Gas turbine rotor blade tip grinding tool and gas turbine rotor blade tip grinding method

Abstract

The present application relates to the technical field of engine, and discloses a gas turbine rotor blade tip grinding tool and a gas turbine rotor blade tip grinding method, wherein the gas turbine rotor blade tip grinding tool comprises a connecting rod, a turbine disc, a positioning sleeve, a first sleeve, a first pressing block, a second sleeve and a second pressing block; the turbine disc is sleeved on the connecting rod and is provided with a plurality of blade bodies at intervals on the outer periphery; the first sleeve is sleeved on the connecting rod; each first pressing block is arranged on the outer side end face of the first sleeve through a first fastener and abuts against one side surface of a blade body; each second pressing block is arranged on the outer side end face of the second sleeve through a second fastener and abuts against the other side surface of a blade body; the first fastener radially extrudes the first pressing block, and the second fastener radially extrudes the second pressing block, so that the blade body is opened. The blade body can be kept in an opened state for grinding and machining by the first pressing block and the second pressing block, the stress is uniform, and the structure is stable.

Description

Technical Field

[0001] This invention relates to the field of engine technology, and more specifically to a tooling for grinding gas turbine rotor blade tips and a method for grinding gas turbine rotor blade tips. Background Technology

[0002] A gas turbine, also known as a gas turbine, is a bladed machine that converts the energy of a high-temperature, high-pressure gas flow into mechanical energy. It is a core component of an engine. Gas turbines generally employ a tongue-and-groove connection structure, meaning that the turbine blades and turbine disk are connected via tongue and groove joints and secured with locking plates.

[0003] Gas turbine blades require blade tip grinding within the rotor assembly; however, these blades can only be fully opened during high-speed rotation. Ordinary grinding equipment cannot achieve the required blade opening speed. Therefore, a press is typically used to compress rubber, forcing the blades into a fully opened state, before the outer circumference of the blades is machined using grinding equipment.

[0004] The drawback of this structure is that the rubber is prone to aging and deterioration, and the existing grinding fixtures will cause uneven stress on the outer edge area of ​​the blade. During the processing of some blades, the grinding force is greater than the tension, which can easily cause the outer circle of the blade to loosen during the grinding process, resulting in the outer circle size and runout value of the blade exceeding the tolerance range. Summary of the Invention

[0005] In view of this, the present invention provides a gas turbine rotor blade tip grinding fixture and a gas turbine rotor blade tip grinding method to solve the problem that when a press is used to squeeze rubber to open and process the blade body, the blade body is subjected to uneven force, which easily leads to the blade body exceeding the tolerance range during processing.

[0006] In a first aspect, the present invention provides a grinding fixture for gas turbine rotor blade tips, comprising:

[0007] The connecting rod has a retaining ring in the middle area;

[0008] The turbine disk is fitted onto the connecting rod and has multiple blade bodies. One side of the turbine disk abuts against one end face of the retaining ring.

[0009] The positioning sleeve is fitted onto the connecting rod. One side of the positioning sleeve abuts against the other side of the turbine disk, and the opposite side is locked onto the connecting rod by a locking device. The turbine disk, positioning sleeve, and connecting rod are coaxially arranged.

[0010] The first sleeve is fitted onto the connecting rod and connected to the positioning sleeve;

[0011] Multiple first pressure blocks are set one-to-one with multiple blade bodies. Each first pressure block is set on the outer end face of the first sleeve by a first fastener and abuts against one side surface of a blade body.

[0012] The second sleeve is fitted onto the connecting rod and is fixedly connected to the other end face of the retaining ring;

[0013] Multiple second pressure blocks are set one-to-one with multiple blade bodies. Each second pressure block is set on the outer end face of the second sleeve by a second fastener and abuts against the opposite side surface of a blade body.

[0014] The first fastener radially presses against the first pressure block, and the second fastener radially presses against the second pressure block, so that the blade body opens.

