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CN-117324885-B - Repair device and repair method for turbine sealing ring of aero-engine

CN117324885BCN 117324885 BCN117324885 BCN 117324885BCN-117324885-B

Abstract

The invention relates to the technical field of aero-engines, in particular to a repair device and a repair method for a turbine sealing ring of an aero-engine, which comprises a bottom plate, a cover plate and a connecting structure, wherein the upper surface of the inner side of the bottom plate is provided with a circle of first arc-shaped bulges and a circle of first arc-shaped grooves, the middle of the cover plate is provided with a first cylindrical abdication hole, the lower surface of the inner side of the cover plate is provided with a circle of second arc-shaped bulges and a circle of second arc-shaped grooves, the second arc-shaped grooves correspond to the upper and lower positions of the first arc-shaped bulges, and the second arc-shaped bulges correspond to the upper and lower positions of the first arc-shaped grooves. The axial dimension of the stop step assembly surface of the turbine sealing ring is shaped and corrected, and the dimension of the turbine sealing ring to be repaired is stabilized through a heat treatment process, so that the axial dimension of the stop step assembly surface of the turbine sealing ring is repaired, the turbine sealing ring can be reused, the service time of the turbine sealing ring is prolonged, and the running cost of an aeroengine is reduced.

Inventors

  • DU YUAN
  • YANG BIN
  • PAN GANG
  • Leng Shaobo
  • REN ZHIYONG
  • WU KE

Assignees

  • 国营川西机器厂

Dates

Publication Date
20260505
Application Date
20231120

Claims (7)

  1. 1. The repair method of the turbine sealing ring of the aeroengine is characterized by comprising the following steps of: a. Manufacturing an aeroengine turbine sealing ring repairing device, wherein the aeroengine turbine sealing ring repairing device comprises a bottom plate (1), a cover plate (2) and a connecting structure, a circle of first arc-shaped protrusions (11) and a circle of first arc-shaped grooves (12) are arranged on the upper surface of the inner side of the bottom plate (1), and the first arc-shaped protrusions (11) are positioned on the outer side of the first arc-shaped grooves (12); a first cylindrical yielding hole (23) is formed in the middle of the cover plate (2), a circle of second arc-shaped protrusions (21) and a circle of second arc-shaped grooves (22) are formed in the lower surface of the inner side of the cover plate (2), the first arc-shaped protrusions (11) are located on the inner side of the first arc-shaped grooves (12), and the first arc-shaped protrusions (11) are connected with the side wall of the first cylindrical yielding hole (23); The second arc-shaped groove (22) corresponds to the upper and lower positions of the first arc-shaped bulge (11), and the second arc-shaped bulge (21) corresponds to the upper and lower positions of the first arc-shaped groove (12); The stop step assembly surface (42) of the turbine sealing ring (4) can be matched and clamped in the first arc-shaped groove (12) and the second arc-shaped groove (22), the lower surface of the stop step assembly surface (42) is abutted against the surface of the first arc-shaped bulge (11) and the inner wall of the first arc-shaped groove (12), and the upper surface of the stop step assembly surface (42) is abutted against the surface of the second arc-shaped bulge (21) and the inner wall of the second arc-shaped groove (22); the bottom plate (1) and the cover plate (2) are detachably connected together through a connecting structure, and the cover plate (2) is positioned above the bottom plate (1); b. The method comprises the steps of fixedly mounting a turbine sealing ring (4) to be repaired in an aircraft engine turbine sealing ring repairing device, wherein the turbine sealing ring (4) is made of waspaloy alloy or GH738 alloy, the waspaloy alloy or GH738 alloy has the thickness of 0.3mm, specifically, firstly, matching and clamping a stop step assembly surface (42) of the turbine sealing ring in a first arc-shaped groove (12) and a second arc-shaped groove (22), wherein the lower surface of the stop step assembly surface (42) is abutted against the surface of a first arc-shaped bulge (11) and the inner wall of the first arc-shaped groove (12), the upper surface of the stop step assembly surface (42) is abutted against the surface of a second arc-shaped bulge (21) and the inner wall of the second arc-shaped groove (22), and then, detachably connecting a bottom plate (1) and a cover plate (2) together through a connecting structure; c. The size of the turbine sealing ring (4) to be repaired is stabilized through a heat treatment process, wherein the heat treatment process parameters are as follows, the turbine sealing ring (4) to be repaired is put into a furnace at a temperature of less than or equal to 150 ℃, at least is pre-vacuumized to 13.3pa, heated for 70min-100min, heated to 760 ℃ plus or minus 10 ℃, kept for 4h-5h, and then is filled with argon of 2bar-3bar to be cooled to below 80 ℃ and discharged.
  2. 2. The method for repairing a turbine seal ring of an aircraft engine according to claim 1, wherein the turbine seal ring (4) to be repaired and the turbine seal ring repairing device of the aircraft engine are cleaned by an organic solvent before the turbine seal ring (4) to be repaired is fixedly installed on the turbine seal ring repairing device of the aircraft engine.
  3. 3. The method for repairing the turbine sealing ring of the aeroengine as claimed in claim 1, wherein the connecting structure comprises a connecting bolt (3), a first connecting hole (14) arranged on the outer side of the base plate (1) and a second connecting hole (24) arranged on the outer side of the cover plate (2), and the connecting bolt (3) penetrates through the first connecting hole (14) and the second connecting hole (24) in a matching mode to detachably connect the base plate (1) and the cover plate (2) together.
  4. 4. The method for repairing the turbine sealing ring of the aeroengine as claimed in claim 3, wherein the connecting structure comprises a plurality of connecting bolts (3), a plurality of first connecting holes (14) and a plurality of second connecting holes (24), the first connecting holes (14) are uniformly arranged on the outer side of the bottom plate (1), the second connecting holes (24) are uniformly arranged on the outer side of the cover plate (2), and one second connecting hole (24) corresponds to one first connecting hole (14) in the upper and lower positions; A connecting bolt (3) passes through a first connecting hole (14) and a second connecting hole (24) in a matching way to detachably connect the bottom plate (1) and the cover plate (2) together.
  5. 5. A repair method for turbine sealing rings of aeroengines as claimed in claim 1, characterized in that the base plate (1) and the cover plate (2) are made of heat-resistant steel.
  6. 6. The repair method of the turbine sealing ring of the aeroengine, as set forth in claim 1, is characterized in that a first positioning hole (15) is formed on the outer side of the bottom plate (1), a second positioning hole (25) is formed on the outer side of the cover plate (2), and the positioning pin is detachably arranged in the second positioning hole (25) and the first positioning hole (15).
  7. 7. The repair method of the turbine sealing ring of the aeroengine as claimed in claim 1, wherein a second cylindrical yielding hole (13) is formed in the middle of the base plate (1), and the first cylindrical yielding hole (23) corresponds to the second cylindrical yielding hole (13) in upper and lower positions.

