Turbine rotor over-rotation test assembly and turbine moving blade over-rotation test piece thereof

Abstract

The invention relates to a turbine rotor over-rotation test assembly and a turbine moving blade over-rotation test piece thereof, which are used for reducing the over-rotation test cost. The turbine moving blade over-rotation test piece comprises a tenon and a balancing weight; the tenon has the same structure as the tenon of the real movable blade and is used for being inserted into the mortise of the turbine disc; the balancing weight is located on the peripheral side of the tenon, so that the weight and the mass center position of the turbine moving blade over-rotation test piece are the same as those of a real moving blade; wherein two sides of the balancing weight in the circumferential direction are provided with self-locking surfaces, the self-locking surfaces are inclined relative to the assembly direction of the tenon, and the self-locking surface of one turbine moving blade over-rotation test piece is used for being attached to the self-locking surface of the other turbine moving blade over-rotation test piece in the circumferential direction so as to prevent the tenon from being disengaged in the assembly direction.

Description

Technical Field

[0001] The present invention relates to the technical field of turbine engine tests, and particularly relates to a turbine rotor over-speed test assembly and an over-speed test piece for turbine moving blades thereof. Background Art

[0002] The low-pressure turbine rotor is composed of multiple stages of turbine rotors. Each stage of turbine rotor is composed of a turbine disk 1', a moving blade 2, and a retaining ring 3'. As Figure 1 shown, the tenon 4' on the inner circumferential side of the moving blade 2 is fitted with the mortise of the turbine disk 1'. The serrated leaf crowns on the outer circumferential side of the moving blades 2 are engaged with each other. The retaining ring 3' is installed between the turbine disk 1' and the moving blade 2 to prevent the moving blade 2 from disengaging from the turbine disk 1'.

[0003] The turbine disk 1' is a key component of the turbine rotor. According to airworthiness requirements, an over-speed test needs to be carried out. The turbine disk 1' equipped with the moving blade 2 is subjected to an over-speed test on a test bench at 120% of its maximum allowable speed and kept loaded for five minutes. After the test, no cracks are required in the parts. The structure of the moving blade 2 is complex and the processing difficulty is high. Using the real moving blade 2 for the over-speed test has a high cost. Summary of the Invention

[0004] The purpose of the present invention is to provide a turbine rotor over-speed test assembly and an over-speed test piece for turbine moving blades thereof, so as to reduce the cost of the over-speed test.

[0005] In a first aspect, the present invention provides an over-speed test piece for turbine moving blades. According to an embodiment of the present invention, the over-speed test piece for turbine moving blades includes a tenon and a counterweight; the tenon has the same structure as the tenon of a real moving blade and is used for inserting into the mortise of the turbine disk; the counterweight is located on the outer circumferential side of the tenon, so that the weight and the centroid position of the over-speed test piece for turbine moving blades are the same as those of the real moving blade; wherein, the counterweight is provided with self-locking surfaces on both circumferential sides, the self-locking surfaces are inclined relative to the assembly direction of the tenon, and the self-locking surfaces of one over-speed test piece for turbine moving blades are used to abut against the self-locking surfaces of another over-speed test piece for turbine moving blades in the circumferential direction to prevent the tenon from disengaging along the assembly direction.

[0006] In one or more embodiments, the counterweight is provided with self-locking blocks, and the self-locking blocks protrude from the circumferential side wall of the counterweight, and the circumferential side wall of the self-locking blocks provides the self-locking surfaces.

[0007] In one or more embodiments, the self-locking blocks are located at the ends of the counterweight on the outer circumferential side.

[0008] In one or more embodiments, the self-locking surfaces are planes.

[0009] In one or more embodiments, a stop is configured on the axial side of the tenon. The stop has an axial spacing from the axial end face of the tenon, so as to provide a groove between the stop and the axial end face of the tenon. The groove is used for inserting a retaining ring to prevent the tenon from disengaging along the assembly direction.

[0010] In one or more embodiments, the counterweight is in the shape of a rectangular block.