[0015] Beneficial effects: This invention first fixes the turbine disk and the first sleeve to the connecting rod using a positioning sleeve, so that multiple first pressure blocks are correspondingly set with multiple blade bodies. Additionally, by fitting a second sleeve onto the connecting rod, multiple second pressure blocks are correspondingly set with multiple blade bodies. Because the first fastener radially presses against the first pressure block, and the second fastener radially presses against the second pressure block, the blade body is jointly pressed by the first and second pressure blocks, thus maintaining a fully open state, allowing ordinary grinding equipment to process the outer circumference of the blade body. Compared to the traditional structure that uses a press to squeeze rubber, the blade body of this invention experiences uniform force during grinding, has a stable structure, and achieves higher processing accuracy, effectively controlling the processing tolerances of the blade body.

[0016] In one alternative embodiment, the outer end face of the first sleeve is provided with a step to form a first end face and a second end face. The first pressure block is fixed to the first end face by a first fastener. The second end face is provided with a first baffle. The projection of the first baffle in the direction perpendicular to the axis of the first sleeve can cover part or all of the first pressure block.

[0017] Beneficial effects: Since the first pressure block is fixed to the first end face by the first fastener and the second end face is provided with the first baffle, the first pressure block is set inside the first baffle, so the first baffle can prevent the first pressure block from detaching from the first sleeve during use.

[0018] In one alternative embodiment, the first sleeve and the positioning sleeve are fixedly connected by a third fastener, and a first adjusting pad is provided between the first sleeve and the positioning sleeve.

[0019] Beneficial effects: The first sleeve and the positioning sleeve are fixedly connected by a third fastener, resulting in lower operating costs. A first adjusting shim is provided between the first sleeve and the positioning sleeve, which allows for adjustment of the axial position of the blade body.

[0020] In one alternative embodiment, a pressure cap is further included, which is sleeved on the connecting rod and fixedly connected to the second sleeve by a fourth fastener. The pressure cap also abuts against the second pressure block by a soft gasket.

[0021] Beneficial effects: The gland is fixedly connected to the second sleeve via a fourth fastener, used to secure the second sleeve. The gland also abuts against the second pressure block via a soft gasket, which eliminates the height difference of the blade body and ensures uniform force on the blade body.

[0022] In one alternative embodiment, a second adjusting shim is provided between the gland and the second sleeve.

[0023] Beneficial effect: A second adjusting shim is provided between the gland and the second sleeve. The compression of the soft shim can be adjusted by the second adjusting shim in order to eliminate the height difference of the blade body.

[0024] In one alternative embodiment, the outer end face of the gland extends axially to form a second baffle, the projection of the second baffle in a direction perpendicular to the axis of the second sleeve being able to cover part or all of the second pressure block.

[0025] Beneficial effect: Since the projection of the second baffle in the direction perpendicular to the axis of the second sleeve can cover part or all of the second pressure block, the second baffle can prevent the second pressure block from detaching from the second sleeve during use.

[0026] In one optional embodiment, a counterseat element is further included, which is sleeved on the connecting rod and spaced apart from the pressure cap, and the counterseat element is coaxial with the connecting rod.

[0027] Beneficial effects: By directly mounting a dial indicator on the connecting rod, the dial indicator can be directly compared with the ground blade body, enabling intuitive detection and judgment of whether the blade body grinding is qualified, shortening the quality inspection time of the blade body, and thus improving the processing efficiency of the blade body.

[0028] In one alternative embodiment, the end faces of opposite ends of the connecting rod are respectively provided with positioning center holes.

[0029] Beneficial effects: The end faces of the two opposite ends of the connecting rod are respectively provided with positioning center holes, which facilitates the clamping of the connecting rod with two centers through the positioning center holes, thereby calibrating the coaxiality of the connecting rod with components such as the turbine disk and the first sleeve, and also facilitates the improvement of the installation accuracy of the connecting rod and the grinding equipment.

[0030] Secondly, the present invention also provides a method for grinding the tip of a gas turbine rotor, comprising the following steps:

[0031] The turbine disc is fitted onto the connecting rod, so that one side of the turbine disc abuts against one end face of the retaining ring of the connecting rod, and the other side is connected to the positioning sleeve. The positioning sleeve is locked to the connecting rod by a locking device.

