position of each first adjustment screw 3 is adjusted, the axial position of the external thread end of the engine compressor rotor is adjusted by the abutting action of each first adjustment screw 3 on the external thread of the engine compressor rotor, similarly, the screwing position of each second adjustment screw 14 is adjusted, the slotted bushing 20 is abutted by each second adjustment screw 14, the axial position adjustment of the spline end of the engine compressor rotor is indirectly realized, so that the unbalance loading generated by gravity in the process of clamping the engine compressor rotor is eliminated, the coaxiality of the axial line of the engine compressor rotor and the main shaft of a machine tool is ensured, and the processing quality of the engine compressor rotor is improved.
Specifically, as shown in fig. 4, in a preferred embodiment of the present invention, the front ends of the first adjusting screw 3 and the second adjusting screw 14 are respectively and fixedly provided with a butting portion 8 having a hardness lower than that of the external thread of the engine compressor rotor and the slotted bush 20, the butting portion 8 of the present embodiment is obtained by welding copper on the front end of the second adjusting screw 14, the thickness of the copper is 2mm, and since the hardness of the copper is lower than that of the external thread of the engine compressor rotor and the slotted bush 20, the external thread of the component and the slotted bush 20 are effectively prevented from being damaged in the adjusting process.
Specifically, in a preferred embodiment of the present invention, a cylindrical boss 19 is further convexly disposed in the middle of the bushing mounting hole 18, the cylindrical boss 19 is coaxial with the bushing mounting hole 18, when the spline end of the engine compressor rotor is provided with a central unthreaded hole, a cylindrical surface of the cylindrical boss 19 is in clearance fit with the central unthreaded hole, and when the spline end of the engine compressor rotor is provided with a central threaded hole, a cylindrical surface of the cylindrical boss 19 is provided with an external thread which is matched with the central threaded hole.
In the embodiment, by arranging the columnar boss 19, the cylindrical surface of the columnar boss 19 can be set to be a smooth surface or an external thread matched with the cylindrical surface according to the structural characteristics of the central hole of the splined end of the rotor of the engine compressor, so that the cylindrical surface plays a role in assisting positioning and supporting the splined end of the rotor of the engine compressor in the clamping process, the pressure of the splined end of the rotor of the engine compressor on the inner wall of the slotted liner 20 is reduced, and the assembling speed between the splined end of the rotor of the engine compressor and the inner hole of the slotted liner 20 is increased.
Specifically, in a preferred embodiment of the present invention, a cylindrical surface of the front end fixture body 1 is uniformly provided with a plurality of first transmission rod mounting holes 7 along a circumferential direction; the cylindrical surface of the rear end clamp body 12 is uniformly provided with a plurality of second dowel bar mounting holes 15 along the circumferential direction. Because the front end clamp body 1 and the rear end clamp body 12 are in driving connection with the machine tool spindle through the friction force of the center, in order to prevent the center from slipping between the front end clamp body 1 and the rear end clamp body 12, a first dowel bar mounting hole 7 and a second dowel bar mounting hole 15 are respectively arranged on the front end clamp body 1 and the rear end clamp body 12, dowel bars can be respectively arranged on the first dowel bar mounting hole 7 and the second dowel bar mounting hole 15, the power of the machine tool spindle is transmitted to the front end clamp body 1 and the rear end clamp body 12, and the synchronous rotation of the engine compressor rotor and the machine tool spindle is ensured.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The utility model provides an aeroengine compressor rotor grinding apex location aligning device which characterized in that includes:
the front end fixture comprises a columnar front end fixture body (1), one end of the front end fixture body (1) is provided with a threaded hole (4) coaxial with the axis of the front end fixture body (1), the threaded hole (4) is matched with the external thread of an engine compressor rotor according to corresponding tightness, the other end of the front end fixture body is provided with a first tip hole (6) coaxial with the axis of the front end fixture body (1), and the cylindrical surface of the front end fixture body (1) is uniformly provided with a plurality of first fine-adjustment devices for adjusting the position of the axis of the engine compressor rotor along the circumferential direction;
the rear end fixture comprises a columnar rear end fixture body (12), one end of the rear end fixture body (12) is provided with a bushing mounting hole (18) coaxial with the axis of the rear end fixture body (12), and a slotted bushing (20) in clearance fit with the outer peripheral wall of the splined end of the engine compressor rotor is arranged in the bushing mounting hole (18); the other end of the rear end clamp body is provided with a second center hole (16) which is coaxial with the axis of the rear end clamp body (12), and the cylindrical surface of the rear end clamp body (12) is uniformly provided with a plurality of second fine adjustment devices for adjusting the position of the axis of the rotor of the compressor of the engine along the circumferential direction.