[0011] In a second aspect, the present invention provides a turbine rotor overspeed test assembly. According to an embodiment of the present invention, the turbine rotor overspeed test assembly includes a turbine disk and the above-mentioned turbine blade overspeed test piece; the turbine disk is provided with a plurality of tenon grooves along the disk circumference; the tenon of each turbine blade overspeed test piece is inserted into one of the tenon grooves, and the plurality of turbine blade overspeed test pieces are circumferentially installed on the outer periphery of the turbine disk; wherein, the self-locking surfaces of each turbine blade overspeed test piece are circumferentially abutted against the self-locking surfaces of the circumferentially adjacent turbine blade overspeed test pieces to prevent the tenon from disengaging from the tenon groove along the assembly direction.

[0012] In one or more embodiments, the turbine rotor overspeed test assembly further includes a retaining ring. The retaining ring is arranged on the axial side of the tenon groove, and the retaining ring is inserted into the plurality of grooves of the plurality of turbine blade overspeed test pieces to prevent the tenon from disengaging from the tenon groove along the assembly direction.

[0013] In one or more embodiments, the retaining ring is provided with a circumferential opening.

[0014] The embodiments of the present invention at least have the following beneficial effects:

[0015] 1. The weight and centroid position of the counterweight make the weight and centroid position of the turbine blade overspeed test piece the same as those of the real blade, which enables the turbine blade overspeed test piece to simulate the centrifugal force load of the real blade in the overspeed test, ensuring the authenticity and reliability of the overspeed test. The structure of the counterweight is simple, which simplifies the structure of the turbine blade overspeed test piece and reduces the cost of the overspeed test.

[0016] 2. The self-locking surface is inclined relative to the assembly direction of the tenon. The self-locking surfaces of each turbine blade overspeed test piece are circumferentially abutted against the self-locking surfaces of another circumferentially adjacent turbine blade overspeed test piece to prevent the tenon from disengaging from the tenon groove along the assembly direction, preventing the turbine blade overspeed test piece from disengaging from the turbine disk during flipping, and facilitating the assembly of the turbine rotor overspeed test assembly. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The above and other features, properties and advantages of the present invention will become more apparent from the following description in conjunction with the drawings and embodiments, wherein:

[0018] Figure 1Is an oblique view of an existing turbine rotor;

[0019] Figure 2 Is an oblique view of the over-speed test piece of the turbine moving blade of the present invention;

[0020] Figure 3 Is an oblique view of the over-speed test assembly of the turbine rotor of the present invention;

[0021] Figure 4 Is a side view of the over-speed test assembly of the turbine rotor of the present invention;

[0022] Figure 5 Is a sectional view of the over-speed test assembly of the turbine rotor of the present invention;

[0023] Figure 6 Is an oblique view of another over-speed test piece of the turbine moving blade of the present invention;

[0024] Reference numerals:

[0025] 1'- Turbine disk;

[0026] 2 - Moving blade;

[0027] 3'- Retaining ring;

[0028] 4'- Tenon;

[0029] 1 - Turbine disk;

[0030] 3 - Retaining ring;

[0031] 4 - Tenon;

[0032] 5 - Over-speed test piece of turbine moving blade;

[0033] 6 - Mortise;

[0034] 7 - Counterweight;

[0035] 8 - Self-locking surface;

[0036] 9 - Self-locking block;

[0037] 10 - Retaining part;

[0038] 11 - Groove part;

[0039] 12 - Claw;

[0040] 13 - Sealing ring. Detailed implementation manners

[0041] Reference will now be made in detail to embodiments of the present invention, one or more examples of which are illustrated in the accompanying drawings. Each example is provided to explain the present invention, not to limit it. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made to the present invention without departing from the scope or spirit thereof. For example, features shown or described as part of one embodiment can be used with another embodiment to yield yet another embodiment. Accordingly, the present invention is intended to cover such modifications and variations that fall within the scope of the appended claims and their equivalents.