[0032] Calibrate and re-measure the coaxiality of the turbine disk, connecting rod, and positioning sleeve;

[0033] The first pressure block is placed on the outer end face of the first sleeve by the first fastener; the first sleeve is sleeved on the connecting rod and connected to the positioning sleeve;

[0034] Multiple blade bodies are installed into the turbine disk;

[0035] The second pressure block is placed on the outer end face of the second sleeve by the second fastener; the second sleeve is sleeved on the connecting rod and fixedly connected to the other end face of the retaining ring;

[0036] Adjust the first sleeve so that multiple first pressure blocks correspond one-to-one with multiple blade bodies, and at the same time adjust the second sleeve so that multiple second pressure blocks correspond one-to-one with multiple blade bodies;

[0037] Tighten the first fastener to radially press the first pressure block, and at the same time, tighten the second fastener to radially press the second pressure block, so that the blade body opens.

[0038] The outer circumference of the blade body is machined using grinding equipment.

[0039] Beneficial effects: This invention first fixes the turbine disk and the first sleeve to the connecting rod using a positioning sleeve, so that multiple first pressure blocks are correspondingly set with multiple blade bodies. Additionally, by fitting a second sleeve onto the connecting rod, multiple second pressure blocks are correspondingly set with multiple blade bodies. Because the first fastener radially presses against the first pressure block, and the second fastener radially presses against the second pressure block, the blade body is jointly pressed against the first and second pressure blocks, thus maintaining a fully open state, allowing ordinary grinding equipment to process the outer circumference of the blade body. The blade body of this invention experiences uniform force during grinding, has a stable structure, and achieves high machining accuracy, effectively controlling the machining tolerances of the blade body.

[0040] In one alternative implementation, the following steps are also included:

[0041] After machining the outer circumference of the blade body, loosen the first fastener and the second fastener; remove the first sleeve, the first pressure block and the positioning sleeve.

[0042] Replace the turbine disk with another one, and reinstall the first sleeve, the first pressure block and the positioning sleeve; install the unprocessed blade body into the turbine disk;

[0043] The first sleeve is readjusted so that the multiple first pressure blocks correspond one-to-one with the multiple blade bodies, and the second sleeve is readjusted so that the multiple second pressure blocks correspond one-to-one with the multiple blade bodies.

[0044] Tighten the first fastener to radially press the first pressure block, and at the same time, tighten the second fastener to radially press the second pressure block, so that the blade body opens.

[0045] The outer circumference of the blade body is machined using grinding equipment.

[0046] Beneficial effects: When grinding the blade bodies of other turbine disks in subsequent processes, this invention only requires disassembling the first sleeve, the first pressure block, and the positioning sleeve, without disassembling all components. Afterwards, the turbine disk and blade body are reinstalled, and the positions of the blade body relative to the first and second pressure blocks are recalibrated before grinding the subsequent blade bodies, thus improving the efficiency of the cyclic processing of blade bodies. Attached Figure Description

[0047] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0048] Figure 1 This is a schematic diagram of the structure of a gas turbine rotor blade tip grinding fixture according to an embodiment of the present invention;

[0049] Figure 2 This is a schematic diagram of the lower module of a gas turbine rotor blade tip grinding fixture according to an embodiment of the present invention;

[0050] Figure 3 This is a schematic diagram of the upper module of a gas turbine rotor blade tip grinding fixture according to an embodiment of the present invention;

[0051] Figure 4 This is a schematic diagram of the structure of a gas turbine rotor blade tip grinding fixture mounted on an upper module according to an embodiment of the present invention;

[0052] Figure 5 This is a partial structural schematic diagram of a gas turbine rotor blade tip grinding fixture according to an embodiment of the present invention;

[0053] Figure 6 for Figure 5 Sectional view at point AA;

[0054] Figure 7 This is a diagram showing the positional relationship between the first pressing block, the second pressing block, and the blade body in an embodiment of the present invention.

[0055] Figure 8 This is a schematic diagram from another perspective of a gas turbine rotor blade tip grinding fixture according to an embodiment of the present invention;

[0056] Figure 9 This is a schematic diagram of the coaxiality check point of a gas turbine rotor blade tip grinding fixture according to an embodiment of the present invention.

