Gas turbine rotor assembly tip shroud

Abstract

The application discloses a gas turbine rotor assembly tip grinding device, which comprises a tip grinding tool and a pressure tool. The tip grinding tool is used for clamping the gas turbine rotor assembly along the axial direction after the first rotor disc and the second rotor disc are penetrated, and the gas turbine rotor assembly is locked by the two ends of the gas turbine rotor assembly during the forced rotation. The tip grinding tool is used for sealingly connecting the outer side end of the first rotor disc, so that the airflow channel for introducing the external pressure gas into the guide hole of the guide disc is formed between the two. The pressure tool is arranged on the two sides of the tip grinding tool, and is used for vertically supporting the tip grinding tool and the gas turbine rotor assembly, so as to press the gas turbine rotor assembly along the axial direction, and then the tip grinding tool further locks the first rotor disc and the second rotor disc along the axial direction. The device greatly improves the working efficiency, improves the tip grinding quality, makes all the blade tip grinding uniform, and avoids the iron filings from entering the gas film hole during the grinding process.

Description

Technical Field

[0001] This invention relates to the field of aero-engine manufacturing technology, and in particular, to a gas turbine rotor assembly blade tip grinding device. Background Technology

[0002] A certain type of engine's gas turbine rotor assembly consists of a first-stage gas turbine rotor and a second-stage gas turbine rotor, such as... Figure 1 As shown, when the engine is running, the central tie rod and the clamping nut are used to tighten the rotor assembly with other rotor components to ensure end tooth meshing.

[0003] When machining individual aero-engine blades, a margin is left at the blade tip. After the blade is assembled with the turbine disk, the entire disk is ground. The common machining method is to use a conventional horizontal grinder (with the workpiece held in place by mandrels at both ends of the equipment) and to grind the first and second stage rotors separately. Grinding has low precision and poor efficiency. Furthermore, during the grinding process, iron filings can easily enter and clog the film gas holes inside the first stage rotor, making subsequent cleaning difficult and thus increasing the risk of engine test failure. Summary of the Invention

[0004] This invention provides a gas turbine rotor assembly blade tip grinding device to solve the technical problems of low grinding accuracy and poor efficiency in existing gas turbine rotor assembly processing methods, the easy entry of iron filings into the internal film pores of the first-stage rotor for blockage, the difficulty of subsequent cleaning operations, and the risk of engine test failure.

[0005] The technical solution adopted in this invention is as follows:

[0006] A gas turbine rotor assembly tip grinding device is provided for axially clamping, pressing, and locking the gas turbine rotor assembly. The gas turbine rotor assembly includes a primary rotor disk and a secondary rotor disk that are axially meshed, and a guide disk mounted on the journal of the primary rotor disk. The tip grinding device includes a tip grinding fixture and a pressing fixture. The tip grinding fixture is used to clamp the gas turbine rotor assembly axially after passing through the center of the primary and secondary rotor disks, and during rotation under force, the two ends of the gas turbine rotor assembly are clamped and locked relative to each other. The tip grinding fixture is also used to seal the outer end of the primary rotor disk to form an airflow channel between them to introduce external pressurized gas into the guide hole on the guide disk. The pressing fixture is separately connected to both sides of the tip grinding fixture to vertically support the tip grinding fixture and the gas turbine rotor assembly, and to press the gas turbine rotor assembly axially, thereby further locking the primary and secondary rotor disks relative to each other axially by the tip grinding fixture.

[0007] Furthermore, the blade tip grinding fixture includes a mandrel for mounting on a blade tip grinding equipment, and a ventilation and pressure-blocking plate assembly and a pressure-locking assembly mounted on the outer circumferences at both ends of the mandrel; the first end face of the mandrel extends concavely to form an air intake channel communicating with the ventilation device on the blade tip grinding equipment, and a first air hole communicating with the air intake channel is also machined on the outer circumference of the first end of the mandrel; the inner end of the ventilation and pressure-blocking plate assembly respectively meshes with the end face teeth of the first stage rotor disk and the outer ring end of the sealing top abutting guide disk, so as to form a sealed air chamber at the outer end of the first stage rotor disk that communicates with the first air hole and the guide hole, and the air chamber, the first air hole and the air intake channel are sequentially connected to form an airflow channel; the pressure-locking assembly is used to tighten the mandrel during rotation, thereby causing the ventilation and pressure-blocking plate assembly and the pressure-locking assembly to clamp and lock the gas turbine rotor assembly axially.

[0008] Furthermore, a flange is provided on the outer circle of the first end of the mandrel, and an external thread is provided on the outer circle of the opposite second end; the outer end of the venting pressure plate assembly abuts against the flange for limitation, and is detachably fixed to the flange by the first fastener; the pressure locking assembly is installed on the outer circle of the mandrel by its internal thread.

