JP2020131331A - Blade gripping jig - Google Patents

Abstract

To provide a blade gripping jig capable of suppressing occurrence of chatter.SOLUTION: There is provided a blade gripping jig 1 for gripping a blade S when processing at least one of a front edge part and a rear edge part on a wing shape part Sof the blade S as a processed part M. The blade gripping jig 1 comprises a pair of gripping parts 2, 3 for gripping the wing shape part Sfrom both sides of a thickness direction thereof. The pair of gripping parts 2, 3 comprise respectively, a contact surface A, Acontacting a region Aexcept for the processed part Mon a surface of the wing shape part Swhen gripping the wing shape part S. When the contact surfaces A, Acontact the region A, end edges E, Eof the contact surfaces A, Aon the processed part Mside extend over a wing length direction length Lof the processed part Min the vicinity of the processed part M.SELECTED DRAWING: Figure 1

Description

The present disclosure relates to a blade gripping jig for gripping a blade when cutting, grinding, or the like on a blade-shaped portion of the blade.

Patent Document 1 discloses a support device for fixing a fan blade material which is a workpiece when processing a blade surface of a fan blade. In this support device, a support substrate is provided on the back surface of the work surface of the workpiece, and a plurality of workpiece support mechanisms are attached to the support substrate. The workpiece support mechanism includes a cylinder portion that expands and contracts by a spring force and automatically follows the shape of the workpiece, and a sleeve that hydraulically fixes the cylinder portion.

Japanese Unexamined Patent Publication No. 7-299628

However, since the support device supports the workpiece on the back surface of the work surface, the support rigidity may be insufficient when machining a portion away from the support point, and the workpiece may vibrate. there were.

An object of the present disclosure is to provide a blade gripping jig capable of suppressing the occurrence of chatter vibration.

One aspect of the present disclosure is a blade gripping jig that grips the blade when at least one of the front edge portion and the trailing edge portion of the airfoil portion of the blade is machined as a machined portion. The blade gripping jig includes a pair of holding portions that hold the airfoil portion from both sides in the thickness direction. Each of the pair of holding portions has a contact surface that comes into contact with a region of the surface of the airfoil portion excluding the processed portion when the airfoil portion is sandwiched. When the abutting surface comes into contact with the region, the edge of the abutting surface on the workpiece side extends in the vicinity of the workpiece over the length of the workpiece in the blade length direction.

The blade gripping jig may include a positioning portion that abuts on a portion other than the airfoil portion of the blade to position the position of the airfoil portion with respect to the contact surface. Further, each of the contact surfaces may have a surface shape that follows the surface shape of the region in which each contacts. Further, when the abutting surface abuts on the above region, the abutting surface has a blade-shaped portion between the edge on the side to be processed and the edge on the opposite side in the plan view of the abutting surface. Each may have a shape such that the maximum blade thickness line is located.

According to the blade gripping jig, the occurrence of chatter vibration can be suppressed.

It is an assembly perspective view of the blade gripping jig which concerns on 1st Embodiment. It is an assembly perspective view which saw the blade gripping jig which concerns on 1st Embodiment from the direction different from FIG. It is a top view of the stator blade. It is a perspective view which shows one of the pair of sandwiching portions which concerns on 1st Embodiment. It is a perspective view which shows the other of the pair of sandwiching portions which concerns on 1st Embodiment. FIG. 1 is a sectional view taken along line VI-VI of FIG. 1 for explaining how to use the blade gripping jig according to the first embodiment. FIG. 1A is a state in which a pair of holding portions are open, and FIG. 1B is a pair. Indicates a state in which the stator blade is sandwiched between the sandwiching portions of. It is an assembly perspective view of the blade gripping jig which concerns on 2nd Embodiment. It is a top view of a rotor blade. It is a perspective view which shows one of the pair of sandwiching portions which concerns on 2nd Embodiment. It is a perspective view which shows the other of the pair of sandwiching portions which concerns on 2nd Embodiment. It is a figure explaining the use method of the blade gripping jig which concerns on 2nd Embodiment, (a) is a state which a pair of holding parts are open, (b) is a pair of holding parts in the state of (a). The state where the rotor blade is mounted on one side is shown. 11 is a view following FIG. 11, where FIG. 11C shows a state in which the pair of holding portions are closed, and FIG. 11D shows a state in which the pair of holding portions are locked in a closed state by a holding device.

Hereinafter, the blade gripping jig according to some embodiments will be described with reference to the drawings. In each figure, elements having substantially the same function are designated by the same reference numerals, and duplicate description will be omitted.

<First Embodiment>
As shown in FIGS. 1 to 3, the blade gripping tool 1 according to the first embodiment, when processing a part or all of the leading edge S _1L in the airfoil S ₁ of the stator blade S, the stator This is a jig for gripping the blade S. The blade gripping jig 1 is used by being placed and fixed on the table of a multi-axis processing machine such as a 5-axis processing machine.

The stator blade S, which is a blade to be gripped, is a stationary blade for a high-pressure axial compressor such as an aircraft jet engine or an industrial gas turbine engine, and is also called a nozzle guide vane (NGV). .. Stator blades S are, for example, titanium alloys, cobalt-based alloys are made of heat-resistant alloy such as nickel-based alloy, as shown in FIG. 3, the airfoil S ₁ having an airfoil section (airfoil), spanwise It has both ends S ₂ and S ₃ . Both end portions S _2, S _3, when the stator blade S is attached to the compressor, the inner end S ₂ located radially inwardly of the compressor than the airfoil S _1, an outer end located outside consisting of part _{S 3} Metropolitan.