Description

Repair device and repair method for turbine sealing ring of aero-engine Technical Field The invention relates to the technical field of aeroengines, in particular to a repair device and a repair method for a turbine sealing ring of an aeroengine. Background As shown in fig. 1 and 2, the turbine seal ring of a certain aeroengine comprises a main body 41 and a stop step assembly surface 42, wherein the stop step assembly surface 42 is arranged on the outer side of the main body 41 in a connecting way, and the turbine seal ring is generally made of waspaloy alloy or GH738 alloy, and the thickness of waspaloy alloy or GH738 alloy is 0.3mm. The stop step assembly surface 42 is formed by a circle of arc-shaped bulges and a circle of arc-shaped grooves which are connected together, the longest distance between the arc-shaped bulges and the arc-shaped grooves is L, and in the operation process of the aeroengine, the turbine sealing ring is extruded and jogged for a long time to cause axial elastic attenuation, so that the axial dimension of the stop step assembly surface 42 of the turbine sealing ring is reduced, namely the L dimension shown in fig. 2 is reduced, the axial dimension of the stop step assembly surface 42 of the turbine sealing ring is reduced, the tightness of the turbine guide and the turbine guide shell is reduced, and meanwhile, the effectiveness of axial positioning is difficult to ensure. At present, there is no effective repairing device and repairing method for repairing the turbine sealing ring, so that the turbine sealing ring with the smaller axial dimension of the stop step assembly surface 42 cannot be repaired, only can be scrapped, the operation cost of the aeroengine is increased, and the resource utilization rate is lower. Disclosure of Invention The technical problem solved by the invention is to provide the aeroengine turbine sealing ring repairing device capable of repairing the aeroengine turbine sealing ring. The technical scheme adopted by the invention for solving the technical problems is that the aero-engine turbine sealing ring repairing device comprises a bottom plate, a cover plate and a connecting structure, wherein the upper surface of the inner side of the bottom plate is provided with a circle of first arc-shaped bulges and a circle of first arc-shaped grooves, and the first arc-shaped bulges are positioned at the outer sides of the first arc-shaped grooves; The middle of the cover plate is provided with a first cylindrical abdication hole, the lower surface of the inner side of the cover plate is provided with a circle of second arc-shaped bulges and a circle of second arc-shaped grooves, the first arc-shaped bulges are positioned on the inner side of the first arc-shaped grooves, and the first arc-shaped bulges are connected with the side wall of the first cylindrical abdication hole; The second arc-shaped groove corresponds to the upper and lower positions of the first arc-shaped bulge, and the second arc-shaped bulge corresponds to the upper and lower positions of the first arc-shaped groove; the stop step assembly surface of the turbine sealing ring can be matched and clamped in the first arc-shaped groove and the second arc-shaped groove, the lower surface of the stop step assembly surface is abutted against the surface of the first arc-shaped bulge and the inner wall of the first arc-shaped groove, and the upper surface of the stop step assembly surface is abutted against the surface of the second arc-shaped bulge and the inner wall of the second arc-shaped groove; the bottom plate and the cover plate are detachably connected together through a connecting structure, and the cover plate is positioned above the bottom plate. Further, the connecting structure comprises a connecting bolt, a first connecting hole arranged on the outer side of the bottom plate and a second connecting hole arranged on the outer side of the cover plate, and the connecting bolt penetrates through the first connecting hole and the second connecting hole in a matched mode to detachably connect the bottom plate and the cover plate together. Further, the connecting structure comprises a plurality of connecting bolts, a plurality of first connecting holes and a plurality of second connecting holes, wherein the first connecting holes are uniformly arranged on the outer side of the bottom plate, the second connecting holes are uniformly arranged on the outer side of the cover plate, and one second connecting hole corresponds to the upper and lower positions of one first connecting hole; A connecting bolt passes through a first connecting hole and a second connecting hole in a matching way to detachably connect the bottom plate and the cover plate together. Further, the bottom plate and the cover plate are made of heat-resistant steel. Further, be provided with first locating hole on the outside of bottom plate, be provided with the second locating hole on the outside of apron, the locating pin