[0009] Furthermore, the air chamber includes an inner air chamber located between the journal cavity and the spindle, formed by the end face teeth of the first-stage rotor disk connected by the air pressure plate assembly, and an outer air chamber located between the inner and outer rings of the guide disk, formed by the sealing and locking assembly against the outer ring end of the guide disk; the first air hole communicates with the inner air chamber, the inner air chamber communicates with the outer air chamber through the air holes opened on the journal and the inner ring of the guide disk, and the outer air chamber communicates with the guide hole.

[0010] Furthermore, the inner end of the ventilation pressure plate assembly is recessed to form an inner ring cavity and an outer ring cavity that are coaxially arranged; the inner ring cylinder between the inner ring cavity and the outer ring cavity meshes with the end face teeth of the first-stage rotor disk so that the inner ring cavity is connected to the inner air cavity to form an inner ring air cavity; the outer ring cylinder outside the outer ring cavity seals against the outer ring end of the guide plate so that the outer ring cavity is connected to the outer air cavity to form an outer ring air cavity.

[0011] Furthermore, the ventilation and pressure plate assembly includes a base mounted on the outer circle of the first end of the spindle, and a hollow cylindrical support ring sleeved on the base; the outer end of the base is used to abut against the blade tip grinding equipment for positioning, and its outer end is also detachably fixed to the flange by a first fastener; the inner end of the base is recessed to form an inner annular cavity, and the inner end of the base is also machined with meshing teeth for meshing with the end face teeth of the first stage rotor disk; a second air hole is opened on the side wall of the inner annular cavity; the outer end of the support ring abuts against the inner end of the base for limitation, and is detachably fixed to the base by a second fastener; the inner end of the support ring seals against the outer annular end of the guide plate.

[0012] Furthermore, the pressure locking assembly includes a pressure plate and a locking nut sequentially mounted on the outer circle of the second end of the spindle along the axial direction; the pressure plate is used to press against the outer end of the secondary rotor disc; the locking nut is threadedly connected to the spindle to tighten the spindle during rotation, thereby clamping the gas turbine rotor assembly relative to the ventilated pressure disc assembly and the pressure plate.

[0013] Furthermore, the pressure-pressuring fixture includes a support, a wrench cylinder, and a pressure-pressurizing device; the support is mounted on the outer circle of the first end of the mandrel to vertically support the blade tip grinding fixture and the gas turbine rotor assembly; the wrench cylinder is supported on the top of the gas turbine rotor assembly and covers the pressure-locking assembly, and is connected to the pressure-locking assembly; the pressure-pressurizing device is supported on the top of the wrench cylinder and connected to the mandrel to pull the mandrel upward along the axial direction while pressing the wrench cylinder, thereby causing the wrench cylinder to press down on the gas turbine rotor assembly. The wrench cylinder is also used to rotate the pressure-locking assembly after the pressure-pressurizing device has finished pressing, so as to further lock the first-stage rotor disc and the second-stage rotor disc relative to each other.

[0014] Furthermore, the wrench assembly includes a wrench head detachably connected to the locking nut, a wrench rod detachably connected to the wrench head, and a support sleeve supported on the top of the gas turbine rotor assembly and covering the wrench head; the side wall of the support sleeve has a force-applying cavity for the wrench rod to pass through and apply force; the force-applying end of the wrench rod extends outward after passing through the force-applying cavity, so as to turn the wrench head under the action of external force, thereby causing the wrench head to turn the locking nut.

[0015] Furthermore, the pressure device includes a hydraulic pump supported at the top of the wrench cylinder and a force-applying screw; the force-applying screw passes through the center of the hydraulic pump and is connected to the top of the spindle.

[0016] The present invention has the following beneficial effects:

[0017] In this invention, to improve machining accuracy and efficiency, the machining method for the gas turbine rotor assembly is improved by using a high-speed blade tip grinding device. The two-stage rotors are combined and ground simultaneously in one process, grinding both stages of blade tips. During high-speed blade tip grinding, the main shaft drives the blade tip grinding fixture to rotate at high speed, allowing the loose blades on the gas turbine rotor assembly to obtain sufficiently large centrifugal force. This compensates for the gap between the turbine disk tenon and the blade tenon, and simulates the working state for blade tip grinding and online measurement. This greatly improves work efficiency and blade tip grinding quality, ensuring uniform grinding of all blade tips. Furthermore, the blade tip grinding device of this invention also includes... The pressure-pressuring fixture, by applying pressure to the gas turbine rotor assembly, further tightens the axial meshing of the first-stage and second-stage rotor disks, ensuring proper engagement of their end teeth and thus improving the blade tip grinding quality. Furthermore, the blade tip grinding fixture of this invention also seals the outer end of the first-stage rotor disk, forming an airflow channel between them to introduce pressurized gas into the guide holes on the guide plate. During operation, the pressurized gas enters the guide holes on the guide plate through this airflow channel, then flows into the gap between the tenon groove of the first-stage rotor disk and the tenon of the first-stage blade, and finally exits outward through the film gas holes of the first-stage blade. Figure 2 As shown, this effectively prevents iron filings from entering the film pores during grinding, which would prevent subsequent processes from thoroughly cleaning the pores and causing engine test failure risks.

