Mechanism for ensuring that an aero-engine sealing ring is assembled in place and method of operation thereof

Abstract

This invention discloses a mechanism and its working method for ensuring the proper assembly of aero-engine sealing rings. The mechanism includes a base, a sealing cover, a screw, and a locking nut. The sealing cover includes an inner abutment block and an outer shell. An annular groove is provided between the inner wall of the outer shell and the outer wall of the inner abutment block. An air intake valve communicating with the annular groove is connected to the outer wall of the outer shell. One end of the screw is threaded into a threaded hole in the base, and the other end passes sequentially through a press-fitting hole connecting a casing component with a sealing ring groove, a first sealing ring, and the inner abutment block, before connecting to the locking nut. By rotating the locking nut, the first sealing ring is pressed, closing the open end of the annular groove to form a sealing cavity. Based on the original assembly operation, this invention arranges a sealing cavity on the opposite side of the contact surface. By introducing air into the sealing cavity, axial gas force is applied to the sealing ring in the gap to return it to its original position, ensuring the consistency of the sealing state at the time of engine delivery with the operating state, and improving sealing reliability.

Description

Technical Field

[0001] This invention relates to the field of aircraft engine sealing, and in particular, to a mechanism and its working method for ensuring that an aircraft engine sealing ring is properly assembled. Background Technology

[0002] Sealing devices are a crucial component of aero engines, with rubber ring seals being an important type of engine sealing structure. When installing grooved parts and sealing rings into holes, lubricant is typically applied only to the inner wall of the hole and the rubber ring, and then manually or with external force is used to tighten them. However, due to differences in the fit dimensions between the rubber ring and the hole, the compression ratio varies. Especially for rubber rings with a larger compression ratio, when axial force is applied to cause axial displacement, the cross-section of the rubber ring is no longer elliptical but rather an abnormally tilted teardrop shape. That is, the axial distance from the part of the rubber ring that contacts the groove to the mating surface is less than the axial distance from the part of the rubber ring that contacts the hole to the mating surface. After initial assembly, operators and inspectors may assume that the assembly is in place. However, during engine operation, due to factors such as vibration, the axial position of the rubber ring and the two contact parts may gradually change. The rubber ring, which is in an abnormal assembly state, tilted, or teardrop-shaped, will gradually return to its normal elliptical position through axial displacement. This axial displacement will cause the original assembly pressing surfaces to no longer fit together, resulting in an increased gap between the mating surfaces. Furthermore, as the rubber ring gradually transforms into an elliptical shape, the central axis of grooved parts will become misaligned, leading to weakened or even failed end-face sealing effects and other malfunctions. Summary of the Invention

[0003] The purpose of this invention is to provide a mechanism and its working method for ensuring that the sealing ring of an aero-engine is properly assembled. With the above mechanism, the compressed and tilted elliptical ring can be moved to a normal working state, preventing the failure of sealing caused by the gradual return of the improperly assembled parts with the ring groove during use, thus improving the reliability of the seal.

[0004] The above-mentioned objective of the present invention is achieved through the following technical solution:

[0005] A mechanism for ensuring the proper assembly of a sealing ring for an aircraft engine includes a base, a sealing cover, a screw, a locking nut, and a casing component with a sealing ring groove clamped between the base and the sealing cover.

[0006] The sealing cover includes an inner abutment block and an outer cover. One end of the outer cover is integrally sealed and connected to the inner abutment block, and the other end protrudes from the inner abutment block to form an insertion interface. An annular groove is provided between the inner wall of the outer cover and the outer wall of the inner abutment block. An air intake valve communicating with the annular groove is connected to the outer wall of the outer cover.

[0007] The base has a threaded hole in the middle that mates with the screw, and the inner abutment block has a pressurized through hole in the middle for the screw to pass through. When the insertion interface of the outer cover is covered on the outer wall of the casing, the end face of the inner abutment block abuts against the end face of the part. A first sealing ring is provided between the end face of the inner abutment block and the end face of the part, and a second sealing ring is provided between the inner wall of the insertion interface and the outer wall of the casing.

[0008] One end of the screw is threaded to the threaded hole, and the other end passes sequentially through the casing component with the rubber ring groove, the first sealing ring, and the crimping through hole before connecting to the locking nut. By rotating the locking nut, the first sealing ring is pressed to close the opening end of the ring groove to form a sealing cavity.

[0009] Furthermore, the outer wall of the base is provided with a positioning plate, the outer diameter of which is larger than the mounting hole diameter of the casing. The positioning plate abuts against the outer wall of the casing. The end of the base facing the sealing cover is provided with a reduced diameter positioning section, which extends into the mounting hole of the casing for positioning.

[0010] Furthermore, the outer wall of the end of the casing connected to the sealing cover insertion interface is provided with an annular mounting groove, and the second sealing ring is embedded in the annular mounting groove.

[0011] The above-described mechanism for ensuring the proper assembly of the aircraft engine sealing ring includes the following steps:

[0012] A. Manually assemble the parts with the rubber ring grooves onto the casing. The sealing rubber ring on the outer wall of the parts should be tightly attached to the inner wall of the casing assembly position. A second sealing ring should be fitted on the outer wall at the position where the casing and the outer cover interlock.