[0057] Explanation of reference numerals in the attached figures:

[0058] 1. Connecting rod; 101. Retaining ring; 102. Positioning center hole; 2. Turbine disk; 3. Blade body; 4. Positioning sleeve; 5. Locking component; 6. First sleeve; 601. First end face; 602. Second end face; 603. First baffle; 7. First pressure block; 8. First fastener; 9. Second sleeve; 10. Second pressure block; 11. Second fastener; 12. Third fastener; 13. First adjusting shim; 14. Pressure cap; 1401. Second baffle; 15. Fourth fastener; 16. Soft shim; 17. Second adjusting shim; 18. Alignment component. Detailed Implementation

[0059] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0060] Existing gas turbine rotor blade tip grinding fixtures use a press to squeeze rubber to open the blade body, resulting in uneven stress on the blade body and easily causing the blade body to exceed tolerance ranges during grinding. This invention addresses this issue by applying radial pressure to a first and second pressure block, causing them to press tightly against the blade body. This allows the blade body to remain open during grinding, resulting in uniform stress distribution and structural stability, effectively controlling the processing tolerances of the blade body.

[0061] The following is combined with Figures 1 to 9 The following describes embodiments of the present invention.

[0062] According to embodiments of the present invention, in one aspect, such as Figure 1 As shown, a gas turbine rotor blade tip grinding fixture is provided, which mainly includes: a connecting rod 1, a turbine disk 2, a positioning sleeve 4, a first sleeve 6, a plurality of first pressure blocks 7, a second sleeve 9, and a plurality of second pressure blocks 10.

[0063] Specifically, a retaining ring 101 is provided in the middle region of the connecting rod 1. A turbine disk 2 is fitted onto the connecting rod 1 and has multiple blade bodies 3. One side of the turbine disk 2 abuts against one end face of the retaining ring 101. A positioning sleeve 4 is fitted onto the connecting rod 1. One side of the positioning sleeve 4 abuts against the other side of the turbine disk 2, and the opposite side is locked to the connecting rod 1 by a locking member 5. The turbine disk 2, positioning sleeve 4, and connecting rod 1 are coaxially arranged. A first sleeve 6 is fitted onto the connecting rod 1 and connected to the positioning sleeve 4. Multiple first pressure blocks 7 are arranged one-to-one with multiple blade bodies 3. Each first pressure block 7 is located on the outer end face of the first sleeve 6 by a first fastener 8 and abuts against one side surface of a blade body 3. A second sleeve 9 is fitted onto the connecting rod 1 and fixedly connected to the other end face of the retaining ring 101. Multiple second pressure blocks 10 are arranged one-to-one with multiple blade bodies 3. Each second pressure block 10 is disposed on the outer end face of the second sleeve 9 by a second fastener 11 and abuts against the opposite side surface of a blade body 3. The first fastener 8 radially presses the first pressure block 7, and the second fastener 11 radially presses the second pressure block 10 to open the blade body 3.

[0064] In this embodiment of the invention, the turbine disk 2 and the first sleeve 6 are firstly fixed to the connecting rod 1 by the positioning sleeve 4, so that multiple first pressure blocks 7 are correspondingly set with multiple blade bodies 3. Additionally, by fitting the second sleeve 9 onto the connecting rod 1, multiple second pressure blocks 10 are correspondingly set with multiple blade bodies 3. Because the first fastener 8 radially presses against the first pressure block 7, and the second fastener 11 radially presses against the second pressure block 10, the blade body 3 is jointly pressed by the first pressure block 7 and the second pressure block 10, thus maintaining a fully open state, allowing ordinary grinding equipment to process the outer diameter of the blade body 3. Compared to the traditional structure that uses a press to squeeze rubber, the blade body 3 of this invention experiences uniform force during grinding, has a stable structure, and higher processing accuracy, effectively controlling the processing tolerance of the blade body 3.

[0065] In addition, compared with the use of high-speed blade tip grinding equipment, the gas turbine rotor blade tip grinding fixture provided in this embodiment of the invention can use ordinary grinding equipment with a lower rotation speed, which can reduce the cost of grinding.