[0018] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0019] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0020] Figure 1 This is a schematic diagram of the main structure of the gas turbine rotor assembly;

[0021] Figure 2 This is a schematic diagram of the grinding state of the blade tip grinding fixture according to a preferred embodiment of the present invention;

[0022] Figure 3 This is a schematic diagram of the pressurization state of the gas turbine rotor assembly blade tip grinding device according to a preferred embodiment of the present invention;

[0023] Figure 4 yes Figure 3 Schematic diagram of the spatial structure of the locking nut;

[0024] Figure 5 yes Figure 3 A schematic diagram of the spatial structure of a center wrench head.

[0025] Legend

[0026] 1. Gas turbine rotor assembly; 11. First-stage rotor disc; 12. Second-stage rotor disc; 13. Guide disc; 131. Guide hole; 2. Blade tip grinding fixture; 20. Mandrel; 201. Inlet passage; 202. First air hole; 203. Flange; 30. Ventilation and pressure plate assembly; 301. Second air hole; 31. First fastener; 32. Base; 33. Support ring; 34. Second fastener; 35. Sealing ring; 40. Pressure locking assembly; 41. Pressure plate; 42. Locking nut; 421. Slot; 50. Sealing ring; 60. Support; 70. Wrench sleeve; 71. Wrench head; 711. Insert block; 712. Insert hole; 72. Wrench rod; 73. Support sleeve; 731. Force application chamber; 80. Pressure pump; 81. Hydraulic pump; 82. Force application screw. Detailed Implementation

[0027] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0028] Reference Figure 1 and Figure 3 A preferred embodiment of the present invention provides a gas turbine rotor assembly blade tip grinding device for axially clamping, pressing, and locking a gas turbine rotor assembly 1. The gas turbine rotor assembly 1 includes a primary rotor disk 11 and a secondary rotor disk 12 that are axially meshed with each other, and a guide disk 13 mounted on the journal of the primary rotor disk 11. The blade tip grinding device includes a blade tip grinding fixture 2 and a pressing fixture. The blade tip grinding fixture 2 is used to clamp the gas turbine rotor assembly 1 axially after passing through the centers of the primary rotor disk 11 and the secondary rotor disk 12, and rotates under force. The two ends of the gas turbine rotor assembly 1 are clamped and locked together. The blade tip grinding fixture 2 is also used to seal and connect the outer end of the first-stage rotor disk 11 so that an airflow channel is formed between them to introduce external pressurized gas into the guide hole 131 on the guide disk 13. The pressure fixture is connected to both sides of the blade tip grinding fixture 2 to vertically support the blade tip grinding fixture 2 and the gas turbine rotor assembly 1, so as to press the gas turbine rotor assembly 1 along the axial direction, thereby making the blade tip grinding fixture 2 further lock the first-stage rotor disk 11 and the second-stage rotor disk 12 together along the axial direction.

[0029] When the blade tip grinding device of the present invention is in operation, the base portion of the pressure fixture located on the side of the first-stage rotor disk 11 is first placed vertically on the worktable, and then the blade tip grinding fixture 2 and the gas turbine rotor assembly 1 are installed and locked in sequence (i.e. Figure 2(See component status shown); then continue to install and connect the remaining parts of the pressure-pressurizing fixture to the top of the gas turbine rotor assembly 1 and the blade tip grinding fixture 2; next, turn on the pressure-pressurizing fixture to pressurize the gas turbine rotor assembly 1 axially, so that the first-stage rotor disk 11 and the second-stage rotor disk 12 are further meshed tightly; after the pressure is completed, rotate the blade tip grinding fixture 2 to further lock the first-stage rotor disk 11 and the second-stage rotor disk 12 relative to each other axially; then remove the pressure-pressurizing fixture and hoist it. Figure 2 The blade tip grinding equipment is positioned as shown in the diagram. After the blade tip grinding fixture 2 is clamped and positioned on the blade tip grinding equipment, the gas turbine rotor assembly 1 is aligned, and blade tip grinding can then be performed.