Both end portions S _2, S _3, for example, welded to the inner shroud and an outer shroud (not shown), respectively, brazing, it is fixed by diffusion bonding or the like. Engaging the inner end S _2, is inserted into the engaging hole provided in the inner shroud, the engagement portion S _2a to be fixed is formed on the outside end portion S _3, which is provided on the outer shroud is inserted into Goana engaging portion S _3a to be fixed is formed.

The airfoil portion S ₁ includes a front edge portion S _1L , a trailing edge portion S _1T, and a central portion S _1M located between them in the chord direction. The position of the maximum blade thickness of the airfoil portion S ₁ belongs to the central portion S _1M . Also, if the aerofoil of the airfoil S ₁ is has a camber, the position of the maximum camber belong to the central portion S _1M. The maximum blade thickness is not particularly limited, but is, for example, about 2 mm.

Surface or Tsubasamen of the airfoil S ₁ has a three-dimensional curved surface shape. In this embodiment, at least the surfaces of the central portion S _1M and the trailing edge portion S _1T have a final product shape or a shape close to the final product shape (near net shape). Therefore, the central portion S _1M and the trailing edge portion S _1T are excluded from the processing range.

Blade gripping tool 1, as shown in FIGS. 1 and 2, has a pair of clamping parts 2, 3 for clamping the airfoil S ₁ from the thickness direction both sides. The sandwiching portions 2 and 3 may be formed of a metal softer (lower hardness) than the stator blade S, which is a workpiece, such as brass or an aluminum alloy.

In the following description of the present embodiment, as shown in FIGS. 1 to 3, when the clamping portion 2 is sandwiched airfoils S _1, the work unit M _{1 (FIG} relative clamping unit 2,3 The side where the front edge portion _S1L including (see 3) is located is the front side, and the opposite side is the rear side. Further, substantially parallel to the spanwise airfoil S ₁ in a state of being clamped by the clamping unit 2, the direction orthogonal to the longitudinal direction X ₁ and the vertical direction Z _1. In the blade gripping jig 1, the side fixed to the table of the multi-axis machine is the lower side, and the opposite side is the upper side. Further, the direction orthogonal to the front-rear direction X ₁ and the vertical direction Z ₁ is defined as the left-right direction Y ₁ . It should be noted that these directions are defined for convenience to explain the relative positional relationship between each part / element in the present embodiment, and do not limit the actual mounting posture of the blade gripping jig 1. Absent. The front-back direction X ₁ , the left-right direction Y ₁ and the up-down direction Z ₁ are also simply referred to as the X ₁ direction, the Y ₁ direction, and the Z ₁ direction, respectively.

As shown in FIGS. 1 and 2, the blade gripping jig 1 may include a base portion 4 that supports the holding portions 2 and 3. A flange 4a is provided at the lower end of the base portion 4, and a plurality of holes 4b are provided in the flange 4a. Fasteners such as bolts (not shown) are inserted into each hole 4b. By fastening this fastener, the blade gripping jig 1 is positioned and fixed on the table of the multi-axis machine.

Of the holding portions 2 and 3, the right holding portion (hereinafter, right holding portion) 2 is integrally connected to the upper surface 4d of the base 4 at the lower end thereof, as shown in FIG. The left holding portion (hereinafter, left holding portion) 3 is a movable member that can be separated from the right holding portion 2 as shown in FIG. 5, and as shown in FIG. 1, for example, the right holding portion 2 is provided by the cam lever mechanism 5. It is movably connected to the Y ₁ direction relative.

As shown in FIG. 6, the cam lever mechanism 5 includes a shaft 6, a pin 7 screwed into a threaded portion 6b at the tip of the shaft 6, and a cam lever 8 rotatably connected to the shaft 6 via the pin 7. It is provided with a contact plate 9. Shaft 6 has a hole 2a penetrating the both of the two sandwiching portions 2 and 3 in the _{Y 1} direction, it is inserted in 3a, and the head 6a is engaged with the Hidarikyo lifting unit 3. Further, the contact plate 9 is arranged between the right side surface 2b of the right holding portion 2 and the cam lever 8 in a state where the shaft 6 is penetrated.

The cam lever 8 has a cam portion 8a through which a pin 7 is inserted and a lever portion 8b extending from the cam portion 8a. The cam portion 8a is provided with a cylindrical cam surface 8c on the outer periphery thereof. The central axis 8d of the cam surface 8c is eccentric with respect to the central axis 7a of the pin 7.

The cam lever 8 has an unclamping position (see FIG. 6A) in which the lever portion 8b extends substantially parallel to the shaft 6 and a clamp position extending substantially perpendicular to the shaft 6 (FIG. 6B). )), It is rotatable around the central axis 7a of the pin 7. Then, by rotating the cam lever 8 between the unclamp position and the clamp position, the distance between the contact P of the cam surface 8c with the contact plate 9 and the central axis 7a of the pin 7 can be increased or decreased. It is possible. When the cam lever 8 is in the unclamped position, the distance is small, and the left holding portion 3 is located in an open position (see FIG. 6A) separated from the right holding portion 2. When the cam lever 8 is in the clamp position, the distance is large, and the left holding portion 3 is located in a closed position (see FIG. 6B) where the stator blade S can be sandwiched between the cam lever 8 and the right holding portion 2. .. In the open position, a gap G having a size sufficient for setting the stator blade S or taking out the stator blade S from between them is formed between the holding portions 2 and 3.

When the cam lever 8 is rotated from the unclamped position to the clamped position, a leftward force F acts on the contact plate 9 from the cam surface 8c, and a rightward force F acts on the shaft 6 from the pin 7. Then, the leftward force F is transmitted to the left holding portion 3 via the head portion 6a of the shaft 6, and the rightward force F is transmitted to the right holding portion 2 via the contact plate 9, whereby the left and right forces F are transmitted to the right holding portion 2. The sandwiching portions 2 and 3 move in directions close to each other. After the contact surfaces A ₂ and A _{3 of} both holding portions 2 and 3 abut on the surface of the airfoil portion S ₁ , the force F is applied to the airfoil portion S ₁ via the contact surfaces A ₂ and A _3. acts airfoil S ₁ is held by the force F.

