Gas turbine rotor assembly blade tip grinding tooling

Abstract

This invention discloses a blade tip grinding fixture for a gas turbine rotor assembly, comprising: a mandrel, a ventilated pressure plate assembly mounted on the outer circumference of the first end of the mandrel, and a pressure locking assembly threaded onto the outer circumference of the second end of the mandrel. The end face of the first end of the mandrel extends concavely to form an air intake channel, 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 ventilated pressure plate assembly meshes with the end face teeth of the first-stage rotor disk and the outer ring end of the sealing top guide disk, forming a sealed air chamber at the outer end of the first-stage rotor disk that connects the first air hole and the guide hole on the guide disk. The pressure locking assembly is used to tighten the mandrel during rotation, thereby clamping and locking the gas turbine rotor assembly axially relative to the ventilated pressure plate assembly and the pressure locking assembly. This invention significantly improves working efficiency while also improving the blade tip grinding quality, ensuring uniform grinding of all blade tips and preventing iron filings from entering the film gas pores during grinding.

Description

Technical Field

[0001] This invention relates to the field of aero-engine manufacturing technology, and in particular, to a tooling for grinding the blade tips of a gas turbine rotor assembly. 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 grinding fixture for the blade tips of a gas turbine rotor assembly to solve the technical problems of low grinding accuracy and poor efficiency in existing processing methods for gas turbine rotor assemblies, easy entry of iron filings into the internal film pores of the first-stage rotor for blockage, difficult subsequent cleaning operations, and easy risk of engine test failure.

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

[0006] A gas turbine rotor assembly blade tip grinding fixture is used to clamp a primary rotor disk and a secondary rotor disk axially, and to lock the primary rotor disk, a guide disk mounted on the primary rotor disk journal, and the secondary rotor disk to form a gas turbine rotor assembly. The blade tip grinding fixture includes: a mandrel for mounting on a blade tip grinding device; a venting pressure plate assembly mounted on the outer circle of the first end of the mandrel and used to abut against the outer end of the primary rotor disk; and a pressure locking assembly threaded on the outer circle of the second end of the mandrel and used to abut against the outer end of the secondary rotor disk; the first end face of the mandrel extends concavely. An air intake channel is formed that communicates with the ventilation device on the blade tip mill. A first air hole communicating with the air intake channel is also machined on the outer circle of the first end of the spindle. The inner end of the ventilation pressure plate assembly meshes with the end face teeth of the first stage rotor disk and the outer ring end of the sealing top guide disk 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 on the guide disk. The pressure locking assembly is used to tighten the spindle during rotation, thereby clamping and locking the gas turbine rotor assembly axially relative to each other.

[0007] 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.

[0008] 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.

[0009] 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.

[0010] Furthermore, the outer circle of the first end of the mandrel is provided with multiple sets of air holes arranged sequentially along the axial direction. Each set of air holes includes a first air hole arranged sequentially at intervals along the circumference of the mandrel and vertically connected to the air intake channel. The first air hole is connected to the inner ring air chamber. A second air hole is also provided on the side wall of the inner ring cylinder, connecting the inner ring air chamber and the outer ring air chamber.

[0011] Furthermore, the ventilation and pressure plate assembly includes a base mounted on the outer circle of the first end of the spindle; 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.

[0012] Furthermore, the ventilation pressure plate assembly also includes a hollow cylindrical support ring sleeved outside the base; 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 ring end of the guide plate.

[0013] Furthermore, the ventilation pressure plate assembly also includes a sealing ring mounted on the outer circle of the spindle; the inner end of the support ring is recessed to form an installation cavity, the outer end of the sealing ring is clamped in the installation cavity, and the inner end of the sealing ring seals against the outer ring end of the guide plate.

[0014] Furthermore, the blade tip grinding fixture also includes a sealing ring installed on the outer circle of the mandrel, which is pressed between the outer circle of the mandrel and the inner annular cavity of the first-stage rotor disc.

[0015] 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.

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

[0017] In this invention, to improve processing accuracy and efficiency, the processing method of the gas turbine rotor assembly is improved by using a high-speed blade tip grinding machine. The two-stage rotor assembly is combined and the blade tips of both stages are ground simultaneously in one process. During high-speed blade tip grinding, the main shaft drives the mandrel to rotate at high speed, allowing the loose blades on the gas turbine rotor assembly to obtain sufficient centrifugal force, thereby canceling 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 work efficiency and blade tip grinding quality, ensuring uniform grinding of all blade tips. On the other hand, in the blade tip grinding fixture of this invention, the mandrel is machined with an air intake channel connected to the ventilation device. During operation, pressurized gas first enters the air intake channel, then enters the air cavity formed by the ventilation pressure plate assembly and the outer end of the first-stage rotor disk through the first air hole, then enters the guide hole on the guide plate, then enters the gap between the tenon of the first-stage rotor disk and the tenon of the first-stage blade through the guide hole, and finally is blown outward through the film gas 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.