[0030] In this invention, to improve processing accuracy and efficiency, the processing method of the gas turbine rotor assembly 1 is improved by using a high-speed blade tip grinding device. The two-stage rotors are combined in one process to simultaneously grind the blade tips of both stages. During high-speed blade tip grinding, the main shaft drives the blade tip grinding fixture 2 to rotate at high speed, thereby allowing the loose blades on the gas turbine rotor assembly 1 to obtain sufficiently large centrifugal force. This compensates for the gap between the turbine disk tenon and the blade tenon, and simulates the working state for blade tip grinding and online measurement. This greatly improves work efficiency and blade tip grinding quality, ensuring uniform grinding of all blade tips. Furthermore, the blade tip grinding device of this invention also includes a pressure-pressing fixture, utilizing a pressure-pressing device... The pressing action of the pressure fixture on the gas turbine rotor assembly 1 allows the first-stage rotor disk 11 and the second-stage rotor disk 12 to mesh more tightly along the axial direction, ensuring that the end teeth of both are properly engaged, thereby further improving the blade tip grinding quality. On the other hand, the blade tip grinding fixture 2 of the present invention also seals the outer end of the first-stage rotor disk 11, thereby forming an airflow channel between them to introduce external pressurized gas into the guide holes on the guide disk 13. During operation, the pressurized gas enters the guide holes 131 on the guide disk 13 through this airflow channel, and then enters the gap between the tenon groove of the first-stage rotor disk 11 and the tenon of the first-stage blade through the guide holes 131, and finally is blown outward through the film gas holes of the first-stage blade. Figure 2 As shown, this effectively prevents iron filings from entering the film pores during grinding, which would prevent subsequent processes from thoroughly cleaning the pores and causing engine test failure risks.

[0031] Optionally, such as Figure 2As shown, the blade tip grinding fixture 2 includes a mandrel 20 for mounting on a blade tip grinding machine, and a ventilation and pressure plate assembly 30 and a pressure locking assembly 40 mounted on the outer circumferences at both ends of the mandrel 20. The first end face of the mandrel 20 extends concavely to form an air intake channel 201 communicating with the ventilation device on the blade tip grinding machine. A first air hole 202 communicating with the air intake channel 201 is also machined on the outer circumference of the first end of the mandrel 20. The inner end of the ventilation and pressure plate assembly 30 respectively engages with the end face teeth of the first stage rotor disk 11 and the outer ring end of the sealing top guide disk 13 to form a sealed air chamber at the outer end of the first stage rotor disk 11 that communicates with the first air hole 202 and the guide hole 131. The air chamber, the first air hole 202 and the air intake channel 201 are sequentially connected to form an airflow channel. The pressure locking assembly 40 is used to tighten the spindle 20 during rotation, thereby causing the ventilation pressure plate assembly 30 and the pressure locking assembly 40 to clamp and lock the gas turbine rotor assembly 1 axially.

[0032] In this invention, to improve machining accuracy and efficiency, the machining method of the gas turbine rotor assembly 1 is improved by using a high-speed blade tip grinding machine. Furthermore, the two-stage rotors are combined in a single process to simultaneously grind the blade tips of both stages. During high-speed blade tip grinding, the main shaft drives the mandrel 20 to rotate at high speed, thereby allowing the loose blades on the gas turbine rotor assembly 1 to obtain sufficiently large centrifugal force. This effectively cancels the gap between the turbine disk tenon and the blade tenon. Simulated working conditions are used for blade tip grinding and online measurement, greatly improving both work efficiency and blade tip grinding quality. The blade tips are ground evenly. On the other hand, in the blade tip grinding device of the present invention, the mandrel 20 is machined with an air intake channel 201 communicating with the ventilation device. During operation, pressurized gas first enters the air intake channel 201, then enters the air cavity formed by the ventilation pressure plate assembly 30 and the outer end of the first-stage rotor disk 11 through the first air hole 202, then enters the guide hole 131 on the guide plate 13 through the air cavity, then enters the gap between the tenon groove of the first-stage rotor disk 11 and the tenon of the first-stage blade through the guide hole 131, and finally is blown outward through the air film hole of the first-stage blade. Figure 2 As shown, this avoids the problem of iron filings entering the film pores during grinding, which would prevent subsequent processes from thoroughly cleaning the pores and causing engine test failure risks.

[0033] Optionally, such as Figure 2As shown, the outer circumference of the first end of the spindle 20 is provided with a flange 203, and the outer circumference of the opposite second end is provided with an external thread. The outer end of the ventilation pressure plate assembly 30 is limited by the flange 203 and is detachably fixed to the flange 203 by the first fastener 31. The pressure locking assembly 40 is threaded onto the outer circumference of the spindle 20 by its internal thread; when clamping, rotating the pressure locking assembly 40 can tighten the spindle 20 axially, and the spindle 20 drives the ventilation pressure plate assembly 30 to press against the outer end of the first stage rotor disk 11, while the pressure locking assembly 40 presses against the outer end of the second stage rotor disk 12. Thus, through the tooling of the present invention, the gas turbine rotor assembly 1 can be tightened axially, which is simple to operate and reliable in tightening.