[0066] Specifically, the axis of connecting rod 1 is as follows: Figure 1 As shown in OO. One end of the connecting rod 1 is provided with an external thread, and the locking element 5 is a nut. By tightening the nut, the positioning sleeve 4 is pressed, so that the first sleeve 6 is fixed on the connecting rod 1. The first fastener 8 and the second fastener 11 can both be set screws. The turbine disk 2 is provided with a tenon, and multiple blade bodies 3 are set in the tenon.

[0067] Specifically, such as Figure 6 and Figure 7As shown, multiple first pressing blocks 7 and multiple second pressing blocks 10 are respectively arranged one-to-one with multiple blade bodies 3. Each blade body 3 has two opposite end faces abutted by a first pressing block 7 and a second pressing block 10. The first pressing blocks 7 and the second pressing blocks 10 can be made of metal alloy, such as aluminum alloy.

[0068] In one embodiment, such as Figure 2 As shown, the outer end face of the first sleeve 6 is provided with a step, forming a first end face 601 and a second end face 602. The first pressure block 7 is fixed to the first end face 601 by a first fastener 8. The second end face 602 is provided with a first baffle 603. Specifically, the first baffle 603 is tightened onto the second end face 602 by countersunk screws. The projection of the first baffle 603 in the direction perpendicular to the axis of the first sleeve 6 can cover part or all of the first pressure block 7. The first pressure block 7 is disposed inside the first baffle 603, so that the first baffle 603 can prevent the first pressure block 7 from detaching from the first sleeve 6 during use.

[0069] In one embodiment, such as Figure 1 and Figure 2 As shown, the first sleeve 6 and the positioning sleeve 4 are fixedly connected by the third fastener 12. A first adjusting shim 13 is provided between the first sleeve 6 and the positioning sleeve 4. The axial position of the blade body 3 can be adjusted by the first adjusting shim 13.

[0070] Specifically, the positioning sleeve 4 is an end-tooth positioning sleeve. The third fastener 12 is a screw set, which has a low cost of use. By increasing or decreasing the thickness of the first adjusting shim 13, the axial position of the first sleeve 6 relative to the turbine disk 2 can be adjusted, thereby adjusting the axial position of the blade body 3 relative to the first pressure block 7.

[0071] In one embodiment, such as Figure 1 and Figure 3 As shown, the gas turbine rotor blade tip grinding fixture also includes a pressure cap 14. The pressure cap 14 is sleeved on the connecting rod 1 and fixedly connected to the second sleeve 9 by a fourth fastener 15, used to fix the second sleeve 9. The pressure cap 14 also abuts against the second pressure block 10 through a soft gasket 16. The soft gasket 16 can eliminate the height difference of the blade body 3, ensure that the blade body 3 is subjected to uniform force, and avoid axial movement.

[0072] Specifically, the fourth fastener 15 can also be a screw assembly, which has a simple structure. The soft washer 16 is a fluororubber washer, which has moderate softness and hardness and is easy to use.

[0073] Furthermore, in one embodiment, a second adjusting shim 17 is provided between the pressure cap 14 and the second sleeve 9. The compression of the soft shim 16 can be adjusted by the second adjusting shim 17 to eliminate the height difference of the blade body 3.

[0074] Furthermore, in one embodiment, such as Figure 3 As shown, the outer end face of the pressure cap 14 extends axially to form a second baffle 1401. The projection of the second baffle 1401 in a direction perpendicular to the axis of the second sleeve 9 can cover part or all of the second pressure block 10. The second baffle 1401 can prevent the second pressure block 10 from detaching from the second sleeve 9 during use.

[0075] In one embodiment, such as Figure 1 , Figure 5 and Figure 8 As shown, the gas turbine rotor blade tip grinding fixture also includes a gauge piece 18. The gauge piece 18 is sleeved on the connecting rod 1 and spaced apart from the pressure cap 14, and is coaxial with the connecting rod 1. By directly sleeved on the connecting rod 1, the gauge piece 18 can be directly compared with the ground blade body 3, enabling intuitive detection and judgment of whether the grinding of the blade body 3 is qualified, shortening the quality inspection time of the blade body 3, and thus improving the processing efficiency of the blade body 3.

