Gas turbine rotor balance weight structure, turbine disc and turbine rotor

Abstract

The invention provides a gas turbine rotor balance weight structure, a turbine disc and a turbine rotor.The gas turbine rotor balance weight structure is installed on the turbine disc and comprises a U-shaped groove, the U-shaped groove is connected with an installation edge on the turbine disc in a clamped mode, the U-shaped groove is provided with a pin hole, and when the U-shaped groove is in an assembly position, the pin hole is formed in the U-shaped groove; the pin holes correspond to matching holes in the turbine disc in position; and the limiting groove and the U-shaped groove are arranged at intervals, the limiting groove is located at the rear end of the U-shaped groove, and the limiting groove can be clamped and limited with one end of the limiting plate of the fixing pin. According to the embodiment of the invention, the assembly and disassembly can be realized only by bending the limiting plate on the fixed pin by hands or by a simple tool, compared with the original structure assembly which needs to punch a pin hole and needs to be drilled on a machine tool for damage during disassembly, the disassembly and assembly efficiency is greatly improved, and the balance block which can be repeatedly used can be used for effectively reducing the maintenance cost.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engines, and particularly relates to a balance weight structure for a gas turbine rotor, a turbine disk, and a turbine rotor. Background Art

[0002] The turbine rotor is an important part that drives the rotor to rotate in aero-engines and gas turbines. The turbine rotor needs to work in a high-speed environment. Excessive residual unbalance will cause the turbine rotor to vibrate greatly during operation, and even cause rubbing and damage to the turbine rotor, leading to major safety failures. The balance weight block is the main part used for balancing the turbine rotor and reducing the residual unbalance of the turbine rotor. A certain balance weight block is assembled on the turbine disk through a pin, and the pin is limited and fixed by a three-point stamping method. When assembling this balance weight block, it is necessary to strike the punching point, which is likely to cause damage to the balance weight block; during the disassembly process, it is necessary to destroy the "punching point" and the pin through mechanical processing methods to achieve the disassembly of the balance weight block. In the disassembly process, the turbine disk has been damaged many times due to operation errors. In addition, using the method of destroying the pin for disassembly will damage the balance weight block, making the balance weight block unable to be reused. And the balance weight block is often machined from a ring forging, with a high price, which increases the use cost of this structure of the balance block. Summary of the Invention

[0003] In view of this, the present invention provides a balance weight structure for a gas turbine rotor, a turbine disk, and a turbine rotor, so as to achieve the purpose of making the disassembly and assembly of the balance weight block on the turbine disk convenient, with high safety, and at the same time having better economy.

[0004] The present invention provides the following technical solutions: A balance weight structure for a gas turbine rotor, which is installed on a turbine disk. The balance weight structure for a gas turbine rotor includes: a U-shaped groove, which is clamped with the mounting edge on the turbine disk. The U-shaped groove is provided with a pin hole, and at the assembly position, the pin hole corresponds to the position of the mating hole on the turbine disk; a limiting groove, which is spaced from the U-shaped groove and is located at the rear end of the U-shaped groove, and the limiting groove can be clamped and limited with one end of the limiting plate of the fixing pin.

[0005] Further, the balance weight structure for a gas turbine rotor further includes a limiting boss, which is arranged at the rear end of the U-shaped groove. The limiting boss is located outside the limiting groove, and the limiting boss can be clamped and limited with the other end of the limiting plate of the fixing pin.

[0006] Further, there are two limiting bosses, and the two limiting bosses are spaced apart and form a circumferential clamping groove, and the other end of the limiting plate can be placed in the circumferential clamping groove.

[0007] Furthermore, the other end of the limiting plate is a bent end. When in the free state, the other end of the limiting plate is bent and can rotate around the rotation axis of the fixing pin; when in the locked state, the other end of the limiting plate is straight and is placed in the circumferential clamping groove and circumferentially limited by the circumferential clamping groove.

[0008] Furthermore, in the free state, one end of the limit plate is placed outside the limit groove (4) and can rotate around the rotation axis of the fixing pin, and the fixing pin can move freely axially; in the locked state, one end of the limit plate is placed in the limit groove and is axially limited by the limit groove.

[0009] Furthermore, in the assembly position, the bottom of the U-shaped groove abuts against the mounting edge of the turbine disc.

[0010] The present invention also provides a turbine disk, comprising the above-mentioned gas turbine rotor balancing weight structure.

[0011] The present invention also provides a turbine rotor, comprising the turbine disk.