[0034] In this optional solution, such as Figure 2 As shown, the air chamber includes an inner air chamber formed by the end face teeth of the first-stage rotor disk 11 connected by the venting and pressure-resistant plate assembly 30, located between the journal cavity and the spindle 20, and an outer air chamber formed by the pressure-locking assembly sealing against the outer ring end of the guide disk 13, located between the inner and outer rings of the guide disk 13. The first air hole 202 communicates with the inner air chamber, and the inner air chamber communicates with the outer air chamber through air holes opened on the journal and the inner ring of the guide disk 13. The outer air chamber communicates with the guide hole 131. During operation, pressurized gas first enters the intake channel 201, then enters the inner air chamber between the journal cavity and the spindle 20 through the first air hole 202, then enters the outer air chamber between the inner and outer rings of the guide disk 13 through air holes opened on the journal and the inner ring of the guide disk 13, then enters the guide hole 131 on the guide disk, then enters the gap between the tenon groove of the first-stage rotor disk 11 and the tenon of the first-stage blade through the guide hole 131, and finally is blown outward through the air film holes of the first-stage blade.

[0035] Preferably, such as Figure 2 As shown, the inner end of the ventilated pressure plate assembly 30 is recessed to form an inner annular cavity and an outer annular cavity coaxially arranged. The inner annular cylinder between the inner and outer annular cavities meshes with the end face teeth of the first-stage rotor disk 11, so that the inner annular cavity connects to the inner air cavity to form an inner annular air cavity. The outer annular cylinder outside the outer annular cavity seals against the outer annular end of the guide disk 13, so that the outer annular cavity connects to the outer air cavity to form an outer annular air cavity. In this preferred embodiment, through the structural arrangement of the ventilated pressure plate assembly 30, the original inner air cavity connects to the inner annular cavity to form an inner annular air cavity with a larger cavity area, and the original outer air cavity connects to the outer annular cavity to form an outer annular air cavity with a larger cavity area, thereby increasing the flow rate of pressurized gas and improving the blowing effect on the gas film orifice.

[0036] Furthermore, such as Figure 2As shown, the outer circumference of the first end of the mandrel 20 is provided with multiple sets of air holes arranged sequentially along the axial direction. Each set of air holes includes a first air hole 202 arranged at intervals along the circumference of the mandrel 20 and perpendicularly connected to the air intake channel 201. The first air hole 202 is connected to the inner annular air chamber. A second air hole 301 connecting the inner annular air chamber and the outer annular air chamber is also provided on the side wall of the inner annular cylinder. In this further embodiment, by setting multiple sets of air holes and the second air hole 301, the flow rate requirement of the air chamber after the area is increased is met, the blowing effect of the air film orifice is further improved, and the blockage of the air film orifice is effectively prevented.

[0037] In specific embodiments of this optional solution, such as Figure 2 As shown, the ventilated pressure plate assembly 30 includes a base 32 mounted on the outer circumference of the first end of the spindle 20. The outer end of the base 32 is used for positioning against the blade tip grinding equipment, and its outer end is also detachably fixed to the flange 203 by a first fastener 31. The inner end of the base 32 is recessed to form an inner annular cavity, and the inner end of the base 32 is also machined with meshing teeth for external engagement with the end face teeth of the first-stage rotor disk 11. The base 32 engages with the end face teeth of the first-stage rotor disk 11 through its meshing teeth, which serves the purpose of connection and pressure application, while protecting the end face teeth on the first-stage rotor disk 11, and improving the effect of the base 32 in applying force to the first-stage rotor disk 11. A second air hole 301 is provided on the side wall of the inner annular cavity; the base 32 has a simple structure and is easy to manufacture.

[0038] Furthermore, such as Figure 2 As shown, the ventilated pressure plate assembly 30 also includes a hollow cylindrical support ring 33 sleeved on the base 32. The outer end of the support ring 33 abuts against the inner end of the base 32 for limitation, and is detachably fixed to the base 32 by a second fastener 34. The inner end of the support ring 33 seals against the outer ring end of the guide plate 13. The support ring 33 has a simple structure and is easy to manufacture. Furthermore, by separating the ventilated pressure plate assembly 30 into the base 32 and the support ring 33, the overall structure of the ventilated pressure plate assembly 30 is simple, easy to manufacture, and convenient to assemble and disassemble.

