Aeroengine turbine seal ring repairing device and repairing method

Abstract

This invention relates to the field of aero-engine technology, and more particularly to a turbine seal ring repair device and method for aero-engines. The device includes a base plate, a cover plate, and a connecting structure. The upper inner surface of the base plate has a first arc-shaped protrusion and a first arc-shaped groove. The cover plate has a first cylindrical clearance hole in its center. The lower inner surface of the cover plate has a second arc-shaped protrusion and a second arc-shaped groove. The second arc-shaped groove corresponds vertically to the first arc-shaped protrusion, and vice versa. The axial dimension of the turbine seal ring's stop step assembly surface is shaped and corrected, and then the dimensions of the turbine seal ring to be repaired are stabilized through a heat treatment process. This completes the repair of the axial dimension of the turbine seal ring's stop step assembly surface, allowing the turbine seal ring to be reused, extending its service life, and reducing the operating costs of the aero-engine.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and in particular to an aero-engine turbine sealing ring repair device and repair method. Background Technology

[0002] like Figure 1 , Figure 2 As shown, a turbine sealing ring for a certain type of aero-engine includes a main body 41 and a stop-step mounting surface 42. The stop-step mounting surface 42 is connected and disposed on the outer side of the main body 41. The turbine sealing ring is typically made of Waspaloy alloy or GH738 alloy, with a thickness of 0.3 mm. The stop-step mounting surface 42 consists of a ring of arc-shaped protrusions and a ring of arc-shaped grooves connected together. The longest distance between the arc-shaped protrusions and the arc-shaped grooves is L. During the operation of this type of aero-engine, the turbine sealing ring is subjected to long-term compression and fretting, resulting in axial elastic decay. This causes the axial dimension of the stop-step mounting surface 42 of the turbine sealing ring to decrease, that is... Figure 2 As shown, a smaller L dimension and a smaller axial dimension of the stop step assembly surface 42 of the turbine sealing ring will lead to a poorer seal between the turbine guide and the turbine guide housing, and make it difficult to ensure the effectiveness of axial positioning.

[0003] Currently, there are no effective repair devices or methods to repair turbine sealing rings. As a result, turbine sealing rings with reduced axial dimensions of the stop step assembly surface 42 cannot be repaired and must be scrapped, which increases the operating cost of aero engines and results in low resource utilization. Summary of the Invention

[0004] The technical problem solved by this invention is to provide an aircraft engine turbine seal ring repair device capable of repairing aircraft engine turbine seal rings.

[0005] The technical solution adopted by the present invention to solve its technical problem is: an aero-engine turbine sealing ring repair device, including a base plate, a cover plate and a connecting structure, wherein a first arc-shaped protrusion and a first arc-shaped groove are provided on the upper surface of the inner side of the base plate, and the first arc-shaped protrusion is located outside the first arc-shaped groove.

[0006] A first cylindrical clearance hole is provided in the center of the cover plate. A second arc-shaped protrusion and a second arc-shaped groove are provided on the lower surface of the inner side of the cover plate. The first arc-shaped protrusion is located inside the first arc-shaped groove and is connected to the side wall of the first cylindrical clearance hole.

[0007] The second arc-shaped groove corresponds vertically to the first arc-shaped protrusion, and the second arc-shaped protrusion corresponds vertically to the first arc-shaped groove.

[0008] The stop step assembly surface of the turbine sealing ring can be matched and locked in the first arc-shaped groove and the second arc-shaped groove, and the lower surface of the stop step assembly surface is in contact with the surface of the first arc-shaped protrusion and the inner wall of the first arc-shaped groove, and the upper surface of the stop step assembly surface is in contact with the surface of the second arc-shaped protrusion and the inner wall of the second arc-shaped groove.

[0009] The base plate and the cover plate are detachably connected together via a connecting structure, with the cover plate located on top of the base plate.

[0010] Furthermore, the connection structure includes connecting bolts, a first connecting hole on the outside of the base plate, and a second connecting hole on the outside of the cover plate. The connecting bolts pass through the first connecting hole and the second connecting hole to detachably connect the base plate and the cover plate together.