[0012] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above technical solutions adopted by the present invention include at least:

[0013] Compared with the original structure, the assembly and disassembly of this structure only requires bending the limit plate on the fixed pin with bare hands or simple tools. Compared with the original structure that requires punching the pin hole during assembly and drilling and destruction on a machine tool during disassembly, the disassembly and assembly efficiency is greatly improved;

[0014] During the disassembly and assembly process, only the limit plate on the fixed pin needs to be bent, which will not damage the balance block. The balance block made of the ring forging can be reused, which can reduce the use cost compared with the need to destroy the fixed pin and balance block when the original structure is disassembled;

[0015] When the original structure is disassembled, improper operation often causes damage to the turbine disk. The present balancing weight structure will not damage the turbine disk during the disassembly and assembly process, and safety is greatly improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0017] Figure 1 It is a schematic diagram of the assembly state of the balancing weight structure of the present invention;

[0018] Figure 2 is a front view of the balancing weight of the present invention;

[0019] Figure 3 is a cross-sectional view of a balancing weight of the present invention;

[0020] Figure 4 is a front view of the fixing pin of the present invention;

[0021] Figure 5 It is a cross-sectional view of a fixing pin of the present invention.

[0022] The reference numerals in the figure are: 1, turbine disc; 2, balancing block; 3, fixing pin; 4, limiting groove; 5, limiting boss; 6, pin hole; 7, pin body; 8, limiting plate. DETAILED DESCRIPTION

[0023] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0024] The following describes the implementation methods of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific implementation methods, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the following embodiments and the features in the embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work belong to the scope of protection of the present application.

[0025] like Figures 1 to 5 As shown, an embodiment of the present invention provides a gas turbine rotor balancing weight structure, which is installed on a turbine disk 1, and the gas turbine rotor balancing weight structure includes a U-shaped groove and a limiting groove 4. The U-shaped groove is clamped with the mounting edge on the turbine disk 1, and the U-shaped groove is provided with a pin hole 6. When in the assembly position, the pin hole 6 corresponds to the position of the matching hole on the turbine disk 1; the limiting groove 4 is spaced apart from the U-shaped groove and is located at the rear end of the U-shaped groove, and the limiting groove 4 can be clamped with one end of the limiting plate 8 of the fixing pin for limiting.

[0026] The assembly and disassembly of the embodiment of the present invention only requires bending the limit plate on the fixing pin by hand or with simple tools. Compared with the original structure which requires punching the pin hole during assembly and drilling and destroying on a machine tool during disassembly, the assembly and disassembly efficiency is greatly improved.

[0027] The limiting plate 8 is connected to the fixing pin 3 to form an integral structure.

[0028] The gas turbine rotor balancing weight structure also includes a limiting boss 5, which is arranged at the rear end of the U-shaped groove. The limiting boss 5 is located outside the limiting groove 4, and the limiting boss 5 can be clamped and limited with the other end of the limiting plate 8 of the fixing pin.

[0029] The gas turbine rotor balancing weight structure realizes a fast and safe assembly and disassembly process through the ingenious cooperation between the limiting boss 5 and the limiting plate 8, significantly improves the assembly efficiency, reduces the maintenance cost, and at the same time enhances the reliability and safety of the structure, so that the balancing block can be reused, reducing the risk of damage to the turbine disc and the balancing block.

[0030] There are two limiting bosses 5, which are arranged at intervals and form a circumferential clamping groove, and the other end of the limiting plate 8 can be placed in the circumferential clamping groove. The other end of the limiting plate 8 is a bent end. In the free state, the other end of the limiting plate 8 is bent and can rotate around the rotation axis of the fixing pin; in the locked state, the other end of the limiting plate 8 is straight and is placed in the circumferential clamping groove and is circumferentially limited with the circumferential clamping groove.

[0031] The technical effect of the gas turbine rotor balancing weight structure is that through the cooperation between the limiting boss 5 and the limiting plate 8, fast and safe assembly and disassembly are achieved, which greatly improves the assembly efficiency, reduces the maintenance cost, enhances the reliability and safety of the structure, allows the reuse of the balancing block, and effectively reduces the risk of damage to the turbine disc and the balancing block.

[0032] In the embodiment of the present invention, in the free state, one end of the limit plate 8 is placed outside the limit slot 4 and can rotate around the rotation axis of the fixing pin, and the fixing pin can move freely axially; in the locked state, one end of the limit plate 8 is placed in the limit slot 4 and is axially limited by the limit slot 4.

[0033] The design of the limit plate 8 allows it to rotate flexibly around the rotation axis of the fixing pin in the free state, and in the locked state, one end of the limit plate 8 can be fixed in the limit groove 4 and achieve axial limitation. This design improves the flexibility of assembly and the stability of locking, ensuring the reliability and safety of the rotor balance weight structure during operation.

[0034] It should be noted that, in the assembly position, the bottom of the U-shaped groove abuts against the mounting edge of the turbine disc 1, transmitting the centrifugal load of the balancing weight structure when the turbine rotor rotates. The present invention can support the turbine disc 1 through the bottom of the U-shaped groove to prevent the fixing pin from being subjected to shear stress.

[0035] The present invention also provides a turbine disk, comprising the above-mentioned gas turbine rotor balancing weight structure.