[0042] It should be noted that these and subsequent other drawings are only examples, and they are not drawn under the condition of equal proportion, and should not be used to limit the actual scope of protection required by the present invention.

[0043] As Figure 3 shown, the turbine rotor overspeed test assembly includes a turbine disk 1 and a plurality of turbine blade overspeed test pieces 5. Further referring to Figure 5 , a plurality of tenon grooves 6 are formed in the turbine disk 1 along the disk circumference. The tenon grooves 6 can extend substantially axially, can extend axially, or can be inclined at a certain angle relative to the axis. The plurality of tenon grooves 6 can be circumferentially evenly distributed on the turbine disk 1. The structure of the turbine disk 1 can be the same as that of the real turbine disk. Further referring to Figure 2 and Figure 6 , each turbine blade overspeed test piece 5 includes a tenon head 4, and the tenon head 4 has the same structure as the tenon head of the real blade. The tenon head 4 of each turbine blade overspeed test piece 5 is inserted into a tenon groove 6, and thus the plurality of turbine blade overspeed test pieces 5 are circumferentially installed on the outer periphery of the turbine disk 1. The extending direction of the tenon groove 6 limits the extending direction of the tenon head 4, and the extending direction of the tenon head 4 is the same as that of the tenon groove 6. The tenon head 4 can extend substantially axially, can extend axially, or can be inclined at a certain angle relative to the axis. The extending direction of the tenon head 4 and the tenon groove 6 is also the assembling direction of the tenon head 4 and the tenon groove 6. The tenon head 4 is inserted into or pulled out of the tenon groove 6 along this extending direction.

[0044] As Figure 2 and Figure 6 shown, each turbine blade overspeed test piece 5 further includes a counterweight 7. The counterweight 7 is located on the outer peripheral side of the tenon head 4, and the inner peripheral wall of the counterweight 7 can be connected to the outer peripheral wall of the tenon head 4. The weight and the centroid position of the counterweight 7 are such that the weight and the centroid position of the turbine blade overspeed test piece 5 are the same as those of the real blade, which enables the turbine blade overspeed test piece 5 to simulate the centrifugal force load of the real blade in the overspeed test and ensures the authenticity and reliability of the overspeed test. Compared with the real blade, the counterweight 7 has a simple structure, simplifies the structure of the turbine blade overspeed test piece 5, and reduces the cost of the overspeed test.

[0045] As Figure 2 and Figure 6As shown, the counterweight 7 can be in the shape of a rectangular block with a rectangular axial end face, which is convenient for machining and at the same time easy to determine its centroid position, further reducing the cost of the super-rotation test. The counterweight 7 can also be in other shapes that are convenient for machining, such as a parallelogram block with a parallelogram axial end face or a rhombus block with a rhombus axial end face.

[0046] As Figures 2 to 4 shown, self-locking surfaces 8 are provided on both circumferential sides of the counterweight 7. Two self-locking surfaces 8 are provided for each counterweight 7, one self-locking surface 8 is located on one circumferential side of the counterweight 7, and the other self-locking surface 8 is located on the other circumferential side of the counterweight 7. The self-locking surface 8 can be directly provided by the circumferential side wall of the counterweight 7. The two circumferential side wall surfaces of the counterweight 7 are respectively the two self-locking surfaces 8. However, using the entire circumferential side wall surface as the self-locking surface 8 has high machining requirements for the counterweight 7, resulting in a high cost for the super-rotation test. As Figure 2 and Figure 3 shown, the counterweight 7 can be provided with self-locking blocks 9. The self-locking blocks 9 protrude from the circumferential side wall of the counterweight 7. The circumferential side wall of the self-locking block 9 provides the self-locking surface 8. The circumferential side wall surface of the self-locking block 9 serves as the self-locking surface 8. Compared with using the circumferential side wall surface of the counterweight 7 as the self-locking surface 8, the area of the self-locking surface 8 is reduced, which is convenient for machining and further reduces the cost of the super-rotation test. Two self-locking blocks 9 can be provided for each counterweight 7, one self-locking block 9 protrudes from one circumferential side wall of the counterweight 7, and the other self-locking block 9 protrudes from the other circumferential side wall of the counterweight 7. The self-locking blocks 9 can protrude circumferentially from the circumferential side wall of the counterweight 7 and have an arc-shaped contour at the axial end face. The self-locking blocks 9 can be arranged at the end of the counterweight 7 on the outer peripheral side as Figures 2 to 4 shown, which makes the locking of the self-locking blocks 9 similar to the locking of the blade crown of a real moving blade, with better simulation. The self-locking blocks 9 can also be arranged at the end of the counterweight 7 on the inner peripheral side as Figure 6 shown.