The sandwiching portions 2 and 3 may have a positioning pin 10 (see FIG. 1) and a positioning hole 11 (see FIG. 2) into which the positioning pin 10 is fitted. In the present embodiment, as shown in FIGS. 4 and 5, the positioning hole 11 is provided penetrating in the Y ₁ direction in the lower part of the Hidarikyoji portion 3, the left side surface 2c of the right gripping portion 2, positioning holes 11 and Y _The positioning pin 10 is provided so as to project at a position facing in _one direction. Since the positioning pin 10 maintains the state of being fitted into the positioning hole 11 even when the left holding portion 3 is in the open position, the left holding portion 3 rotates around the shaft 6 by its own weight. Can be prevented. This facilitates the setting or removal of the stator blade S.

The sandwiching portions 2 and 3 have contact surfaces A ₂ and A ₃ that come into contact with the surface of the airfoil portion S ₁ when the airfoil portion S ₁ is sandwiched. As shown in FIG. 4, the right holding portion 2 has an abutting surface A ₂ on the left side surface 2c thereof, and the left holding portion 3 has an abutting surface A ₃ on the right side surface 3c as shown in FIG. Has. The contact surfaces A ₂ and A ₃ are regions on the surface of the airfoil portion S ₁ excluding the workpiece M ₁ , for example, in the present embodiment, the central portion S _{1 M} and the trailing edge portion as shown in FIG. It abuts on the surface of S _1T . Abutment surface A _2, A _3, the surface shape of each following the surface shape of the region A _S abutting the airfoil S ₁ of the surface, i.e. each was transferred to the surface shape of the abutting area A _S shape Each has. Grooves, irregularities, etc. may be formed on the surfaces of the contact surfaces A ₂ and A ₃ in order to make the contact surface pressure more appropriate.

When the abutment surface _A 2, _{A 3} is in contact with the area _{A S,} the edge _E 2, _{E 3} of the machined portion _{M 1} side contact surface _A 2, _{A 3} is of the machined portion _{M 1} extending across the workpiece portions M ₁ spanwise length L _{M1 (see} FIG. 3) in the vicinity. Shape in the Y ₁ direction as viewed edge E _2, E ₃ is not limited to the illustrated, it may be curved. Edge _E 2, _{E 3} along the portion to be processed _{M 1,} may extend substantially parallel to the workpiece unit _{M 1.}

Each abutment surface _A 2, _{A 3} of the edge _E 2, _E of spanwise length of the portion extending along the portion to be processed _{M 1} of _{3 (Z 1} direction _{length) L E2,} L _E3 (FIG. 4 and see FIG. 5) is preferably respectively 70% or more of the spanwise length L _M1 of the processing unit M _1. It is more preferably 80% or more, further preferably 90% or more, and most preferably 100% or more. Of the end edges E ₂ and E ₃ of both contact surfaces A ₂ and A ₃ , the portion extending along the workpiece M ₁ is the airfoil portion S in order to improve the support rigidity by the end edges E ₂ and E _{3. 1} may be arranged so as to contour overlap each other in the Y ₁ direction projected in nipped state.

3 and 6 (b) perpendicular on the blade surface, between the region boundary and the edge E _2, E ₃ of the machined portion M _1, the spanwise (Z ₁ direction) A predetermined distance d ₁ is provided in the direction of movement. The size of the distance _{d 1} is particularly but not limited to, over spanwise length _{L E2, L E3} entire portion extending along the machined portion _{M 1} of the edge _E 2, _{E 3,} the multi-axis machine It is preferable that the tip diameter D of the tool T such as the end mill used in the above is in the range of 5% or more and 200% or less. It is more preferably 5% or more and 100% or less, further preferably 5% or more and 60% or less, and most preferably 5% or more and 40% or less. Holding portions 2 and _{3 so that} the edge edges E ₂ and E ₃ of the contact surfaces A ₂ and A ₃ are as close as possible to the workpiece M ₁ while avoiding interference between the sandwiching portions 2 and 3 and the tool T. An inclined surface or concave surfaces 2d and 3d may be formed on the front portion of the surface.

Further, as shown in FIG. 3, the outer peripheral edges of the contact surfaces A ₂ and A _{3 have} end edges E ₂ and E ₃ on the machined portion M ₁ side (front side) and the machined portion M in a plan view. _It has a shape such that the maximum blade thickness line L _S is located between the edge edges E ₄ and E ₅ on the opposite side (rear side) from the ₁ side. That is, when the contact surface _A 2, _{A 3} is in contact with the area _{A S,} the edge _E 2, _E trailing edge _{S 1T} side than _3, and the edge _E 4, _E before the ₅ edge The maximum blade thickness line L _S is located on the S _1L side. Still other words, when the contact surface A _2, A ₃ is in contact with the area A _S, (also referred to as the maximum blade thickness portion collectively) maximum blade Atsusen L _S and the adjacent region thereof on the blade surface but contact over the length of the maximum blade Atsusen L _S abutment surface _a 2, _{a 3.} The length of the contact region between the maximum blade thickness portion and the contact surfaces A ₂ and A _{3 in} the blade length direction is preferably 70% or more, more preferably 80% or more of the length of the maximum blade thickness line L _S. , More preferably 90% or more. The maximum blade thickness line L _S is a line formed by connecting the maximum blade thickness positions in the blade cross section at each blade length direction in the blade length direction.