[0076] Specifically, after the blade body 3 is machined, the overall outer circumferential dimensions of the blade body 3 and the turbine disk 2 are the same as the outer circumferential dimensions of the matching part 18. The outer circumferential dimensions of the matching part 18 are as follows: Figure 8 As shown by line B in the diagram.

[0077] In addition, the connecting rod 1, turbine disk 2, positioning sleeve 4, and matching element 18 are all coaxially arranged. To improve the machining accuracy of the blade body 3, the connecting rod 1, turbine disk 2, positioning sleeve 4, and matching element 18 need to undergo a coaxiality test after installation. Figure 9 As shown, a first check point C is set on the outer periphery of the dial indicator 18, a second check point D and a third check point E are set on the outer periphery of the turbine disk 2, and a fourth check point F is set on the outer periphery of the positioning sleeve 4. By checking these four check points, coaxiality testing is achieved, making it convenient to use.

[0078] In one embodiment, such as Figure 1 As shown, the end faces of the two opposite ends of the connecting rod 1 are respectively provided with positioning center holes 102. This facilitates the clamping of the connecting rod 1 with two centers through the positioning center holes 102, thereby enabling the coaxiality of the connecting rod 1 with components such as the turbine disk 2 and the first sleeve 6, and also helps to improve the installation accuracy of the connecting rod 1 and the grinding equipment.

[0079] According to an embodiment of the present invention, in another aspect, a method for grinding the tip of a gas turbine rotor is also provided, comprising the following steps:

[0080] S100: The turbine disk 2 is fitted onto the connecting rod 1, so that one side of the turbine disk 2 abuts against one end face of the retaining ring 101 of the connecting rod 1, and the other side is connected to the positioning sleeve 4. The positioning sleeve 4 is locked to the connecting rod 1 by the locking member 5.

[0081] S200: Calibrate and retest the coaxiality of turbine disk 2, connecting rod 1 and positioning sleeve 4.

[0082] Specifically, the end faces of the two opposite ends of the connecting rod 1 are respectively provided with positioning center holes 102. The two centers are clamped through the positioning center holes 102, and the coaxiality of the turbine disk 2, the connecting rod 1, and the positioning sleeve 4 is calibrated. Since the turbine disk 2, the connecting rod 1, and the positioning sleeve 4 are coaxially arranged, the uniformity of the blade tip clearance between the rotor and stator can be improved.

[0083] S300: The first pressure block 7 is placed on the outer end face of the first sleeve 6 by the first fastener 8; the first sleeve 6 is sleeved on the connecting rod 1 and connected to the positioning sleeve 4.

[0084] S400: Multiple blade bodies 3 are installed into turbine disk 2.

[0085] S500: The second pressure block 10 is placed on the outer end face of the second sleeve 9 by the second fastener 11; the second sleeve 9 is sleeved on the connecting rod 1 and fixedly connected to the other end face of the retaining ring 101.

[0086] S600: Adjust the first sleeve 6 so that multiple first pressure blocks 7 correspond one-to-one with multiple blade bodies 3, and at the same time adjust the second sleeve 9 so that multiple second pressure blocks 10 correspond one-to-one with multiple blade bodies 3.

[0087] S700: Tighten the first fastener 8 to radially press the first pressure block 7, and at the same time, tighten the second fastener 11 to radially press the second pressure block 10 so that the blade body 3 opens.

[0088] Step S700 also includes S710: inserting the dial indicator 18 into the connecting rod 1 and locking it by tightening the nut.

[0089] S800: The outer circle of the blade body 3 is machined using grinding equipment.

[0090] Specifically, the grinding equipment uses two positioning center holes 102 to achieve two-top clamping, aligns the runout of the connecting rod 1 and the positioning sleeve 4, recalibrates the runout of the dial indicator 18, and then grinds the outer circle of the blade body 3. The reference of the turbine disk 2 can be converted into the reference of the grinding equipment, simplifying the operation steps.

[0091] Step S800 also includes S810: performing quality inspection on the processed blade body 3 by means of the dial indicator 18.