[0047] As Figures 2 to 4 and Figure 6 shown, the self-locking surface 8 is inclined relative to the assembly direction of the tenon 4. The self-locking surfaces 8 of each turbine moving blade super-rotation test piece 5 abut against the self-locking surfaces 8 of another circumferentially adjacent turbine moving blade super-rotation test piece 5 in the circumferential direction to prevent the tenon 4 from disengaging from the mortise 6 along the assembly direction. When a turbine moving blade super-rotation test piece 5 tends to move along the assembly direction of the tenon 4 and disengage from the mortise 6, the two self-locking surfaces 8 of this turbine moving blade super-rotation test piece 5 are respectively abutted by the self-locking surfaces 8 of the two circumferentially adjacent turbine moving blade super-rotation test pieces 5. The self-locking surface 8 can be a plane, and the two self-locking surfaces 8 of each turbine moving blade super-rotation test piece 5 are parallel, so that the self-locking surfaces 8 of two circumferentially adjacent turbine moving blade super-rotation test pieces 5 abut against each other. The assembly of the turbine rotor super-rotation test assembly is a typical situation where the self-locking surface 8 plays a role in preventing disengagement. As Figure 4As shown, during assembly, the turbine blade over-rotation test piece 5 needs to be assembled on the turbine disk 1 first. When the turbine disk 1 equipped with the turbine blade over-rotation test piece 5 is turned over for the subsequent assembly of the retaining ring 3, under the action of gravity G, the turbine blade over-rotation test piece 5 tends to move along the assembly direction of the tenon 4 and slip out of the tenon groove 6. The component force F of the gravity G causes the self-locking surface 8 to resist, and multiple turbine blade over-rotation test pieces 5 form a whole and cannot fall off from the turbine disk 1, which is convenient for the assembly of the turbine rotor over-rotation test assembly.

[0048] like Figures 2 to 6 As shown, the tenon 4 of each turbine blade super-rotation test piece 5 may be provided with a stopper 10 on the axial side, and the stopper 10 and the axial end face of the tenon 4 have an axial spacing, so that a groove 11 is provided between the stopper 10 and the axial end face of the tenon 4. The stopper 10 may be provided only on one axial side of the tenon 4. After a plurality of turbine blade super-rotation test pieces 5 are circumferentially installed on the outer periphery of the turbine disk 1, the grooves 11 of the turbine blade super-rotation test pieces 5 are circumferentially connected to form an annular groove. The axial end face of the tenon 4 may be perpendicular to the axial direction, and the stopper 10 may be perpendicular to the axial direction, so that the groove 11 is perpendicular to the axial direction, and the annular groove formed by the circumferential connection of the grooves 11 still has a flat axial end face. The stopper 10 may be a claw 12, which protrudes from the end of the counterweight block 7 on the inner circumference, and the circumferential width of the claw 12 is smaller than the circumferential width of the counterweight block 7 to reduce weight, and the claw 12 may be consistent with the structure of a real blade. As shown Figure 3 and Figure 5 As shown, the turbine rotor overspeed test assembly may also include a retaining ring 3, which is arranged on the axial side of the tenon groove 6. The retaining ring 3 is inserted into the multiple grooves 11 of the multiple turbine blade overspeed test pieces 5 to prevent the tenon 4 from slipping out of the tenon groove 6 along the assembly direction. The retaining ring 3 can be fixed on the axial side of the tenon groove 6 by a sealing ring 13. The retaining ring 3 can be provided with a circumferential opening, and the elasticity of the retaining ring 3 allows the circumferential opening to be closed under external force to insert into the annular groove portion of the groove portion 11 that is circumferentially connected, and the elasticity of the retaining ring 3 also allows the circumferential opening to open after the external force is removed. The retaining ring 3 can be consistent with the structure of a real retaining ring.

