A fixture for a turbine rotor to improve its processing and measuring stability and a method of using the same

Abstract

The application discloses a kind of clamps for improving the processing and measurement stability of turbine rotor, including top pin in turbine disc mortise vent hole, force component connected with top pin, and support component for installing force component;Force component is obliquely arranged on support component, and the two are connected by thread connection.It also discloses a kind of clamp for improving the processing and measurement stability of turbine rotor, and the steps include: determining the simulation principle of aero-engine, lifting the blade, making the blade tenon and disc mortise top tightly without gap;Top pin is installed in turbine disc mortise vent hole;Using screw thread transmission principle, force is applied to top pin by screw, and force is transmitted to turbine blade tenon, blade is lifted, and turbine rotor simulation working state is realized.Processing and measurement of turbine rotor outer diameter are carried out by installing the clamp and method, simulate the working condition of engine turbine rotor blade being thrown away by centrifugal force when working, to improve the stability of turbine rotor.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine manufacturing technology, specifically relating to a fixture for improving the processing and measurement stability of a turbine rotor and its usage method. Background Technology

[0002] As a core component of the engine, the high-pressure turbine rotor has extremely high clearance requirements between itself and the corresponding casing during operation. If the clearance is too large, it will lead to engine combustion leakage and reduce engine efficiency. If the clearance is too small, the high-speed rotating turbine rotor will rub against the casing. Therefore, controlling the clearance between the turbine rotor and the casing is particularly important.

[0003] There is a significant difference between the engine manufacturing process and the final operating state. When the engine rotor is in operation, it rotates at high speed and the blades are subjected to a great centrifugal force, which causes the outer diameter of the rotor to be larger than the outer diameter in the free state during manufacturing. This makes it difficult to control the gap between the high-vortex rotor blade tip and the casing.

[0004] The high-pressure turbine rotor consists of high-pressure turbine disk, high-pressure turbine blades, and open retaining rings. The only usable space to lift the blades is the vent hole inside the turbine disk tenon. The vent hole is only 5mm in diameter, which is too small. To lift the blades, a radial force needs to be applied to the blades, but the 5mm space is not enough to accommodate a mechanism that can generate a radial force. Summary of the Invention

[0005] To address the aforementioned problems, this invention aims to provide a fixture and its method for improving the machining and measurement stability of turbine rotors. By using the fixture proposed in this invention for machining and measurement, the manufactured engine turbine rotor can be made closer to its working state, thereby improving its stability.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] A fixture for improving the machining and measurement stability of a turbine rotor includes a top pin disposed in a vent hole in a turbine disk tenon groove, a force-applying component connected to the top pin, and a support component for mounting the force-applying component.

[0008] The force-applying component is inclined on the support component, and the two are connected by threads.

[0009] The force-applying component is a screw connected to the top pin; the top pin and the screw are set in a one-to-one correspondence.

[0010] The support component is a disc, with screws passing through the disc and connecting to the top pin.

[0011] The disc is mounted on the turbine disc.

[0012] An inclined threaded hole is provided on the disc, and a screw passes through the threaded hole to connect with the top pin.

[0013] Multiple threaded holes are provided, evenly distributed on the disk.

[0014] The top pin is installed at an angle in the vent hole of the turbine disk tenon.

[0015] A method for using a fixture to improve the machining and measurement stability of a turbine rotor includes the following steps:

[0016] S1. Determine the working principle of the simulated aero-engine, that is, lift the blade so that the blade tenon and the disc tenon are tightly fitted without gap;

[0017] S2. A top pin is used to install the turbine disk tenon groove in the vent hole;

[0018] S3. Utilizing the principle of threaded transmission, force is applied to the top pin through the screw, and the force is transmitted to the turbine blade tenon, causing the blade to lift up and simulating the working state of the turbine rotor.

[0019] Compared with the prior art, the present invention has the following advantages:

[0020] The present invention discloses a fixture and its method for improving the machining and measurement stability of a turbine rotor. By machining and measuring the outer diameter of the turbine rotor, the manufactured engine turbine rotor can be made closer to its working state, thereby improving the stability of the turbine rotor.

[0021] In this invention, the principle of threaded transmission is utilized. By tightening the screw, force and motion are transmitted to the top pin, thereby further transmitting the force to the turbine blades, achieving the purpose of lifting the blades to simulate their working state.

[0022] This invention is simple to operate, easy to implement, and can better simulate the working state of an aero-engine. The blade tip outer diameter is machined in the jacked-up state, and the resulting rotor outer diameter is close to the outer diameter of the engine rotor in the working state, providing a reference for better control of the gap between the turbine rotor and the casing. Attached Figure Description

[0023] To more clearly illustrate the technical solutions in the specific embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0024] Figure 1 This is a partial structural diagram of the connection between the turbine rotor and the clamp in this invention;

[0025] Figure 2 This is a schematic diagram showing the angle between the screw and the top pin in this invention;

[0026] Figure 3 This is a schematic diagram illustrating the use of the fixture of the present invention in conjunction with the grinding blade fixture;

[0027] Reference numerals: 1-Top pin, 2-Screw, 3-Disc, 4-Grinding blade clamp. Detailed Implementation

[0028] The present invention will be further described below with reference to the accompanying drawings and specific embodiments. However, it should not be construed that the scope of the subject matter of the present invention is limited to the following embodiments. All modifications, substitutions and alterations made based on ordinary technical knowledge and common practices in the art without departing from the above-described technical concept of the present invention are included within the scope of the present invention.