[0036] In practical applications, the present invention can be used for the assembly of rotating parts of the shaft type in aircraft engines and gas turbines. During assembly, the balancing block 2 is installed at the corresponding pin hole of the turbine disk 1; the pin body 7 of the fixing pin 3 is passed through the pin hole 6 on the balancing block, the fixing pin is rotated to the limit groove 4 on the balancing block, and the bending part of the limit plate 8 on the fixing pin 3 is bent to the middle of the two circumferential limit bosses 5 of the balancing block to limit the rotation of the fixing pin 3. During disassembly, it is only necessary to bend out the middle part of the limit plate 8 on the fixing pin 3 located on the circumferential limit boss 5 of the balancing block 2, and then the fixing pin 3 can be rotated, and the fixing pin 3 and the balancing block 2 can be disassembled from the turbine disk 1 in turn.

[0037] In this example, the balance block 2 can be made of a forged material with higher strength, such as a high-temperature alloy, which is consistent with the turbine disk. The fixing pin 3 can be made of a material with lower hardness and better plasticity. The balance block 2 can be made of a high-temperature alloy made of the same material as the turbine disk and obtained through solid solution treatment.

[0038] The diameter of the pin hole 6 in the balancing block 2 is consistent with the diameter of the pin body 7, which is φ3.5~φ4mm. The diameter of the pin hole on the turbine disk 1 is about 0.2mm larger than the diameter of the pin body, which ensures that the pin is fixed while avoiding shearing of the pin during operation; the chamfer of the pin hole on the balancing block is C0.3~C0.5, which is convenient for fixing the pin assembly; the width of the balancing block limit groove 4 can be selected to be 1~1.2mm, which is slightly larger than the thickness of the limit plate 8 of 0.8~1mm; the height of the balancing limit boss 5 is 2~2 .5mm, which is about 2 to 3 times the thickness of the limiting plate 8; the width of the limiting boss 5 is 6.2mm, which is slightly larger than the width of the limiting plate 8 of 6mm. The limiting plate 8 is bent at a suitable position by 30° to 60°, usually 45°, to ensure that the bent plate can rotate freely; the chamfer of the limiting boss 5 is C0.5, which is convenient for guiding the bent limiting plate 8 to be stuck into the limiting groove; the bottom of the limiting boss is processed into an oblique angle of about -10° to ensure that the limiting plate 8 can still be reliably stuck in the limiting boss 5 after deformation recovery after bending.

[0039] Preferably, the present invention also provides a turbine rotor, comprising the above-mentioned turbine disk.

[0040] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A gas turbine rotor balancing weight structure, mounted on a turbine disk (1), characterized in that: The gas turbine rotor balancing weight structure comprises: A U-shaped groove is clamped with a mounting edge on the turbine disk (1), the U-shaped groove is provided with a pin hole (6), and when in the assembly position, the pin hole (6) corresponds to the position of the matching hole on the turbine disk (1); The limiting groove (4) is spaced apart from the U-shaped groove and is located at the rear end of the U-shaped groove. The limiting groove (4) can be engaged with one end of the limiting plate (8) of the fixing pin for limiting.

2. The gas turbine rotor balancing weight structure according to claim 1, characterized in that: The gas turbine rotor balancing weight structure also includes a limiting boss (5) arranged at the rear end of the U-shaped groove, the limiting boss (5) is located outside the limiting groove (4), and the limiting boss (5) can be engaged with the other end of the limiting plate (8) of the fixing pin for limiting.

3. The gas turbine rotor balancing weight structure according to claim 2, characterized in that: There are two limiting bosses (5), which are arranged at an interval and form a circumferential clamping groove, and the other end of the limiting plate (8) can be placed in the circumferential clamping groove.

4. The gas turbine rotor balancing weight structure according to claim 3, characterized in that: The other end of the limiting plate (8) is a bent end. In a free state, the other end of the limiting plate (8) is bent and the other end of the limiting plate (8) can rotate around the rotation axis of the fixing pin; In the locked state, the other end of the limiting plate (8) is straight and is placed in the circumferential clamping groove and is circumferentially limited with the circumferential clamping groove.

5. The gas turbine rotor balancing weight structure according to claim 4, characterized in that: In a free state, one end of the limiting plate (8) is placed outside the limiting groove (4) and can rotate around the rotation axis of the fixing pin, and the fixing pin can freely move axially; In the locked state, one end of the limiting plate (8) is placed in the limiting groove (4) and is axially limited with the limiting groove (4).

6. The gas turbine rotor balancing weight structure according to claim 5, characterized in that: When in the assembly position, the bottom of the U-shaped groove abuts against the mounting edge of the turbine disc (1).

7. A turbine disk, comprising a gas turbine rotor balancing weight structure, characterized in that: The gas turbine rotor balancing weight structure is the gas turbine rotor balancing weight structure according to any one of claims 1 to 6.

8. A turbine rotor, comprising a turbine disk, characterized in that: The turbine disk is the turbine disk according to claim 7.

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