[0039] Preferably, such as Figure 2 As shown, the ventilation and pressure plate assembly 30 also includes a sealing ring 35 mounted on the outer circumference of the spindle 20. The inner end of the support ring 33 is recessed to form a mounting cavity, and the outer end of the sealing ring 35 is clamped in the mounting cavity. The inner end of the sealing ring 35 seals against the outer ring end of the guide plate 13. In order to improve the blowing effect of the air film orifice and prevent pressurized gas from leaking through the gap between the support ring 33 and the outer ring end of the guide plate 13, and at the same time to prevent the support ring 33 from damaging the guide plate 13, a sealing ring 35 is provided between the support ring 33 and the guide plate 13.

[0040] Preferably, such as Figure 2As shown, the blade tip grinding device also includes a sealing ring 50 installed on the outer circle of the mandrel 20. The sealing ring 50 is pressed between the outer circle of the mandrel 20 and the inner ring cavity of the first-stage rotor disk 11. Similarly, in order to improve the blowing effect of the air film hole and prevent pressurized gas from leaking between the outer circle of the mandrel 20 and the inner ring cavity of the first-stage rotor disk 11, in a preferred embodiment of the present invention, a sealing ring 50 for sealing is also provided between the outer circle surface of the mandrel 20 and the inner ring cavity of the first-stage rotor disk 11.

[0041] Optionally, such as Figure 2 As shown, the pressure locking assembly 40 includes a pressure plate 41 and a locking nut 42 sequentially mounted axially on the outer circle of the second end of the spindle 20. The pressure plate 41 is used to press against the outer end of the secondary rotor disk 12. The locking nut 42 is threadedly connected to the spindle 20 to tighten the spindle 20 during rotation, thereby clamping the gas turbine rotor assembly 1 between the ventilation pressure disk assembly 30 and the pressure plate 41. During installation, the locking nut 42 is first tightened to tighten the spindle 20 axially, causing the ventilation pressure disk assembly 30 and the pressure plate 41 to clamp the gas turbine rotor assembly 1 between them. Then, the locking nut 42 is tightened. Next, pressure is applied to the pressure plate 41 using a pressure application device to make the end teeth of the primary rotor disk 11 and the secondary rotor disk 12 mesh together. Finally, the locking nut 42 is tightened again. Preferably, to improve the locking effect of the gas turbine rotor assembly 1, multiple sets of locking nuts 42 can be provided simultaneously.

[0042] Optionally, such as Figure 3 As shown, the pressing fixture includes a support 60, a wrench cylinder 70, and a pressurizer 80. The support 60 is mounted on the outer circle of the first end of the mandrel 20 to vertically support the blade tip grinding fixture 2 and the gas turbine rotor assembly 1. The wrench cylinder 70 is supported on the top of the gas turbine rotor assembly 1 and covers the pressing and locking assembly 40, and is connected to the pressing and locking assembly 40. The pressurizer 80 is supported on the top of the wrench cylinder 70 and connected to the mandrel 20, to pull the mandrel 20 upward along the axial direction while pressing the wrench cylinder 70, thereby causing the wrench cylinder 70 to press down on the gas turbine rotor assembly 1. The wrench cylinder 70 is also used to rotate the pressing and locking assembly 40 after the pressurizer 80 has finished pressing, to further lock the first-stage rotor disk 11 and the second-stage rotor disk 12 relative to each other. During clamping, the support 60 is first placed vertically on the worktable, and then the blade tip grinding fixture 2 and the gas turbine rotor assembly 1 are installed in sequence (i.e., Figure 2 (As shown in the component status), and tighten the locking nut 42. Then, continue installing the wrench cylinder 70 and the pressure pump 80. Then, turn on the pressure pump 80 to pressurize the gas turbine rotor assembly 1 according to the pressure required by the process document. After the pressure is reached, apply force to the wrench cylinder 70 to turn the locking nut 42 to further lock the first-stage rotor disk 11 and the second-stage rotor disk 12 relative to each other, completing the clamping of the parts. Finally, remove the pressure pump fixture and hoist the assembly. Figure 2When the gas turbine rotor assembly 1 is pressed by the pressure-pressing fixture on the machine tool of the blade tip grinding equipment as shown, its primary rotor disk 11 and secondary rotor disk 12 are further meshed tightly in the axial direction to ensure that the end teeth of the two are meshed in place, thereby further improving the blade tip grinding quality.