[0011] Furthermore, the connection structure includes multiple connecting bolts, multiple first connecting holes, and multiple second connecting holes. The first connecting holes are evenly distributed on the outer side of the base plate, and the second connecting holes are evenly distributed on the outer side of the cover plate. The upper and lower positions of one second connecting hole correspond to one first connecting hole.

[0012] A connecting bolt is fitted through a first connecting hole and a second connecting hole to detachably connect the base plate and the cover plate together.

[0013] Furthermore, the base plate and cover plate are made of heat-resistant steel.

[0014] Furthermore, a first positioning hole is provided on the outer side of the base plate, and a second positioning hole is provided on the outer side of the cover plate. The positioning pin is detachably installed in the second positioning hole and the first positioning hole.

[0015] Furthermore, a second cylindrical clearance hole is provided in the center of the base plate, and the first cylindrical clearance hole and the second cylindrical clearance hole are positioned vertically opposite each other.

[0016] Furthermore, the technical problem solved by this invention is to provide a method for repairing turbine seal rings of aero engines.

[0017] The repair method for turbine sealing rings of aircraft engines includes the following steps:

[0018] a. Fabricate the aforementioned aircraft engine turbine seal ring repair device;

[0019] b. Fix the turbine sealing ring to be repaired in the aero-engine turbine sealing ring repair device. Specifically: First, match the stop step assembly surface of the turbine sealing ring in the first arc-shaped groove and the second arc-shaped groove, with the lower surface of the stop step assembly surface abutting against the surface of the first arc-shaped protrusion and the inner wall of the first arc-shaped groove, and the upper surface of the stop step assembly surface abutting against the surface of the second arc-shaped protrusion and the inner wall of the second arc-shaped groove. The main body of the turbine sealing ring is matched and set in the first cylindrical clearance hole; then, the base plate and the cover plate are detachably connected together through the connecting structure.

[0020] c. Stabilize the dimensions of the turbine sealing ring to be repaired through heat treatment process; the heat treatment process parameters are as follows: the turbine sealing ring to be repaired is put into the furnace at 4≤150℃, pre-evacuated to at least 13.3pa, heated for 70min-100min to 760℃±10℃, held for 4h-5h, after the holding period, argon gas of 2bar-3bar is introduced and cooled to below 80℃ before being taken out of the furnace.

[0021] Preferably, the turbine sealing ring is made of Waspaloy alloy or GH738 alloy, and the thickness of Waspaloy alloy or GH738 alloy is 0.3mm.

[0022] Preferably, before the turbine seal ring to be repaired is fixedly installed in the aircraft engine turbine seal ring repair device, the turbine seal ring to be repaired and the aircraft engine turbine seal ring repair device are cleaned with an organic solvent.

[0023] The beneficial effects of this invention are: the turbine sealing ring repair device of this invention can correct the axial dimension of the stop step assembly surface of the turbine sealing ring, and then stabilize the dimension of the turbine sealing ring to be repaired through heat treatment process, thereby completing the repair of the axial dimension of the stop step assembly surface of the turbine sealing ring, so that the turbine sealing ring can be reused, extending the service life of the turbine sealing ring, reducing the operating cost of the aero-engine, improving resource utilization, and having important economic value. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the turbine sealing ring;

[0025] Figure 2 This is a schematic diagram of the cross-section of the turbine sealing ring;

[0026] Figure 3 This is a schematic diagram of the turbine seal ring repair device for aircraft engines during repair.

[0027] Figure 4 This is a structural diagram of the base plate;

[0028] Figure 5This is the front sectional view of the base plate;

[0029] Figure 6 yes Figure 5 Enlarged view of point A in the middle;

[0030] Figure 7 This is a structural schematic diagram of the cover plate;

[0031] Figure 8 This is the front sectional view of the cover plate;

[0032] Figure 9 yes Figure 8 Enlarged view at point B in the middle;

[0033] The markings are as follows: base plate 1, first arc-shaped protrusion 11, first arc-shaped groove 12, second cylindrical clearance hole 13, first connecting hole 14, first positioning hole 15, cover plate 2, second arc-shaped protrusion 21, second arc-shaped groove 22, first cylindrical clearance hole 23, second connecting hole 24, second positioning hole 25, connecting bolt 3, turbine sealing ring 4, main body 41, stop step assembly surface 42. Detailed Implementation

[0034] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0035] The directions mentioned below are in the form of Figure 3 The orientation of each component is used as a reference.