Blade gripping tool 1, the right clamping portion 2 of the stationary side may be provided with a positioning portion 12 for positioning the position of the airfoil S ₁ with respect to the abutment surface A _2, A _3. For example, as shown in FIG. 4, protrusions 2e and 2f protruding to the left from the side surface 2c may be provided on the upper and lower portions of the left side surface 2c of the right holding portion 2, and the front surfaces thereof may be used as the positioning portion 12. Further, the upper surface 4d of the base portion 4 connected to the lower end of the right holding portion 2 may be used as the positioning portion 12.

When setting by inserting the stator blade S into the gap G between both of the two sandwiching portions 2, 3, upper and lower projections 2e, the front surface of the 2f, for example, as shown in FIG. 4, respectively inner and outer ends S ₂ , S ₃ to abut on the rear ends of the engaging portions S _2a , S _3a . Thus, the upper and lower projections 2e, the front surface of the 2f positions the _{X 1} direction position of the airfoil _{S 1} with respect to the abutment surface _A 2, _{A 3.} Further, the upper surface 4d of the base portion 4 abuts on the lower surface of the inner end portion S ₂ to position the airfoil portion S _{1 in} the Z ₁ direction with respect to the contact surfaces A ₂ and A ₃ . Incidentally, the projections 2e, either or both of 2f, and detachably configured for right gripping unit 2, the airfoil has a surface shape of the S ₁ is common inner end S ₂ or outer end portion S Positioning portions for stator blades having different shapes of ₃ may be formed.

When using the blade gripping jig 1, first, the blade gripping jig 1 is positioned and fixed at a predetermined position on the table of the multi-axis machine. Next, as shown in FIG. 6A, the cam lever 8 of the cam lever mechanism 5 is rotated to the unclamped position, and the left holding portion 3 is moved to the open position. Then, as shown by the alternate long and short dash line in FIGS. 4 and 6 (a), the stator blade S is inserted into the gap G formed between the two sandwiching portions 2 and 3, and the both end portions S ₂ and S ₃ are positioned. is brought into contact with the 12 to position the position of the airfoil _{S 1} with respect to the abutment surface _a 2, _{a 3.} After that, as shown in FIG. 6B, the cam lever 8 is rotated to the clamp position to move the left holding portion 3 to the closed position, whereby the airfoil portion S is placed between the left and right holding portions 2 and 3. Hold ₁ in between. When taking out the stator blade S from the holding portions 2 and 3, the operation opposite to the above may be performed.

Hereinafter, the action and effect of this embodiment will be described.

(1) During machining such as cutting and grinding, a continuous vibration generally called chatter vibration may occur in a workpiece, tools or machine tool. The chatter vibration is roughly classified into forced chatter vibration and self-excited chatter vibration according to the cause of the vibration. Forced chatter vibration is a manifestation of some kind of forced vibration caused by the vibration characteristics of the machine, and the vibration source is, for example, the periodic cutting force in intermittent cutting of milling (including end milling). , There is vibration of the drive system of the machine tool. Self-excited chatter vibration occurs when there is a closed loop in the machining process that feeds back the vibration and expands it. When chatter vibration occurs, the dimensional accuracy of the work surface of the workpiece may decrease or the surface roughness may deteriorate.

In the blade gripping tool 1, when clamping the airfoil _{S 1} by the pair of clamping portions 2 and 3, the abutment surface _A 2, the edge _E 2 of the machined portion _{M 1} side _{A 3, E 3,} extending over the spanwise length L _M1 in the vicinity of the machined portion M _1. That is, the work portion M ₁ of the airfoil S ₁ is over its spanwise length L _M1, is supported near. Therefore, according to the blade gripping tool 1, to prevent the can increase the support rigidity of the work unit M _1, during processing, is chatter stator blades S vibrations by a load that is intermittently input occurs Can be done. In addition, the deflection of the stator blade S due to cutting force, grinding force, etc. can be suppressed, and the machining accuracy can be improved.

(2) Further, in the blade gripping tool 1, the positioning portion 12 abuts against the inner end S ₂ and the outer end portion S ₃ is a portion other than the airfoil S ₁ of the stator blade S, abutment surface positioning the position of the airfoil _{S 1} with respect to _{a 2,} a _3. Therefore, when clamping the airfoil _{S 1} in a sandwich portions 2 and 3, a predetermined positional relationship with the airfoil _{S 1} and the contact surface _A 2, _{A 3 (X 1} direction and the _{Z 1} direction relative position, and it is easy to place the relative angle) around an axis parallel to the Y ₁ direction. Thus, such polarization per between the airfoil S ₁ and abutment surface A _2, A _3, may be undesirable load is prevented from acting on the airfoil S _1.

(3) Furthermore, the blade gripping tool 1, the abutment surface A _2, A _3, has a surface shape that each of the surface of the airfoil S ₁ is following the surface shape of the abutting area A _S ing. Therefore, contact with the surface of the airfoil S ₁ having a three-dimensional curved surface shape, it is possible to contact surface A _2, A ₃ abuts or surface contact in a wider range, the airfoil S ₁ It becomes possible to arrange the surfaces A ₂ and A ₃ with higher accuracy. Further, it is possible to reduce the contact surface pressure of the contact surface A _2, A ₃ when clamping the airfoil S ₁ in a sandwich portions 2 and 3, the surface damage of the airfoil S ₁ by pinching Can be prevented.

(4) Further, in the blade gripping tool 1, the outer peripheral edge of each contact surface _A 2, _{A 3} are, in a plan view of the abutment surface _A 2, _{A 3} when in contact with the area _{A S,} the workpiece It has a shape such that the maximum blade thickness line L _S is located between the edge edges E ₂ and E ₃ on the side of the portion M _{1 and} the edge edges E ₄ and E ₅ on the opposite side. Therefore, when clamping the airfoil S ₁ in a sandwich portions 2 and 3, contact surface A _2, A ₃ part distance between becomes maximum, that is, the portion corresponding to the maximum blade thickness portion of the stator blade S , The maximum wing thickness is easy to fit. Thus, the airfoil S ₁ and the contact surface A _2, A _3, it is easy to place in a predetermined positional relationship in particular X ₁ direction.