2. The aeroengine compressor rotor grinding blade tip positioning and aligning device of claim 1,
the major diameter of the threaded hole (4) is larger than or equal to the upper limit value of the major diameter of the external thread of the engine compressor rotor, the sizes of the middle diameters of the threaded holes (4) are divided into two groups, when the measured major diameter of the external thread of the engine compressor rotor is larger than or equal to a preset value, the middle diameter of the threaded hole (4) is selected to be larger in group size, otherwise, the middle diameter of the external thread of the engine compressor rotor is selected to be smaller in group size; the preset value is the middle value of the major diameter of the external thread of the engine compressor rotor within the tolerance range of the major diameter.
3. The aero-engine compressor rotor grinding tip positioning and aligning device as claimed in claim 2, wherein the minor group of dimensions is a median value of the pitch diameter of the external threads of the engine compressor rotor within a tolerance range thereof; the larger group size is the sum of the upper limit value of the pitch diameter of the external thread of the engine compressor rotor within the tolerance range and 0.02-0.08 mm.
4. The aeroengine compressor rotor grinding apex location aligning device of claim 2, characterized in that, the pitch of screw hole (4) is unanimous with the external screw thread pitch and the profile of tooth of engine compressor rotor, and the slot between the adjacent profile of tooth includes isosceles trapezoid slot (10), establishes isosceles triangle slot (11) on isosceles trapezoid slot (10) top, the contained angle on two inclined planes of isosceles trapezoid slot (10) with the external screw thread profile of engine compressor rotor is unanimous, the two inclined plane contained angles of isosceles triangle slot (11) are less than the contained angle on two inclined planes of isosceles trapezoid slot (10), the maximum distance of isosceles trapezoid slot (10) and isosceles triangle slot (11) junction and screw thread slot symmetry line (9) is one tenth of pitch.
5. The aeroengine compressor rotor grinding blade tip positioning and aligning device of claim 1,
the cylindrical surface of the slotted bushing (20) is uniformly provided with a notch (21) and a plurality of grooves (22) parallel to the axis of the slotted bushing (20) along the circumferential direction, the width of each groove (22) is consistent with the width of the notch (21), and the depth of each groove is smaller than the wall thickness of the slotted bushing (20).
6. The aeroengine compressor rotor grinding blade tip positioning and aligning device of claim 5,
the width of the notch (21) is 2-3 mm, and the gap between the inner hole of the slotting lining (20) and the outer peripheral wall of the spline end of the engine compressor rotor is 0.18-0.35 mm; the clearance between the outer diameter of the slotted bushing (20) and the bushing mounting hole (18) is 0.5-1.0 mm.
7. The aeroengine compressor rotor grinding blade tip positioning and aligning device according to claim 1, characterized in that the first fine adjustment device comprises first adjustment screws (3), a plurality of first adjustment screw holes (5) radially penetrating through the threaded holes (4) are distributed on the cylindrical surface of the front end clamp body (1) along the circumferential direction, and the first adjustment screws (3) are screwed into the first adjustment screw holes (5); the second fine adjustment device comprises a second adjustment screw (14), a plurality of second adjustment screw holes (17) which radially penetrate through the bushing mounting hole (18) are circumferentially distributed in the cylindrical surface of the rear-end clamp body (12), and the second adjustment screw (14) is screwed into the second adjustment screw holes (17).
8. The aeroengine compressor rotor grinding blade tip positioning and aligning device according to claim 7, characterized in that the front ends of the first adjusting screw (3) and the second adjusting screw (14) are respectively fixedly provided with an abutting part (8) with hardness lower than that of the external thread of the engine compressor rotor and the slotted bushing (20).
9. The aero-engine compressor rotor grinding tip positioning and aligning device according to claim 1, wherein a cylindrical boss (19) protrudes from the middle of the bushing mounting hole (18), when a splined end of the engine compressor rotor is provided with a central unthreaded hole, a cylindrical surface of the cylindrical boss (19) is in clearance fit with the central unthreaded hole, or when the splined end of the engine compressor rotor is provided with a central threaded hole, the cylindrical surface of the cylindrical boss (19) is provided with an external thread matched with the central threaded hole.
10. The aeroengine compressor rotor grinding blade tip positioning and aligning device of claim 1,
a plurality of first transmission rod mounting holes (7) are uniformly formed in the cylindrical surface of the front end clamp body (1) along the circumferential direction;
and a plurality of second dowel bar mounting holes (15) are uniformly formed in the cylindrical surface of the rear-end clamp body (12) along the circumferential direction.
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| CN202010359949.6A CN111604734B (en) | 2020-04-30 | 2020-04-30 | Aeroengine compressor rotor grinding apex location aligning device |
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| CN202010359949.6A CN111604734B (en) | 2020-04-30 | 2020-04-30 | Aeroengine compressor rotor grinding apex location aligning device |
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| CN111604734B CN111604734B (en) | 2021-11-19 |
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| CN116050194A (en) * | 2023-04-03 | 2023-05-02 | 中国航发四川燃气涡轮研究院 | Method for determining radial matching tightness of bolt-free baffle of turbine rotor |
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| CN111604734B (en) | 2021-11-19 |
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