[0013] B. Place the base against the outer wall of the casing, pass the screw through the inner abutment block and connect it to the threaded hole of the base. The first sealing ring is located between the part with the rubber ring groove and the abutment block. The insertion interface of the outer cover is covered on the inner end cylinder wall of the casing. The insertion interface is sealed with the casing by the second sealing ring. Rotate the locking nut to the end face of the part that needs to be pressed until it can no longer be pressed. The opening of the annular groove is closed to form a sealing cavity.

[0014] C. Gas at a certain pressure is introduced into the sealing cavity through the air inlet valve, and the gas pressure causes the sealing ring on the part to return to its normal position.

[0015] The technical effects of this invention are as follows: Based on the original assembly operation, this invention arranges a sealing cavity on the opposite side of the contact surface, and uses the method of air intake into the sealing cavity to ensure that axial gas force is applied to the rubber ring in the gap, so that the cross section of the rubber ring deformed during the original assembly gradually produces axial displacement, so that the rubber ring returns to its normal elliptical state, ensuring that it will not return to its original position due to abnormal deformation caused by the early assembly during the later engine operation, thus ensuring the consistency between the sealing state at the time of engine delivery and the operating state.

[0016] By applying axial force to a small gap between the shaft and bore after normal assembly, the sealing effect is improved. Gas pressure is used to move any misaligned rubber rings to their proper axial position. This avoids discrepancies between the sealing condition of the engine's delivered seals and their usage condition, reduces the occurrence of weakened sealing performance or even leakage, ensures stable engine operation, and contributes to the company's development. Attached Figure Description

[0017] Figure 1 This is a front structural diagram of the present invention.

[0018] Figure 2 This is a schematic diagram of the rear structure of the present invention.

[0019] Figure 3 yes Figure 2 A schematic diagram of the cross-sectional structure along the middle AA.

[0020] In the diagram, 1. Base; 11. Threaded hole; 12. Positioning plate; 13. Reduced diameter positioning section; 2. Sealing cover; 21. Inner abutment block; 211. Press-fit through hole; 22. Outer cover; 221. Insertion interface; 23. Annular groove; 3. Locking nut; 4. Screw; 5. Intake valve; 6. Casing; 61. Assembly hole; 62. Annular mounting groove; 7. Part; 71. Sealing ring; 8. First sealing ring; 9. Second sealing ring. Detailed Implementation

[0021] The present invention will now be described in detail with reference to the accompanying drawings. These drawings are simplified schematic diagrams, illustrating only the basic structure of the invention, and therefore only show the components relevant to the invention.

[0022] Reference Figures 1 to 3 The present invention discloses a mechanism for ensuring the proper assembly of the sealing ring 71 of an aircraft engine, comprising a base 1, a sealing cover 2, a screw 4, and a locking nut 3, wherein a casing 6 component with a sealing ring groove 7 is clamped between the base 1 and the sealing cover 2.

[0023] The sealing cover 2 includes an inner abutment block 21 and an outer cover 22. One end of the outer cover 22 is integrally sealed and connected to the inner abutment block 21, and the other end protrudes from the inner abutment block 21 to form an insertion interface 221. An annular groove 23 is provided between the inner wall of the outer cover 22 and the outer wall of the inner abutment block 21, and an air intake valve 5 communicating with the annular groove 23 is connected to the outer wall of the outer cover 22.

[0024] The base 1 has a threaded hole 11 in the middle that mates with the screw 4, and the inner abutment block 21 has a pressurized through hole 211 in the middle for the screw 4 to pass through. When the insertion interface 221 of the outer cover 22 is placed on the outer wall of the casing 6, the end face of the inner abutment block 21 abuts against the end face of the part 7. A first sealing ring 8 is provided between the end face of the inner abutment block 21 and the end face of the part 7, and a second sealing ring 9 is provided between the inner wall of the insertion interface 221 and the outer wall of the casing 6. One end of the screw 4 is threadedly connected to the threaded hole 11, and the other end passes sequentially through the casing 6 component with the rubber ring groove 7, the first sealing ring 8, and the pressurized through hole 211 before connecting to the locking nut 3. By rotating the locking nut 3, the first sealing ring 8 is pressed, thereby closing the open end of the annular groove 23 to form a sealed cavity.

[0025] Furthermore, the outer wall of the base 1 is provided with a positioning plate 12. The outer diameter of the positioning plate 12 is larger than the diameter of the mounting hole 61 of the casing 6. The positioning plate 12 abuts against the outer wall of the casing 6. The end of the base 1 facing the sealing cover 2 is provided with a reduced diameter positioning section 13. The reduced diameter positioning section 13 extends into the mounting hole 61 of the casing 6 for positioning.

[0026] Furthermore, the outer wall of the end of the casing 6 connected to the housing insertion interface 221 of the sealing cover 2 is provided with an annular mounting groove 62, and the second sealing ring 9 is embedded in the annular mounting groove 62.