[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 of the gas turbine rotor assembly according to a preferred embodiment of the present invention.

[0022] Legend

[0023] 11. Primary rotor disc; 12. Secondary rotor disc; 13. Guide disc; 131. Guide hole; 20. Mandrel; 201. Inlet channel; 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; 50. Sealing ring. Detailed Implementation

[0024] 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.

[0025] Reference Figure 1-2 A preferred embodiment of the present invention provides a gas turbine rotor assembly blade tip grinding fixture for axially clamping a primary rotor disk 11 and a secondary rotor disk 12, and locking the primary rotor disk 11, the guide disk 13 mounted on the journal of the primary rotor disk 11, and the secondary rotor disk 12 to form a gas turbine rotor assembly. The blade tip grinding fixture includes: a mandrel 20 for mounting on a blade tip grinding device; a ventilation and pressure plate assembly 30 mounted on the outer circle of the first end of the mandrel 20 and used to abut against the outer end of the primary rotor disk 11; and a pressure locking assembly 40 threadedly mounted on the outer circle of the second end of the mandrel 20 and used to abut against the outer end of the secondary rotor disk 12. The end face of the first end of the mandrel 20 extends concavely to form an air intake channel 201 communicating with the ventilation device on the blade tip grinding device. 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 pressure plate assembly 30 respectively engage with the end face teeth of the first-stage rotor disk 11 and the outer ring end of the sealing top abutment guide disk 13, so as to form a sealed air chamber at the outer end of the first-stage rotor disk 11, which connects the first air hole 202 and the guide hole 131 on the guide disk 13. The pressure locking assembly 40 is used to tighten the spindle 20 during rotation, thereby clamping and locking the gas turbine rotor assembly axially relative to the ventilation pressure plate assembly 30 and the pressure locking assembly 40.

[0026] When the blade tip grinding fixture of the present invention is in operation, firstly, the mandrel 20 and the ventilation pressure plate assembly 30 are clamped with the first-stage rotor disk 11, the second-stage rotor disk 12, and the guide disk 13; then, the pressure locking assembly 40 is clamped and tightened; next, pressure is applied to the pressure locking assembly 40 using a pressure application device to ensure that the inner end teeth of the first-stage rotor disk 11 and the second-stage rotor disk 12 mesh tightly; finally, the pressure locking assembly 40 is retightened to complete the clamping of the gas turbine rotor assembly, as shown below. Figure 2 As shown; finally, the assembled gas turbine rotor assembly and tooling are clamped together onto the blade tip grinding equipment. After the tooling is clamped and positioned on the blade tip grinding equipment, the gas turbine rotor assembly is aligned and the blade tip grinding can be performed.

[0027] 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 machine. Furthermore, the two-stage rotor assembly is combined and both blade tips are ground simultaneously in a single process. 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 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, ensuring that all... The blade tip is ground evenly; on the other hand, in the blade tip grinding fixture of the present invention, the mandrel 20 is machined with an air intake channel 201 that communicates with the ventilation device. During operation, pressurized gas first enters the air intake channel 201, and 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. Next, it enters the guide hole 131 on the guide plate 13 through the air cavity, 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 hole 131. Finally, it 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.

[0028] Optionally, such as Figure 2 As shown, a flange 203 is provided on the outer circle of the first end of the spindle 20, and an external thread is provided on the outer circle of the opposite second end. 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 through 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 can be tightened axially, which is simple to operate and reliable in tightening.

[0029] In this optional solution, such as Figure 2As 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.

[0030] 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.

[0031] Furthermore, such as Figure 2 As 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.

[0032] In specific embodiments of this optional solution, such as Figure 2As 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.

[0033] 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.

[0034] 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.

[0035] Preferably, such as Figure 2 As shown, the blade tip grinding fixture 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 orifice 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 is also provided between the outer circle surface of the mandrel 20 and the inner ring cavity of the first-stage rotor disk 11 to perform a sealing function.