[0036] like Figures 1 to 9 As shown, the aero-engine turbine sealing ring repair device of the present invention includes a base plate 1, a cover plate 2 and a connecting structure. The upper surface of the inner side of the base plate 1 is provided with a first arc-shaped protrusion 11 and a first arc-shaped groove 12, and the first arc-shaped protrusion 11 is located outside the first arc-shaped groove 12.

[0037] The cover plate 2 has a first cylindrical clearance hole 23 in the center. The lower surface of the inner side of the cover plate 2 has a second arc-shaped protrusion 21 and a second arc-shaped groove 22. The first arc-shaped protrusion 11 is located inside the first arc-shaped groove 12. The first arc-shaped protrusion 11 is connected to the side wall of the first cylindrical clearance hole 23.

[0038] The second arc-shaped groove 22 corresponds vertically to the first arc-shaped protrusion 11, and the second arc-shaped protrusion 21 corresponds vertically to the first arc-shaped groove 12.

[0039] The stop step mounting surface 42 of the turbine sealing ring 4 can be matched and locked in the first arc-shaped groove 12 and the second arc-shaped groove 22, and the lower surface of the stop step mounting surface 42 is in contact with the surface of the first arc-shaped protrusion 11 and the inner wall of the first arc-shaped groove 12, and the upper surface of the stop step mounting surface 42 is in contact with the surface of the second arc-shaped protrusion 21 and the inner wall of the second arc-shaped groove 22.

[0040] The base plate 1 and the cover plate 2 are detachably connected together by a connecting structure, and the cover plate 2 is located above the base plate 1.

[0041] The second arc-shaped groove 22 corresponds vertically to the first arc-shaped protrusion 11, and the second arc-shaped protrusion 21 corresponds vertically to the first arc-shaped groove 12, thus forming a first cavity with an arc-shaped protrusion and a second cavity with an arc-shaped groove. The shape and size of the first cavity are exactly the same as the shape and size of the arc-shaped protrusion of the stop step assembly surface 42, and the shape and size of the second cavity are exactly the same as the shape and size of the arc-shaped groove of the stop step assembly surface 42. When repairing the axial dimension of the stop step assembly surface 42 of the turbine sealing ring 4, the arc-shaped protrusion of the stop step assembly surface 42 is fitted into the first cavity, and the arc-shaped groove of the stop step assembly surface 42 is fitted into the second cavity. The repair device shapes and corrects the stop step assembly surface 4, and then the dimensions of the turbine sealing ring to be repaired are stabilized by a heat treatment process, thus completing the repair of the axial dimension of the stop step assembly surface 42 of the turbine sealing ring 4.

[0042] The connecting structure serves to connect the base plate 1 and the cover plate 2, enabling the fixing and disassembly of the turbine sealing ring 4. To facilitate the use of the connecting structure, a preferred configuration of the connecting structure of this invention is as follows: (Example...) Figure 3 As shown, the connection structure includes connecting bolts 3, a first connecting hole 14 located on the outer side of the base plate 1, and a second connecting hole 24 located on the outer side of the cover plate 2. The connecting bolts 3 pass through the first connecting hole 14 and the second connecting hole 24 to detachably connect the base plate 1 and the cover plate 2 together. To further improve the connection stability and performance of the connection structure, the connection structure includes multiple connecting bolts 3, multiple first connecting holes 14, and multiple second connecting holes 24. The first connecting holes 14 are evenly distributed on the outer side of the base plate 1, and the second connecting holes 24 are evenly distributed on the outer side of the cover plate 2. Each second connecting hole 24 corresponds vertically to one first connecting hole 14. Each connecting bolt 3 passes through one first connecting hole 14 and one second connecting hole 24 to detachably connect the base plate 1 and the cover plate 2 together. The number of connecting bolts 3, first connecting holes 14, and second connecting holes 24 depends on the dimensions of the base plate 1 and the cover plate 2, and is preferably 4-6.