[0092] In this embodiment of the invention, the turbine disk 2 and the first sleeve 6 are firstly fixed to the connecting rod 1 by the positioning sleeve 4, so that multiple first pressure blocks 7 are correspondingly set with multiple blade bodies 3. Additionally, by fitting the second sleeve 9 onto the connecting rod 1, multiple second pressure blocks 10 are correspondingly set with multiple blade bodies 3. Because the first fastener 8 radially presses against the first pressure block 7, and the second fastener 11 radially presses against the second pressure block 10, the blade body 3 is jointly pressed by the first pressure block 7 and the second pressure block 10, thus maintaining a fully open state, allowing ordinary grinding equipment to process the outer diameter of the blade body 3. The blade body 3 of this invention experiences uniform force during grinding, has a stable structure, and achieves high processing accuracy, effectively controlling the processing tolerance of the blade body 3.

[0093] In one embodiment, the gas turbine rotor blade tip grinding method further includes the following steps:

[0094] S900: After machining the outer circle of the blade body 3, loosen the first fastener 8 and the second fastener 11. Disassemble the first sleeve 6, the first pressure block 7, and the positioning sleeve 4.

[0095] Specifically, such as Figure 2 As shown, the first sleeve 6, the first pressing block 7, and the positioning sleeve 4 can serve as the lower module. The remaining parts serve as the upper module, such as... Figure 3 As shown. In this embodiment of the invention, when grinding the blade bodies 3 of other turbine disks 2, only the first sleeve 6, the first pressure block 7, and the positioning sleeve 4 need to be disassembled, without disassembling the upper module. Afterwards, the turbine disk 2 and the blade body 3 are reinstalled, and the positions of the blade body 3, the first pressure block 7, and the second pressure block 10 are recalibrated, so that the subsequent blade bodies 3 can be ground, thus improving the working efficiency of the cyclic processing of the blade bodies 3.

[0096] S1000: Replace the turbine disk 2 with another one, and reinstall the first sleeve 6, the first pressure block 7, and the positioning sleeve 4. Install the unprocessed blade body 3 into the turbine disk 2.

[0097] like Figure 4 As shown, replace the existing upper module with other unprocessed turbine disks 2 and blade bodies 3. Then reinstall the lower module.

[0098] Repeat steps S600 to S800 above.

[0099] After all the blade body 3 has been machined, loosen the first fastener 8 and the second fastener 11, remove the locking piece 5, disassemble the lower module, and finally remove the turbine disk 2 and the blade body 3.

[0100] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A grinding fixture for gas turbine rotor blade tips, characterized in that, include: The connecting rod (1) has a retaining ring (101) in the middle area; A turbine disk (2) is sleeved on the connecting rod (1) and has multiple blade bodies (3). One side of the turbine disk (2) abuts against one side end face of the retaining ring (101). A positioning sleeve (4) is fitted onto the connecting rod (1). One side of the positioning sleeve (4) abuts against the other side of the turbine disk (2), and the other side is locked onto the connecting rod (1) by a locking member (5). The turbine disk (2), the positioning sleeve (4), and the connecting rod (1) are coaxially arranged. The first sleeve (6) is sleeved on the connecting rod (1) and connected to the positioning sleeve (4); Multiple first pressure blocks (7) are arranged one-to-one with multiple blade bodies (3). Each first pressure block (7) is located on the outer end face of the first sleeve (6) by a first fastener (8) and abuts against one side surface of a blade body (3). The second sleeve (9) is sleeved on the connecting rod (1) and fixedly connected to the opposite end face of the retaining ring (101); Multiple second pressure blocks (10) are provided one-to-one with multiple blade bodies (3). Each second pressure block (10) is provided on the outer end face of the second sleeve (9) by a second fastener (11) and abuts against the opposite side surface of one of the blade bodies (3). The first fastener (8) radially presses the first pressure block (7), and the second fastener (11) radially presses the second pressure block (10) to open the blade body (3).

2. The gas turbine rotor blade tip grinding fixture according to claim 1, characterized in that, The outer end face of the first sleeve (6) is provided with a step and forms a first end face (601) and a second end face (602). The first pressure block (7) is fixed to the first end face (601) by the first fastener (8). The second end face (602) is provided with a first baffle (603). The projection of the first baffle (603) in the direction perpendicular to the axis of the first sleeve (6) can cover part or all of the first pressure block (7).