(5) As a known blade processing method, a resin material is solidified and continuously provided in the middle part of the blade, and while the solidified resin material near the processing point is gripped by the rotary chuck of the processing machine, the blade surface including the solidified resin is held. There is a method for processing (see JP-A-2011-733131). On the other hand, in the blade gripping jig 1, since it is not necessary to solidify and continuously install a resin material in the middle portion of the blade, the above method is particularly used when processing a part of the stator blade S (for example, the front edge portion S _1L ). The processing process can be simplified as compared with the above.

(6) Further, while the support device described in Patent Document 1 is provided with a work support mechanism for supporting the work on the back surface of the work surface, the blade gripping jig 1 supports the work. The stator blade S can be gripped with high support rigidity without providing a mechanism. That is, according to the blade gripping jig 1, the structure of the entire device can be simplified as compared with the support device described in Patent Document 1.

In the first embodiment, the abutment surface _A 2, _{A 3} of the clamping portion 2, following the surface shape of the region _{A S} on the surface of the central portion _{S 1M} and trailing edge _{S 1T} of stator blades S It had a surface shape. However, the contact surfaces A ₂ and A ₃ are provided with a surface shape that follows the surface shape of the region (for example, the central portion S _1M and the front edge portion S _1L ) excluding the trailing edge portion S _1T of the stator blade S. The contact surfaces A ₂ and A ₃ may be brought into contact with the surface of the region. According to this modification, a part or all of the trailing edge portion S _1T of the stator blade S can be used as the workpiece portion.

<Second Embodiment>
As shown in FIGS. 7 and 8, the blade gripping jig 21 according to the second embodiment has a part or all of the front edge portion R _1L and the trailing edge portion R _1T of the airfoil portion R ₁ of the rotor blade R. It is a jig for gripping the rotor blade R at the time of processing. The blade gripping jig 21 is used by being placed and fixed on the table of a multi-axis processing machine such as a 5-axis processing machine.

The rotor blade R, which is the blade to be gripped, is, for example, a moving blade for a high-pressure axial compressor. The rotor blade R is made of, for example, a heat-resistant alloy, and as shown in FIG. 8, a blade shape portion R ₁ having a blade cross section (airfoil shape), a dove tail portion R _2, and a platform portion R located between them. _{Has 3} and. The dovetail portion R ₂ is fitted and fixed in a dovetail groove provided on the outer peripheral portion of a rotor disk (not shown).

The airfoil portion R ₁ includes a front edge portion R _1L , a trailing edge portion R _1T, and a central portion R _1M located between them in the chord direction. The position of the maximum blade thickness of the airfoil portion R ₁ and the position of the maximum camber belong to the central portion R _1M . The maximum blade thickness is not particularly limited, but is, for example, about 2 mm. The surface of the airfoil portion R ₁ , that is, the airfoil surface, has a three-dimensional curved surface shape. In this embodiment, at least the surface of the central portion _R1M has a final product shape or a shape close to the final product shape (near net shape). Therefore, the central portion R _1M is excluded from the processing range.

Blade gripping tool 21, as shown in FIG. 7, a pair of holding portions 22, 23 for clamping the airfoil R ₁ from the thickness direction both sides. The sandwiching portions 22 and 23 are connected to each other so as to be openable and closable via a hinge pin 24.

In the following description of the present embodiment, as shown in FIG. 7, when the sandwiching portion 22 and 23 sandwich the airfoil R _1, the side on which the airfoil R ₁ which is held against the hinge pin 24 is positioned The front side is the front side, and the opposite side is the rear side. Further, substantially parallel to the thickness direction of the clamping portions 22, 23 of the clamping state airfoil R _1, a direction orthogonal to the longitudinal direction X ₂ and the vertical direction Z _2. In the blade gripping jig 21, the side fixed to the table of the multi-axis machine is the lower side, and the opposite side is the upper side. Further, a direction orthogonal to the front-rear direction X ₂ and the vertical direction Z ₂ and substantially parallel to the extending direction of the hinge pin 24 is defined as the left-right direction Y ₂ . It should be noted that these directions are defined for convenience in order to explain the relative positional relationship between each part / element in the present embodiment, and do not limit the actual mounting posture of the blade gripping jig 21. Absent. The front-back direction X ₂ , the left-right direction Y _2, and the up-down direction Z ₂ are also simply referred to as the X ₂ direction, the Y ₂ direction, and the Z ₂ direction, respectively.

As shown in FIG. 7, the upper holding portion (hereinafter, upper holding portion) 22 of the holding portions 22 and 23 is the rear end portion of the lower holding portion (hereinafter, lower holding portion) 23 at the rear end portion. Is connected via a hinge pin 24. The upper holding portion 22 has an open position (see FIG. 11) separated from the lower holding portion 23 with respect to the lower holding portion 23, and a closed position (FIG. 12) when the rotor blade R is sandwiched between the lower holding portion 23. It is rotatable around the hinge pin 24 (see). In the open position, a gap G having a size sufficient for setting the rotor blade R or taking out the rotor blade R from between them is formed between the holding portions 22 and 23.

As shown in FIGS. 9 and 10, both sandwiching portions 22 and 23 are made of a metal such as brass or aluminum alloy, or a resin such as polycarbonate, which is softer (lower hardness) than the rotor blade R which is a workpiece. It is provided with holding pieces 22A and 23A, respectively. The upper holding piece (hereinafter referred to as the upper holding piece) 22A can be attached to and detached from the side surface of the upper holding portion 22 facing the lower holding portion 23 when the upper holding portion 22 is in the closed position by, for example, a fastener such as a bolt. It is attached. The lower holding piece (hereinafter referred to as the lower holding piece) 23A is detachably attached to the side surface of the lower holding portion 23 facing the upper holding portion 22 when the upper holding portion 22 is in the closed position by a fastener. There is.