[0043] To facilitate the connection between the base plate 1 and the cover plate 2, and to make it easier to fix the turbine sealing ring 4, a first positioning hole 15 is provided on the outer side of the base plate 1, and a second positioning hole 25 is provided on the outer side of the cover plate 2. A positioning pin is detachably installed in the second positioning hole 25 and the first positioning hole 15. Before the connection structure is connected, it is positioned by the first positioning hole 15, the second positioning hole 25, and the positioning pin.

[0044] During the repair of the turbine seal ring 4, heat treatment is required, which is also known as high-temperature treatment. The turbine seal ring repair device for aero-engines needs to be placed in a high-temperature furnace together with the turbine seal ring 4. In order to ensure the stability of the repair device, the base plate 1 and the cover plate 2 are made of heat-resistant steel, such as 0Cr25Ni20 steel. 0Cr25Ni20 steel has good heat resistance and is easy to manufacture and form.

[0045] In order to reduce the manufacturing cost of the base plate 1 and facilitate the observation of the turbine sealing ring 4 when it is installed in the repair device, a second cylindrical relief hole 13 is provided in the center of the base plate 1, and the first cylindrical relief hole 23 and the second cylindrical relief hole 13 are vertically aligned.

[0046] The repair method for turbine sealing rings of aircraft engines includes the following steps:

[0047] a. Fabricate the aforementioned aircraft engine turbine seal ring repair device;

[0048] b. The turbine sealing ring 4 to be repaired is fixedly installed in the aircraft engine turbine sealing ring repair device. Specifically: First, the stop step assembly surface 42 of the turbine sealing ring is matched and fitted in the first arc-shaped groove 12 and the second arc-shaped groove 22, and the lower surface of the stop step assembly surface 42 is in contact with the surface of the first arc-shaped protrusion 11 and the inner wall of the first arc-shaped groove 12, and the upper surface of the stop step assembly surface 42 is in contact with the surface of the second arc-shaped protrusion 21 and the inner wall of the second arc-shaped groove 22. The main body 41 of the turbine sealing ring 4 is matched and set in the first cylindrical relief hole 23. Then, the base plate 1 and the cover plate 2 are detachably connected together through the connecting structure.

[0049] c. Stabilize the dimensions of the turbine sealing ring 4 to be repaired through heat treatment process; the heat treatment process parameters are as follows: the turbine sealing ring 4 to be repaired is put into the furnace at ≤150℃, and at least pre-evacuated to 13.3pa, heated for 70min-100min to 760℃±10℃, held for 4h-5h, and after the holding period, 2bar-3bar argon gas is introduced and cooled to below 80℃ before being taken out of the furnace.

[0050] To ensure the performance of the turbine sealing ring 4, it is made of Waspaloy alloy or GH738 alloy, with a thickness of 0.3mm. Waspaloy alloy is a precipitation-hardening nickel-based superalloy. Cobalt, chromium, and molybdenum are added for solid solution strengthening, aluminum and titanium for precipitation strengthening, and boron and zirconium for purifying and strengthening grain boundaries. It exhibits high strength at 816℃ and oxidation resistance at 954℃.

[0051] In step b, the arc-shaped protrusion of the stop step assembly surface 42 is fitted into the first cavity, and the arc-shaped groove of the stop step assembly surface 42 is fitted into the second cavity, thus the repair device performs shaping and correction on the stop step assembly surface 4. To ensure the effectiveness of the aero-engine turbine sealing ring repair device, it is pre-oxidized in an air furnace at 800°C for more than 4 hours before use, so that a high-temperature oxide film is formed on the surface, improving the anti-adhesion effect and reducing the possibility of adhesion with the turbine sealing ring 4.

[0052] When installing the turbine sealing ring 4 to be repaired, firstly, the turbine sealing ring 4 is installed along the contour of the first arc-shaped protrusion 11 and the first arc-shaped groove 12 on the inner side of the base plate 1. It is then pressed by the cover plate 2, and the positioning pins are symmetrically inserted to fix the installation position. Then, the connecting bolts 3 are fixed. First, they are pre-tightened with a wrench, and then they are tightened symmetrically. They should not be tightened all at once or asymmetrically, as this will cause the cover plate 2 to have a certain degree of tilt, which will affect the quality of deformation repair. Finally, the connecting bolts 3 are used to remove the base plate 1 and the cover plate 2, and the positioning pins are removed to avoid the positioning pins being unable to be removed after heat treatment.