[0036] Optionally, such as Figure 2As 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 relative to the ventilation pressure disk assembly 30 and the pressure plate 41. During installation, the locking nut 42 is first tightened, thereby tightening the spindle 20 axially. The spindle 20 clamps the gas turbine rotor assembly relative to the ventilation pressure disk assembly 30 and the pressure plate 41. Then the locking nut 42 is tightened. Next, pressure is applied to the pressure plate 41 using a pressure application device, causing the end teeth of the primary rotor disk 11 and the secondary rotor disk 12 to mesh together. Finally, the locking nut 42 is tightened again. Preferably, to improve the locking effect of the gas turbine rotor assembly, multiple sets of locking nuts 42 can be provided simultaneously.

[0037] 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 tooling for grinding the blade tips of a gas turbine rotor assembly, characterized in that, The blade tip grinding fixture is used to clamp the first-stage rotor disk (11) and the second-stage rotor disk (12) along the axial direction, and to lock the first-stage rotor disk (11), the guide disk (13) mounted on the journal of the first-stage rotor disk (11), and the second-stage rotor disk (12) to form a gas turbine rotor assembly. The mandrel (20) is installed on the blade tip milling equipment, the ventilation pressure plate assembly (30) is installed on the outer circle of the first end of the mandrel (20) and is used to abut against the outer end of the first stage rotor disk (11), and the pressure locking assembly (40) is threaded on the outer circle of the second end of the mandrel (20) and is used to abut against the outer end of the second stage rotor disk (12). The first end face of the mandrel (20) extends inward to form an air intake channel (201) that communicates with the air intake device on the blade tip grinding equipment. The outer circle of the first end of the mandrel (20) is also machined with a first air hole (202) that communicates with the air intake channel (201). The inner end of the ventilation pressure plate assembly (30) respectively meshes with the end face teeth of the first stage rotor disk (11) and the outer ring end of the sealing top guide plate (13) 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) on the guide plate (13); The pressure locking assembly (40) is used to tighten the spindle (20) during rotation, thereby clamping and locking the gas turbine rotor assembly axially relative to the ventilation pressure plate assembly (30) and the pressure locking assembly (40); A flange (203) is also provided on the outer circle of the first end of the mandrel (20); The air chamber includes an inner air chamber located between the journal cavity and the spindle (20) formed by the end face teeth of the first-stage rotor disk (11) connected by the ventilated pressure plate assembly (30), and an outer air chamber located between the inner and outer rings of the guide disk (13) formed by the ventilated pressure plate assembly (30) sealing and abutting against the outer ring end of the guide disk (13). The first air hole (202) is connected to the inner air cavity. The inner air cavity is connected to the outer air cavity through the air hole opened on the inner ring of the journal and the guide plate (13). The outer air cavity is connected to 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); 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.

2. The gas turbine rotor assembly blade tip grinding fixture according to claim 1, characterized in that, The outer circle of the second end opposite to the mandrel (20) 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 blade tip grinding fixture according to claim 2, characterized in that, The outer circle 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 sequentially at intervals along the circumference of the mandrel (20) and vertically connected to the air intake channel (201). The first air hole (202) is connected to the inner ring air chamber. A second air hole (301) is also provided on the side wall of the inner ring cylinder to connect the inner ring air chamber and the outer ring air chamber.

4. The gas turbine rotor assembly blade tip grinding fixture according to claim 2, characterized in that, The ventilation pressure plate assembly (30) also includes a hollow cylindrical support ring (33) that is sleeved outside the base (32). The outer end of the support ring (33) is limited against the inner end of the base (32) and is detachably fixed to the base (32) by the second fastener (34); The inner end of the support ring (33) is sealed against the outer ring end of the guide plate (13).

5. The gas turbine rotor assembly blade tip grinding fixture according to claim 4, characterized in that, The ventilation pressure plate assembly (30) also includes a sealing ring (35) mounted on the outer circle of the spindle (20); The inner end of the support ring (33) is recessed to form an installation cavity, and the outer end of the sealing ring (35) is clamped in the installation cavity. The inner end of the sealing ring (35) seals against the outer ring end of the guide plate (13).

6. The gas turbine rotor assembly blade tip grinding fixture according to claim 1, characterized in that, The blade tip grinding fixture also includes a sealing ring (50) installed on the outer circle of the mandrel (20), and 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).

7. The gas turbine rotor assembly blade tip grinding fixture 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 relative to each other between the ventilation pressure plate assembly (30) and the pressure plate (41).

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