As shown in FIG. 7, the blade gripping jig 21 may include a holding device 25 provided with a toggle mechanism 25 _T for pressing and holding the upper holding portion 22 in the closed position toward the lower holding portion 23 side. .. Examples of such a holding device 25 include a MISUMI toggle clamp. The holding device 25 can be fixed to, for example, a mounting base 26 fixed to the lower holding portion 23 by using a fastener 26a such as a bolt.

In the holding device 25, when the handle 25a is tilted to the rear side, the arm 25b retracts upward, and when the handle 25a is raised to the front side, the arm 25b is tilted horizontally. Further, when the holding device 25 brings the lower end of the holding metal fitting 25c into contact with the upper surface of the upper holding portion 22 in the closed position and then raises the handle 25a further to the front side, the lower end of the holding metal fitting 25c is brought into contact with the upper holding portion 22. It is designed to be locked when pressed against the top surface.

The sandwiching portions 22 and 23 have contact surfaces A ₂₂ and A ₂₃ that come into contact with the surface of the airfoil portion R ₁ when the airfoil portion R ₁ is sandwiched. As shown in FIG. 10, the upper holding portion 22 has a contact surface A ₂₂ on the lower side surface of the upper holding piece 22A, and the lower holding portion 23 has the lower holding piece 23A as shown in FIG. Has a contact surface A ₂₃ on the upper side surface of the. Each of the contact surfaces A ₂₂ and A ₂₃ is a region of the surface of the airfoil portion R ₁ excluding the workpieces M ₂ and M ₃ , for example, in the present embodiment, the central portion R _1M as shown in FIG. Contact the surface. Abutment surface A _22, A _23, the surface shape of each following the surface shape of the region A _R abutting the airfoil R ₁ of the surface, i.e. each was transferred to the surface shape of the abutting region A _R shape Each has. Grooves, irregularities, etc. may be formed on the surfaces of the contact surfaces A ₂₂ and A ₂₃ in order to make the contact surface pressure more appropriate.

Edge _E 6, _{E 7} of one of the processing unit _{M 2} side of the abutment surface _{A 22, A 23} (front edge _{R 1L} side), against the abutment surface _{A 22, A 23} is a region _{A R} when in contact, extending in span direction length L _M2 of the processing unit M ₂ in the vicinity of the processing unit M _2. Also, the edge _E 8, _{E 9} of the other portion to be processed _{M 3} side of the abutment surface _{A 22, A 23} (trailing edge _{R 1T} side) abutment surface _{A 22, A 23} is in the area _{A R} when in contact, extending in span direction length L _M3 of the processing unit M ₃ in the vicinity of the processing unit M _3. Shape at the edge _{E 6, E 7, E 8} , Z 2 as viewed in the direction of _{E 9} are not limited to those shown, it may be curved. Edge _E 6, _{E 7} along the workpiece unit _{M 2,} may extend substantially parallel to the workpiece unit _{M 2,} also, the edges _E 8, _{E 9} is the work unit _{M 3} along, it may extend substantially parallel to the workpiece unit M _3.

Spanwise length of the portion extending along the portion to be processed _{M 2} of the edge _E 6, _{E 7 (X 2} direction _length) L _{E6, L E7} (see FIGS. 9 and 10) is, the machined portion spanwise length of M _{2 L M2} is preferably (see FIG. 8) 70% or more. It is more preferably 80% or more, further preferably 90% or more, and most preferably 100% or more. Similarly, spanwise length of the portion extending along the portion to be processed _{M 3} of the edge _E 8, _{E 9 (X 2} direction _length) L _{E8, L E9} (see FIGS. 9 and 10) is preferably at least 70% of the machined portion _{M 3} spanwise length _{L M3} (see FIG. 8). It is more preferably 80% or more, further preferably 90% or more, and most preferably 100% or more.

Portion extending along the machined portion _{M 2} of the right-hand edge _E 6, _{E 7} of each abutment face _{A 22, A 23,} in order to improve the support rigidity by the edge _E 6, _{E 7,} airfoil in the state which sandwiches part R _1, may be arranged to contour the Z ₂ direction projection overlap each other. Similarly, of the left end edges E ₈ and E ₉ of both contact surfaces A ₂₂ and A ₂₃ , the portion extending along the workpiece M ₃ is projected in the Z ₂ direction with the airfoil portion R ₁ sandwiched. The contours of the above may be arranged so as to overlap each other.

As shown in FIG. 8, on the blade surface, between the region boundary of the workpieces M ₂ and M ₃ and the edge edges E ₆ , E ₇ , E ₈ and E ₉ , respectively, in the blade length direction (X _2). The predetermined distances d ₂ and d ₃ are provided in the direction orthogonal to the direction). The size of the distance _{d 2} is not particularly limited, in span direction length _{L E6, L E7} entire portion extending along the machined portion _{M 2} of the Kakutan'en _E 6, _{E 7,} end mill tool It is preferably within the range of 5% or more and 200% or less of the tip diameter D of T. It is more preferably 5% or more and 100% or less, further preferably 5% or more and 60% or less, and most preferably 5% or more and 40% or less. Similarly, the size of the distance d ₃ is not particularly limited, but the lengths L _E8 and L _E9 in the blade length direction of the portions of the end edges E ₈ and E ₉ extending along the workpiece M ₃ are covered. It is preferably within the range of 5% or more and 200% or less of the tip diameter D of the tool T such as an end mill. It is more preferably 5% or more and 100% or less, further preferably 5% or more and 60% or less, and most preferably 5% or more and 40% or less.