[0053] To ensure the repair effect of the turbine seal ring 4, before the turbine seal ring 4 to be repaired is fixedly installed in the aircraft engine turbine seal ring repair device, an organic solvent is used to clean the turbine seal ring 4 to be repaired and the aircraft engine turbine seal ring repair device. Acetone is preferred as the organic solvent, as acetone mainly cleans the surface oil and dirt of the turbine seal ring 4 and the aircraft engine turbine seal ring repair device.

[0054] In step c, the dimensions of the turbine sealing ring 4 to be repaired are stabilized by heat treatment. After completion, the turbine sealing ring 4 is cooled to room temperature, the repair device is disassembled, the turbine sealing ring 4 is taken out, and the repaired turbine sealing ring 4 is inspected. If the inspection is qualified, it can be reused.

[0055] The L-distance dimension of the turbine sealing ring (material: Waspaloy alloy, material thickness: 0.3mm) for a certain type of aircraft engine is specified as 2.7. -0.6 mm.

[0056] Example 1

[0057] After a period of use, the L-distance dimension of the turbine sealing ring 4 of an aircraft engine is 1.98mm. The repair method of the turbine sealing ring of the aircraft engine according to the present invention includes the following steps:

[0058] a. Clean the turbine sealing ring 4 and the aircraft engine turbine sealing ring repair device with acetone;

[0059] b. Fix the turbine seal ring 4 to be repaired in the aircraft engine turbine seal ring repair device;

[0060] c. Stabilize the dimensions of the turbine sealing ring 4 to be repaired through heat treatment process; the heat treatment process parameters are as follows: the turbine sealing ring 4 to be repaired is put into the furnace at 25°C, pre-evacuated to 13.3 Pa, heated for 70 min to 760°C, held for 4 h, and after the holding period, 2 bar of argon gas is introduced to cool it to below 80°C before it is taken out of the furnace.

[0061] After the turbine sealing ring 4 cooled to room temperature, the repair device was disassembled, and the turbine sealing ring 4 was removed. The distance L was measured using a digital micrometer, and the measured value was 2.42 mm, which conforms to 2.7 mm. -0.6 The mm is fixed.

[0062] Example 2

[0063] After a period of use, the distance L of the turbine sealing ring 4 of an aircraft engine is 2.05 mm. The repair method of the turbine sealing ring of the aircraft engine according to the present invention includes the following steps:

[0064] a. Clean the turbine sealing ring 4 and the aircraft engine turbine sealing ring repair device with acetone;

[0065] b. Fix the turbine seal ring 4 to be repaired in the aircraft engine turbine seal ring repair device;

[0066] c. Stabilize the dimensions of the turbine sealing ring 4 to be repaired through heat treatment process; the heat treatment process parameters are as follows: the turbine sealing ring 4 to be repaired is put into the furnace at 24℃, pre-evacuated to 13.3pa, heated for 100min to 750℃, held for 5h, and after the holding period, 3bar argon gas is introduced and cooled to below 80℃ before being taken out of the furnace.

[0067] After the turbine seal ring 4 cooled to room temperature, the repair device was disassembled, and the turbine seal ring 4 was removed. The distance L was measured using a digital micrometer, and the measured value was 2.46 mm, which conforms to 2.7 mm. -0.6 The mm is fixed.