[0043] In this optional solution, such as Figure 3 As shown, the wrench cylinder 70 includes a wrench head 71 detachably connected to the locking nut 42, a wrench lever 72 detachably connected to the wrench head 71, and a support sleeve 73 supported on the top of the gas turbine rotor assembly 1 and covering the wrench head 71. A force-applying cavity 731 is provided on the side wall of the support sleeve 73 for the wrench lever 72 to pass through and apply force. The force-applying end of the wrench lever 72 extends outward after passing through the force-applying cavity 731 to turn the wrench head 71 under external force, thereby causing the wrench head 71 to turn the locking nut 42. During operation, after the gas turbine rotor assembly 1 is pressurized, the force-applying lever 72 is applied, causing it to rotate the wrench head 71, which in turn drives the locking nut 42 to rotate, further tightening the gas turbine rotor assembly 1.

[0044] In specific embodiments of this optional solution, such as Figure 4 As shown, the outer circumference of the locking nut 42 is machined with slots 421 arranged at intervals along the circumference, and each slot 421 connects to both ends of the locking nut 42 axially. Figure 5 As shown, the wrench head 71 is a hollow cylindrical shape, with a protruding insert 711 at its bottom end that corresponds to the slot 421. The upper outer circumference of the wrench head has circumferentially spaced insertion holes 712 that penetrate the wall. During installation, the insert 711 of the wrench head 71 is inserted into the slot 421 of the locking nut 42, thus connecting the wrench head 71 to the locking nut 42. Then, the connecting end of the lever 72 is inserted into the insertion hole 712 of the wrench head 71, connecting the lever 72 to the wrench head 71. Furthermore, when tightening the locking nut 42, the lever 72 can switch between different insertion holes 712 to avoid interference when tightening the locking nut 42 through the force application chamber 731 of the support sleeve 73.

[0045] In this optional solution, such as Figure 3 As shown, the pressure device 80 includes a hydraulic pump 81 supported at the top of the wrench cylinder 70 and a force-applying screw 82; the force-applying screw passes through the center of the hydraulic pump 81 and connects to the top of the mandrel. In this optional embodiment, the hydraulic pump 81 includes a piston and a cylinder with inner and outer sleeves, and the force-applying screw 82 passes through the center of the piston and connects to the piston. During operation, oil enters the piston chamber, which causes the piston to drive the force-applying screw 82 to pull the mandrel 20 upward axially, while the cylinder presses down on the wrench cylinder 70, causing the wrench cylinder 70 to press down on the gas turbine rotor assembly 1 axially.

[0046] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A gas turbine rotor assembly blade tip grinding device, characterized in that, The gas turbine rotor assembly (1) is used for clamping, pressing and locking along the axial direction. The gas turbine rotor assembly (1) includes a primary rotor disk (11) and a secondary rotor disk (12) that are meshed together along the axial direction, and a guide disk (13) mounted on the journal of the primary rotor disk (11). The blade tip grinding device includes a blade tip grinding fixture (2) and a pressing fixture. The blade tip grinding fixture (2) is used to pass through the center of the first-stage rotor disk (11) and the second-stage rotor disk (12) and clamp the gas turbine rotor assembly (1) axially. During the rotation under force, the two ends of the gas turbine rotor assembly (1) are clamped and locked. The blade tip grinding fixture (2) is also used to seal the outer end of the first-stage rotor disk (11) so that an airflow channel is formed between the two to introduce external pressurized gas into the guide hole (131) on the guide disk (13). The pressure-pressing fixtures are connected to both sides of the blade tip grinding fixture (2) to vertically support the blade tip grinding fixture (2) and the gas turbine rotor assembly (1) to press the gas turbine rotor assembly (1) along the axial direction, thereby making the blade tip grinding fixture (2) further lock the first-stage rotor disk (11) and the second-stage rotor disk (12) relative to each other along the axial direction. The blade tip grinding fixture (2) includes a mandrel (20) for mounting on a blade tip grinding equipment, and a ventilation and pressure plate assembly (30) and a pressure locking assembly (40) mounted on the outer circles of both ends of the mandrel (20); the first end face of the mandrel (20) extends inward to form an air intake channel (201) communicating with the ventilation device on the blade tip grinding equipment, and a first air hole (202) communicating with the air intake channel (201) is also machined on the outer circle of the first end of the mandrel (20); the inner ends of the ventilation and pressure plate assembly (30) are respectively engaged with the first stage rotor disk (11) The end face teeth of the sealing top abutting the outer ring end of the guide plate (13) are used to form a sealed air chamber at the outer end of the first stage rotor disk (11) and connecting the first air hole (202) and the guide hole (131), and the air chamber, the first air hole (202) and the air inlet channel (201) are connected in sequence to form an airflow channel; the pressure locking assembly (40) is used to tighten the spindle (20) during rotation, thereby making the ventilation pressure plate assembly (30) and the pressure locking assembly (40) clamp and lock the gas turbine rotor assembly (1) axially relative to each other. The air chamber includes an inner air chamber formed by the end face teeth of the first-stage rotor disk (11) connected by the venting pressure plate assembly (30) and located between the journal cavity and the spindle (20), and an outer air chamber formed by the venting pressure plate assembly (30) sealing against the outer ring end of the guide disk (13) and located between the inner and outer rings of the guide disk (13); the first air hole (202) communicates with the inner air chamber, the inner air chamber communicates with the outer air chamber through the air holes opened on the journal and the inner ring of the guide disk (13), and the outer air chamber communicates with the guide hole (131). The inner end of the ventilation pressure plate assembly (30) is recessed to form an inner ring cavity and an outer ring cavity that are coaxially arranged; the inner ring cylinder between the inner ring cavity and the outer ring cavity meshes with the end face teeth of the first-stage rotor disk (11) so that the inner ring cavity is connected to the inner air cavity to form an inner ring air cavity; the outer ring cylinder outside the outer ring cavity is sealed against the outer ring end of the guide plate (13) so that the outer ring cavity is connected to the outer air cavity to form an outer ring air cavity; The ventilation pressure plate assembly (30) includes a base (32) mounted on the outer circle of the first end of the spindle (20) and a hollow cylindrical support ring (33) sleeved on the base (32). The outer end of the base (32) is used to abut against the blade tip grinding equipment for positioning, and its outer end is also detachably fixed to the flange (203) by the first fastener (31). The inner end of the base (32) is recessed to form an inner ring cavity, and the inner end of the base (32) is also machined with meshing teeth for meshing with the end face teeth of the first stage rotor disk (11). A second air hole (301) is opened on the side wall of the inner ring cavity. The outer end of the support ring (33) abuts against the inner end of the base (32) for limiting, and is detachably fixed to the base (32) by the second fastener (34). The inner end of the support ring (33) seals against the outer ring end of the guide plate (13).