Further, as shown in FIG. 8, the outer peripheral edge of each abutment surface _{A 22, A 23} are, in plan view, the edge _E 6, _{E 7} of one of the processing unit _{M 2} side, the other of the processing unit It has a shape such that the maximum blade thickness line _LR is located between the end edges E ₈ and E ₉ on the M ₃ side. That is, when each abutting surface _{A 22, A 23} is in contact with the area _{A R,} the edge _E 6, a rear edge _{R 1T} side of _{E 7,} and, before the edges _E 8, _{E 9} edge The maximum blade thickness line _LR is located on the part R _1L side. Still other words, when the contact surface A _22, A ₂₃ is in contact with the area A _R, (also referred to as the maximum blade thickness portion collectively) maximum blade Atsusen L _R and the adjacent region thereof on the blade surface but contact over the length of the maximum blade Atsusen _{L R} the contact surface _{a 22, a 23.} Spanwise length of the contact region of the maximum blade thickness portion and the contact surface A _22, A ₂₃ is preferably at maximum blade Atsusen L 70% or more of the length of _R, more preferably 80% or more , More preferably 90% or more.

Blade gripping tool 21, for example, as shown in FIGS. 7 and 9, the lower clamping portion 23 of the fixed side, a positioning unit 27 for positioning the position of the airfoil R ₁ for abutment surface A _22, A ₂₃ You may prepare. Positioning unit 27 has a guide surface 27a, the guide surface 27a, when the airfoil _{R 1} is placed in a predetermined posture on the contact surface _{A 23} of the lower clamping pieces 23A, dovetail _{R 2} Is installed at a position and an inclination angle so that the side surface of the guide surface 27a abuts in parallel with the guide surface 27a. Here, the predetermined posture means that the positional relationship between the airfoil portion R ₁ and the lower holding portion 23 (relative positions in the X ₂ direction and Y ₂ direction, and relative angles around the axis parallel to the Z ₂ direction) is the wing. It refers to posture such that substantially the same as their positional relationship at the time of sandwiching the shaped portion R _1.

When the rotor blade R is set on the contact surface A ₂₃ of the lower holding portion 23 with the upper holding portion 22 in the open position, the guide surface 27a comes into contact with the side surface of the dovetail portion R ₂ and comes into contact with the contact surface. positioning the position of the airfoil _{R 1} for _{a 22,} a _23.

The guide surface 27a can be formed by attaching a guide piece 27b made of a metal or resin softer (lower hardness) than the rotor blade R to an inclined surface provided at the front portion of the lower holding portion 23. The position tolerance of the dovetail portion R ₂ with respect to the airfoil R ₁ in the direction perpendicular to the spanwise direction is relatively large, the positional accuracy of the guide surface 27a therefore against the abutment surface A ₂₃ may be low.

As shown in FIG. 7, the blade gripping jig 21 may include a base 28 that supports the lower holding portion 23. The blade gripping jig 21 is positioned and fixed on the table of the multi-axis machine by fastening the base 28 on the table of the multi-axis machine (not shown). Further, as shown in FIGS. 7 and 9, between the positioning portion 27 and the Shitakyo supporting pieces 23A, a concave portion 23a may be provided for avoiding interference with the platform portion R _3.

When using the blade gripping jig 21, first, the blade gripping jig 21 is positioned and fixed at a predetermined position on the table of the multi-axis machine. Next, as shown in FIG. 11A, the handle 25a of the holding device 25 is tilted rearward, the arm 25b is retracted upward, and the upper holding portion 22 is manually rotated to the open position. In that state, as shown in FIG. 11B, the rotor blade R is set on the contact surface A ₂₃ of the lower holding portion 23, the dovetail portion R ₂ is brought into contact with the positioning portion 27, and the contact surface A positioning the position of the airfoil _{R 1} for _23. Then, as shown in FIG. 12 (c), the upper holding portion 22 is manually rotated to the closed position, and then, as shown in FIG. 12 (d), the handle 25a of the holding device 25 is raised to the front side and pressed. The metal fitting 25c is locked while being pressed against the upper holding portion 22. Thereby clamping the airfoil _{R 1} between the upper and lower clamping portions 22, 23. When the rotor blade R is taken out from the holding portions 22 and 23, the operation opposite to the above may be performed.

Hereinafter, the action and effect of this embodiment will be described.

(7) In the blade gripping tool 21, when clamping the airfoil _{R 1} a pair of clamping portions 22 and 23, the abutment surface _{A 22,} one of the machined portion _{M 2} side of _{A 23} (front edge R edge _E 6, _{E 7} of _1L side), extends over the spanwise length _{L M2} in the vicinity of the machined portion _{M 2.} Also, the edge _E 8, _{E 9} is the spanwise length in the vicinity of the processing portion _{M 3} of the other portion to be processed _{M 3} side of the abutment surface _{A 22, A 23} (trailing edge _{R 1T} side) It is extending over _{L M3.} That is, the machined portion _M 2, _{M 3} of the airfoil _{R 1} are each, over its spanwise length _{L M2, L M3,} is supported near. Therefore, according to the blade gripping jig 21, the support rigidity of the workpieces M ₂ and M ₃ can be increased, and the rotor blade R is caused to chatter and vibrate due to the intermittently input load during machining. It can be suppressed. Further, the deflection of the rotor blade R due to cutting force, grinding force, etc. can be suppressed, and the machining accuracy can be improved.