Claims

1. A method for repairing turbine sealing rings of aircraft engines, characterized in that, Includes the following steps: a. Fabricate an aircraft engine turbine sealing ring repair device. The aircraft engine turbine sealing ring repair device includes a base plate (1), a cover plate (2) and a connecting structure. The upper surface of the inner side of the base plate (1) is provided with a first arc-shaped protrusion (11) and a first arc-shaped groove (12), and the first arc-shaped protrusion (11) is located outside the first arc-shaped groove (12). The cover plate (2) has a first cylindrical relief hole (23) in the center. The lower surface of the inner side of the cover plate (2) has a second arc-shaped protrusion (21) and a second arc-shaped groove (22). The first arc-shaped protrusion (11) is located inside the first arc-shaped groove (12). The first arc-shaped protrusion (11) is connected to the side wall of the first cylindrical relief hole (23). The second arc-shaped groove (22) corresponds vertically to the first arc-shaped protrusion (11), and the second arc-shaped protrusion (21) corresponds vertically to the first arc-shaped groove (12). The stop step mounting surface (42) of the turbine sealing ring (4) can be matched and locked in the first arc groove (12) and the second arc groove (22), and the lower surface of the stop step mounting surface (42) is in contact with the surface of the first arc protrusion (11) and the inner wall of the first arc groove (12), and the upper surface of the stop step mounting surface (42) is in contact with the surface of the second arc protrusion (21) and the inner wall of the second arc groove (22); The base plate (1) and the cover plate (2) are detachably connected together by a connecting structure, and the cover plate (2) is located above the base plate (1); b. Fix the turbine sealing ring (4) to be repaired in the turbine sealing ring repair device for aero-engines. The turbine sealing ring (4) is made of Waspaloy alloy or GH738 alloy. The thickness of Waspaloy alloy or GH738 alloy is 0.3mm. Specifically: First, match the stop step assembly surface (42) of the turbine sealing ring in the first arc groove (12) and the second arc groove (22). The lower surface of the stop step assembly surface (42) is in contact with the surface of the first arc protrusion (11) and the inner wall of the first arc groove (12). The upper surface of the stop step assembly surface (42) is in contact with the surface of the second arc protrusion (21) and the inner wall of the second arc groove (22). The main body (41) of the turbine sealing ring (4) is matched and set in the first cylindrical relief hole (23). Then, the base plate (1) and the cover plate (2) are detachably connected together through the connecting structure. c. Stabilize the dimensions of the turbine sealing ring (4) to be repaired through heat treatment process; the heat treatment process parameters are as follows: the turbine sealing ring (4) to be repaired is placed in the furnace at ≤150 ℃, and the vacuum is pre-evacuated to at least 13.3pa. It is heated for 70min-100min to raise the temperature to 760℃±10 ℃, and held for 4h-5h. After the holding period, 2bar-3bar argon gas is introduced and cooled to below 80℃ before being taken out of the furnace.

2. The method for repairing the turbine sealing ring of an aero-engine as described in claim 1, characterized in that: Before the turbine seal ring (4) to be repaired is fixedly installed in the aircraft engine turbine seal ring repair device, the turbine seal ring (4) to be repaired and the aircraft engine turbine seal ring repair device are cleaned with organic solvent.

3. The method for repairing the turbine sealing ring of an aero-engine as described in claim 1, characterized in that: The connection structure includes a connecting bolt (3), a first connecting hole (14) on the outside of the base plate (1) and a second connecting hole (24) on the outside of the cover plate (2). The connecting bolt (3) passes through the first connecting hole (14) and the second connecting hole (24) to detachably connect the base plate (1) and the cover plate (2) together.

4. The method for repairing the turbine sealing ring of an aero-engine as described in claim 3, characterized in that: The connection structure includes multiple connecting bolts (3), multiple first connecting holes (14) and multiple second connecting holes (24). The first connecting holes (14) are evenly arranged on the outside of the base plate (1), and the second connecting holes (24) are evenly arranged on the outside of the cover plate (2). The upper and lower positions of one second connecting hole (24) correspond to one first connecting hole (14). A connecting bolt (3) is fitted through a first connecting hole (14) and a second connecting hole (24) to detachably connect the base plate (1) and the cover plate (2) together.

5. The method for repairing the turbine sealing ring of an aero-engine as described in claim 1, characterized in that: The base plate (1) and cover plate (2) are made of heat-resistant steel.

6. The method for repairing the turbine sealing ring of an aero-engine as described in claim 1, characterized in that: The base plate (1) has a first positioning hole (15) on its outer side, and the cover plate (2) has a second positioning hole (25) on its outer side. The positioning pin is detachably installed in the second positioning hole (25) and the first positioning hole (15).

7. The method for repairing the turbine sealing ring of an aero-engine as described in claim 1, characterized in that: The bottom plate (1) has a second cylindrical clearance hole (13) in the center, and the first cylindrical clearance hole (23) and the second cylindrical clearance hole (13) are positioned vertically opposite each other.

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