3. The gas turbine rotor blade tip grinding fixture according to claim 1, characterized in that, The first sleeve (6) and the positioning sleeve (4) are fixedly connected by a third fastener (12), and a first adjusting pad (13) is provided between the first sleeve (6) and the positioning sleeve (4).

4. The gas turbine rotor blade tip grinding fixture according to claim 1, characterized in that, It also includes a pressure cap (14), which is sleeved on the connecting rod (1) and fixedly connected to the second sleeve (9) by a fourth fastener (15). The pressure cap (14) also abuts against the second pressure block (10) through a soft gasket (16).

5. The gas turbine rotor blade tip grinding fixture according to claim 4, characterized in that, A second adjusting pad (17) is provided between the pressure cap (14) and the second sleeve (9).

6. The gas turbine rotor blade tip grinding fixture according to claim 4, characterized in that, The outer end face of the pressure cap (14) extends along its axial direction to form a second baffle (1401), the projection of the second baffle (1401) in the direction perpendicular to the axis of the second sleeve (9) can cover part or all of the second pressure block (10).

7. The gas turbine rotor blade tip grinding fixture according to claim 4, characterized in that, It also includes a dial indicator (18), which is sleeved on the connecting rod (1) and spaced apart from the pressure cap (14). The dial indicator (18) is coaxial with the connecting rod (1).

8. The gas turbine rotor blade tip grinding fixture according to any one of claims 1 to 7, characterized in that, The end faces of the two opposite ends of the connecting rod (1) are respectively provided with positioning center holes (102).

9. A method for grinding the tip of a gas turbine rotor blade, characterized in that, Includes the following steps: The turbine disk (2) is sleeved on the connecting rod (1), so that one side of the turbine disk (2) abuts against one end face of the retaining ring (101) of the connecting rod (1), and the other side is connected to the positioning sleeve (4). The positioning sleeve (4) is locked to the connecting rod (1) by the locking member (5). The coaxiality of the turbine disk (2), the connecting rod (1), and the positioning sleeve (4) was calibrated and re-measured; The first pressure block (7) is placed on the outer end face of the first sleeve (6) by the first fastener (8); the first sleeve (6) is sleeved on the connecting rod (1) and connected to the positioning sleeve (4); Multiple blade bodies (3) are installed into the turbine disk (2); The second pressure block (10) is placed on the outer end face of the second sleeve (9) by the second fastener (11); the second sleeve (9) is sleeved on the connecting rod (1) and fixedly connected to the other end face of the retaining ring (101); Adjust the first sleeve (6) so that the plurality of first pressure blocks (7) correspond one-to-one with the plurality of blade bodies (3), and at the same time adjust the second sleeve (9) so that the plurality of second pressure blocks (10) correspond one-to-one with the plurality of blade bodies (3); Tighten the first fastener (8) to radially press the first pressure block (7), and at the same time, tighten the second fastener (11) to radially press the second pressure block (10) so that the blade body (3) opens. The outer circle of the blade body (3) is machined using a grinding machine.

10. The method for grinding gas turbine rotor blade tips according to claim 9, characterized in that, It also includes the following steps: After machining the outer circle of the blade body (3), loosen the first fastener (8) and the second fastener (11); disassemble the first sleeve (6), the first pressure block (7) and the positioning sleeve (4); Replace the turbine disk (2) with another one, and reinstall the first sleeve (6), the first pressure block (7) and the positioning sleeve (4); install the unprocessed blade body (3) into the turbine disk (2); The first sleeve (6) is readjusted so that the plurality of first pressure blocks (7) correspond one-to-one with the plurality of blade bodies (3), and the second sleeve (9) is readjusted so that the plurality of second pressure blocks (10) correspond one-to-one with the plurality of blade bodies (3); Tighten the first fastener (8) to radially press the first pressure block (7), and at the same time, tighten the second fastener (11) to radially press the second pressure block (10) so that the blade body (3) opens. The outer circle of the blade body (3) is machined using a grinding machine.

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