(8) Further, in the blade gripping jig 21, the positioning portion 27 abuts on the dovetail portion R ₂ which is a portion other than the airfoil portion R ₁ of the rotor blade R, and the blade with respect to the contact surfaces A ₂₂ and A ₂₃ . positioning the position of the shaped portion R _1. Therefore, when clamping the airfoil _{R 1} in a sandwich portions 22 and 23, a predetermined positional relationship with the airfoil _{R 1} and contact surface _{A 22, A 23 (X 2} direction and _{Y 2} directions position relative, and it is easy to place the relative angle) around an axis parallel to the Z ₂ direction. As a result, it is possible to prevent an unfavorable load such as an unbalanced contact between the airfoil portion R ₁ and the contact surfaces A ₂₂ and A _{23 from} acting on the airfoil portion R ₁ .

(9) Furthermore, the blade gripping tool 21, the abutment surface A _22, A ₂₃ has a surface shape that each of the surface of the airfoil R ₁ is following the surface shape of the abutting region A _R ing. Therefore, the surface of the airfoil R ₁ having a three-dimensional curved surface shape, it is possible abutting portion abuts or surface contact in a wider range, the airfoil R ₁ a contact surface A _22, A It becomes possible to arrange the ₂₃ more accurately. Further, since the contact surface pressure of the contact surfaces A ₂₂ and A ₂₃ when the airfoil portion R ₁ is sandwiched between the sandwiching portions 22 and ₂₃ can be reduced, damage to the surface of the airfoil portion R ₁ due to pinching can be prevented. Can be prevented.

(10) Further, the outer peripheral edge of each abutment surface _{A 22, A 23} are, in a plan view of the abutment surface _{A 22, A 23} at the time of contact with the area _{A R,} the portion to be processed _{M 2} side edge It has a shape such that the maximum blade thickness line _LR is located between E ₆ and E ₇ and the edge edges E ₈ and E ₉ on the side of the processed portion M ₃ . Therefore, when clamping the airfoil R ₁ in a sandwich portions 22 and 23, portions the interval between the abutment surface A _22, A ₂₃ is the maximum, that is, the portion corresponding to the maximum blade thickness portion of the rotor blades R , The maximum wing thickness is easy to fit. As a result, it becomes easy to arrange the airfoil portion R ₁ and the contact surfaces A ₂₂ and A ₂₃ in a predetermined positional relationship particularly in the Y ₂ direction.

Of course, in the present embodiment, the above-mentioned effects (5) and (6) can be obtained.

<Other embodiments>
In the first embodiment, the contact surfaces A ₂ and A ₃ are formed on the surface of the sandwiching portions 2 and 3 itself, but as in the second embodiment, each of the sandwiching portions 2 and 3 is made of, for example, resin. The holding pieces may be attached and contact surfaces A ₂ and A ₃ may be formed on the surfaces of the holding pieces facing each other. Further, by forming the holding portions 22 and 23 of the second embodiment from a metal or resin softer than the workpiece and directly forming the contact surfaces A ₂₂ and A ₂₃ on their surfaces, the holding pieces 22A and 23A are omitted. You may.

Further, the shapes of the contact surfaces A ₂ , A ₃ , A ₂₂ and A ₂₃ of the above embodiment can be appropriately selected according to the shape of the airfoil portion sandwiched by the sandwiching portion. For example, the surface area A _S on the blade _surface, A _R is, if not provided with the near net shape, an area A _S, to measure the actual surface shape of A _R, corresponding to the transfer shape this The shape may be given to the contact surfaces A ₂ , A ₃ , A ₂₂ , and A ₂₃ . Further, the workpiece gripped by the blade gripping jigs 1 and 21 is not limited to the one shown in the above embodiment, and may be, for example, a variable stator blade, a rotor blade with a shroud, or the like. In the blade gripping jig according to these modifications, a recess for avoiding interference with buttons, shrouds, etc., or a positioning portion for positioning the position of the airfoil portion with respect to the contact surface by contacting the buttons or the like is provided. It may be provided at a portion outside the contact surface of the holding portion.

Although some embodiments have been described above, the present disclosure is not limited to these embodiments, and various modifications and changes can be made within the scope of the gist thereof.

1,21 blade gripping tool 2,3,22,23 clamping portion _{A 2, A 3, A 22} , A 23 abutment surface _{E 2, E 3, E 4} , E 5, E 6, E 7, E 8 , E ₉ Edge edge 12, 27 Positioning part S, R Stator blade, rotor blade (blade)
S ₁ , R ₁ Airfoil S _1L , R _1L Front edge S _1T , R _{1T Trailing} edge S ₂ , S ₃ Ends (parts other than the airfoil)
R ₂ dovetail portion (portion other than the airfoil)
M _{1, M} 2, _{M 3} the machined portion A _{R, A S} abutment surface abuts region L _R, L _S maximum blade Atsusen

Claims (4)

A blade gripping jig for gripping the blade when at least one of the front edge portion and the trailing edge portion of the airfoil portion of the blade is machined as a machined portion.
A pair of sandwiching portions for sandwiching the airfoil portion from both sides in the thickness direction are provided.
Each of the pair of holding portions has a contact surface that comes into contact with a region of the surface of the airfoil portion excluding the processed portion when the airfoil portion is sandwiched.
When the contact surface comes into contact with the region, the edge of the contact surface on the workpiece side extends in the vicinity of the workpiece over the blade length direction length of the workpiece. Blade gripping jig. The blade gripping jig according to claim 1, further comprising a positioning portion that abuts on a portion of the blade other than the airfoil portion to position the position of the airfoil portion with respect to the contact surface. The blade gripping jig according to claim 1 or 2, wherein each of the contact surfaces has a surface shape that follows the surface shape of the region to which the contact surface contacts. When the contact surface comes into contact with the region, the contact surface has the airfoil shape between the edge on the side to be processed and the edge on the opposite side in the plan view of the contact surface. The blade gripping jig according to any one of claims 1 to 3, each having a shape such that the maximum blade thickness line of the portion is located.

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