[0049] The assembly method of the turbine rotor overspeed test assembly can be: insert the tenon 4 of the turbine blade overspeed test piece 5 into the tenon groove 6 of the turbine disk 1 along the assembly direction, turn over the turbine disk 1 assembled with all the turbine blade overspeed test pieces 5, and insert the retaining ring 3 into the annular groove portion where multiple grooves 11 are circumferentially connected.

[0050] Although the present invention is disclosed as above by the embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications without departing from the spirit and scope of the present invention.

Claims

1. A turbine moving blade overspeed test piece, characterized in that it includes: a tenon head, having the same structure as the tenon head of the real moving blade, for inserting into the tenon groove of the turbine disk; and a counterweight block, located on the outer peripheral side of the tenon head, making the weight and the centroid position of the turbine moving blade overspeed test piece the same as those of the real moving blade; wherein, self-locking surfaces are arranged on both circumferential sides of the counterweight block, and the self-locking surfaces are inclined relative to the assembly direction of the tenon head. The self-locking surface of one turbine moving blade overspeed test piece is used to abut against the self-locking surface of another turbine moving blade overspeed test piece in the circumferential direction to prevent the tenon head from disengaging along the assembly direction.

2. The turbine moving blade overspeed test piece according to claim 1, characterized in that: the counterweight block is provided with a self-locking block, and the self-locking block protrudes from the circumferential side wall of the counterweight block, and the circumferential side wall of the self-locking block provides the self-locking surface.

3. The turbine moving blade overspeed test piece according to claim 2, characterized in that: the self-locking block is located at the end of the counterweight block on the outer peripheral side.

4. The turbine moving blade overspeed test piece according to claim 1 or 2, characterized in that: the self-locking surface is a plane.

5. The turbine moving blade overspeed test piece according to claim 1, characterized in that: a stopper is arranged on the axial side of the tenon head, and the stopper has an axial interval from the axial end face of the tenon head, so as to provide a groove portion located between the stopper and the axial end face of the tenon head, and the groove portion is used for inserting a retaining ring to prevent the tenon head from disengaging along the assembly direction.

6. The turbine moving blade overspeed test piece according to claim 1, characterized in that: the counterweight block is in a rectangular block shape.

7. A turbine rotor overspeed test assembly, characterized in that it includes: a turbine disk, having a plurality of tenon grooves opened along the disk circumference; and a plurality of turbine moving blade overspeed test pieces according to any one of claims 1 to 6, wherein the tenon head of each turbine moving blade overspeed test piece is inserted into one of the tenon grooves, and the plurality of turbine moving blade overspeed test pieces are circumferentially installed on the outer periphery of the turbine disk; wherein, the self-locking surface of each turbine moving blade overspeed test piece abuts against the self-locking surface of the circumferentially adjacent turbine moving blade overspeed test piece in the circumferential direction to prevent the tenon head from disengaging from the tenon groove along the assembly direction.

8. The turbine rotor overspeed test assembly according to claim 7, characterized in that: the turbine rotor overspeed test assembly further includes a retaining ring, and the retaining ring is arranged on the axial side of the tenon groove, and the retaining ring is inserted into the plurality of groove portions of the plurality of turbine moving blade overspeed test pieces to prevent the tenon head from disengaging from the tenon groove along the assembly direction.

9. The turbine rotor overspeed test assembly according to claim 8, characterized in that: the retaining ring is provided with a circumferential opening.

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