2. The gas turbine rotor assembly tip grinding device according to claim 1, characterized in that, The outer circle of the first end of the mandrel (20) is also provided with a flange (203), and the outer circle of the opposite second end is also provided with an external thread; The outer end of the ventilation pressure plate assembly (30) is limited by the flange (203) and is detachably fixed to the flange (203) by the first fastener (31); The pressure locking assembly (40) is threaded onto the outer circle of the spindle (20) via its internal thread.

3. The gas turbine rotor assembly tip grinding device according to claim 1, characterized in that, The pressure locking assembly (40) includes a pressure plate (41) and a locking nut (42) that are sequentially mounted on the outer circle of the second end of the spindle (20) along the axial direction. The pressure plate (41) is used to press against the outer end of the secondary rotor disk (12); The locking nut (42) is threaded to the spindle (20) to tighten the spindle (20) during rotation, thereby clamping the gas turbine rotor assembly (1) relative to the ventilation pressure plate assembly (30) and the pressure plate (41).

4. The gas turbine rotor assembly tip grinding device according to claim 3, characterized in that, The pressure-pressing fixture includes a support (60), a wrench sleeve (70), and a pressure press (80). The support (60) is mounted on the outer circle of the first end of the spindle (20) to vertically support the blade tip grinding fixture (2) and the gas turbine rotor assembly (1). The wrench cylinder (70) is supported on the top of the gas turbine rotor assembly (1) and covers the pressure locking assembly (40), and is connected to the pressure locking assembly (40). The pressure device (80) is supported on the top of the wrench cylinder (70) and connected to the mandrel (20) for pulling the mandrel (20) upward along the axial direction while pressing the wrench cylinder (70), thereby causing the wrench cylinder (70) to press down on the gas turbine rotor assembly (1). The wrench cylinder (70) is also used to turn the locking assembly (40) after the pressure device (80) has finished pressing, so as to further lock the first-stage rotor disk (11) and the second-stage rotor disk (12) relative to each other.

5. The gas turbine rotor assembly tip grinding device according to claim 4, characterized in that, The wrench assembly (70) includes a wrench head (71) with a detachable locking nut (42), a wrench bar (72) with a detachable wrench head (71), and a support sleeve (73) that is supported on the top of the gas turbine rotor assembly (1) and covers the wrench head (71). The side wall of the support sleeve (73) is provided with a force application cavity (731) for the lever (72) to pass through and apply force. The force-applying end of the lever (72) extends outward after passing through the force-applying cavity (731) to turn the wrench head (71) under the action of external force, thereby causing the wrench head (71) to turn the lock nut (42).

6. The gas turbine rotor assembly tip grinding device according to claim 4, characterized in that, The pressure device (80) includes a hydraulic pump (81) mounted on the top of the wrench cylinder (70) and a force-applying screw; The force-applying screw passes through the center of the hydraulic pump (81) and then connects to the top of the mandrel.

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