[0029] Reference Figure 1 The present invention provides a fixture for improving the processing and measurement stability of a turbine rotor, comprising a top pin 1 disposed in the vent hole of the turbine disk tenon groove, a force-applying component connected to the top pin 1, and a support component for mounting the force-applying component.

[0030] The force-applying component is inclined on the support component, and the two are connected by threads.

[0031] In this invention, the top pin 1 is installed obliquely in the ventilation hole of the turbine disk tenon groove. The top pin 1 plays the role of transmitting motion and force. One end of the top pin 1 is in contact with the bottom of the turbine blade tenon. As long as a force along the axial direction of the top pin 1 is applied to the other end of the top pin 1, the force can be transmitted to the turbine blade tenon, thereby causing the blade to be subjected to a radial lifting force.

[0032] The force-applying component is set as screw 2, and the support component is set as disc 3.

[0033] Specifically, the force-applying component is a screw 2 connected to the top pin 1; the top pin 1 and the screw 2 are set in a one-to-one correspondence. Each blade corresponds to a tenon, and each tenon requires a top pin 1, and each top pin 1 corresponds to a screw 2; for example, the entire turbine rotor requires 78 sets of top pins 1, so there are 78 screws 2. During operation, force needs to be applied evenly to the 78 top pins 1.

[0034] The supporting component is a disc 3, and a screw 2 passes through the disc 3 and connects to the top pin 1. Multiple threaded holes are evenly distributed on the disc 3, with the screw 2 passing through the threaded holes and connecting to the top pin 1.

[0035] Specifically, due to the limited space available for the high-pressure turbine rotor, screw 2 cannot apply force along the axial direction of the top pin 1. Therefore, in this invention, referring to... Figure 2The screw 2 is tilted at an angle of 35° to ensure that the motion and force are transmitted to the top pin 1 with maximum efficiency while avoiding interference.

[0036] The disc 3 is mounted on the turbine disc as a support component. 78 screws 2 are evenly mounted on the disc 3. The screws 2 are mounted on the disc 3 through threaded holes.

[0037] Reference Figure 3 The axial dimension of the disk 3 and the mounting point of the high-pressure turbine disk is increased. The fixture in this invention and the grinding blade outer diameter are used in conjunction with the grinding blade fixture 4 used on the grinding machine to ensure that the dimensions processed and measured are the dimensions that simulate the working state of the turbine rotor.

[0038] The present invention discloses a method for using a fixture to improve the machining and measurement stability of a turbine rotor, with the aim of simulating the working state of the turbine rotor. Essentially, it involves lifting the blades to simulate the centrifugal force that causes the blades to be thrown apart during the operation of an engine turbine rotor. The method includes the following steps:

[0039] S1. Determine the working principle of the simulated aero-engine, that is, lift the blade so that the blade tenon and the disc tenon are tightly fitted without gap;

[0040] S2. The top pin 1 is installed in the vent hole of the turbine disk tenon groove;

[0041] S3. Utilizing the principle of threaded transmission, the screw 2 applies force to the top pin 1, transmitting the force to the turbine blade tenon, causing the blade to lift up and simulating the working state of the turbine rotor.

[0042] In this embodiment, by utilizing the principle of threaded transmission, tightening the screw 2 transmits force and motion to the top pin 1, thereby further transmitting force to the turbine blades. This achieves the purpose of lifting the blades to simulate their working state. This invention is simple to operate, easy to implement, and can better simulate the working state of an aero-engine. The outer diameter of the blade tip is machined in the lifted state, and the resulting rotor outer diameter is close to the outer diameter of the engine rotor in its working state, providing a reference for better control of the gap between the turbine rotor and the casing.

[0043] The foregoing has provided a detailed description of a fixture for improving the machining and measurement stability of a turbine rotor and its usage method. Specific examples have been used to illustrate the structure and working principle of the invention. The descriptions of the embodiments above are merely for the purpose of helping to understand the method and core ideas of the invention. It should be noted that those skilled in the art can make various improvements and modifications to the invention without departing from its principles, and these improvements and modifications also fall within the scope of protection of the claims of this invention.

Claims

1. A method for using a fixture to improve the machining and measurement stability of a turbine rotor, characterized in that: The clamp includes a top pin (1) disposed in the vent hole of the turbine disk tenon groove, a force-applying component connected to the top pin (1), and a support component for installing the force-applying component; The force-applying component is inclined on the supporting component, and the two are connected by threads; The force-applying component is set as a screw (2) connected to the top pin (1); the top pin (1) and the screw (2) are set in a one-to-one correspondence; The support component is set as a disc (3), and a screw (2) passes through the disc (3) and connects to the top pin (1); An inclined threaded hole is provided on the disc (3), and the screw (2) passes through the threaded hole and connects with the top pin (1); The top pin (1) is installed at an angle in the vent hole of the turbine disk tenon groove; The method of using the fixture includes the following steps: S1. Determine the working principle of the simulated aero-engine, that is, lift the blade so that the blade tenon and the disc tenon are tightly fitted without gap; S2. A top pin (1) is used to install the turbine disk tenon groove in the vent hole; S3. Using the principle of thread transmission, the screw (2) applies force to the top pin (1), and the force is transmitted to the turbine blade tenon. The blade is lifted up, and the turbine rotor simulates its working state.

2. The method of using a fixture for improving the machining and measurement stability of a turbine rotor according to claim 1, characterized in that: The disc (3) is mounted on the turbine disc.

3. The method of using a fixture for improving the machining and measurement stability of a turbine rotor according to claim 1, characterized in that: Multiple threaded holes are set and evenly distributed on the disk (3).

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