[0027] The above-described mechanism for ensuring the proper assembly of the aircraft engine sealing ring 71 includes the following steps:

[0028] A. Manually assemble the part 7 with the rubber ring groove onto the housing 6. The sealing rubber ring 71 on the outer wall of the part 7 is tightly attached to the inner wall of the assembly position of the housing 6. A second sealing ring 9 is fitted on the outer wall at the position where the housing 6 mates with the insertion interface 221 of the outer cover 22.

[0029] B. Place the base 1 against the outer wall of the casing 6, pass the screw 4 through the inner abutment block 21 and thread it into the threaded hole 11 of the base 1. The first sealing ring 8 is located between the part 7 with the rubber ring groove and the abutment block. The insertion interface 221 of the outer cover 22 is covered on the inner end wall of the casing 6. The insertion interface 221 and the casing 6 are sealed by the second sealing ring 9. Rotate the locking nut 3 to the end face of the part 7 that needs to be pressed until it can no longer be pressed. The opening of the annular groove 23 is closed to form a sealed cavity.

[0030] C. Gas of a certain pressure is introduced into the sealing cavity through the air inlet valve 5, and the gas pressure causes the sealing ring 71 on the part 7 to return to its normal position.

[0031] Based on the original assembly operation, this invention arranges a sealing cavity on the opposite side of the contact surface and uses the method of air intake into the sealing cavity to ensure that axial gas force is applied to the rubber ring in the gap. This causes the cross-section of the rubber ring, which was deformed during the original assembly, to gradually produce axial displacement, so that the rubber ring returns to its normal elliptical state. This ensures that the engine will not return to its original position due to abnormal deformation caused by the early assembly during the later operation, thus ensuring the consistency between the sealing state at the time of engine delivery and the state of use.

[0032] The implementation principle of this embodiment is as follows: In order to ensure that the rubber ring does not deform or return to its original position after the engine is assembled and used, after the part 7 with the rubber ring groove is manually assembled, the base 1 is placed against the casing 6, the screw 4 is passed through the base 1, the sealing ring is located between the part 7 with the rubber ring groove and the abutment block, the nut is rotated to the end face of the part 7 that needs to be pressed until it can no longer be tightened; at the same time, air is introduced into the air inlet of the sealing cover 2 housing, and the gas pressure is used to make the rubber ring return to its original position.

[0033] The embodiments described herein are preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Therefore, all equivalent changes made in accordance with the structure, shape, and principle of the present invention should be covered within the scope of protection of the present invention.

Claims

1. A mechanism for ensuring that an aeroengine seal packing is fitted in place, characterised in that: The casing assembly, which includes a base, a sealing cover, a screw, a locking nut, and a housing component with a rubber ring groove, is clamped between the base and the sealing cover. The sealing cover includes an inner abutment block and an outer cover. One end of the outer cover is integrally sealed and connected to the inner abutment block, and the other end protrudes from the inner abutment block to form an insertion interface. An annular groove is provided between the inner wall of the outer cover and the outer wall of the inner abutment block. An air intake valve communicating with the annular groove is connected to the outer wall of the outer cover. The base has a threaded hole in the middle that mates with the screw, and the inner abutment block has a crimping through hole in the middle for the screw to pass through. When the insertion interface of the outer cover is covered on the outer wall of the casing, the end face of the inner abutment block abuts against the end face of the part. A first sealing ring is provided between the end face of the inner abutment block and the end face of the part, and a second sealing ring is provided between the inner wall of the insertion interface and the outer wall of the casing. One end of the screw is threaded to the threaded hole, and the other end passes sequentially through the casing component with the rubber ring groove, the first sealing ring, and the crimping through hole before connecting to the locking nut. By rotating the locking nut, the first sealing ring is pressed to close the opening end of the ring groove to form a sealing cavity.

2. The mechanism to ensure the aero-engine seal packing is assembled in place according to claim 1, characterized in that: The outer wall of the base is provided with a positioning plate. The outer diameter of the positioning plate is larger than the diameter of the mounting hole of the casing. The positioning plate abuts against the outer wall of the casing. The end of the base facing the sealing cover is provided with a reduced diameter positioning section. The reduced diameter positioning section extends into the mounting hole of the casing for positioning.

3. The mechanism to ensure the aero-engine seal packing is assembled in place of claim 1, wherein: The outer wall of the end of the casing that is connected to the sealing cover insertion interface is provided with an annular mounting groove, and the second sealing ring is embedded in the annular mounting groove.

4. A method for operating a mechanism to ensure the proper assembly of an aircraft engine sealing ring as described in any one of claims 1-3, characterized in that, Includes the following steps: A. Manually assemble the parts with rubber ring grooves onto the casing. The sealing rubber ring on the outer wall of the parts should be tightly attached to the inner wall of the casing assembly position. A second sealing ring should be fitted on the outer wall at the position where the casing and the outer cover interlock. B. Place the base against the outer wall of the casing, pass the screw through the inner abutment block and connect it to the threaded hole of the base. The first sealing ring is located between the part with the rubber ring groove and the inner abutment block. The insertion interface of the outer cover is covered on the inner end wall of the casing. The insertion interface is sealed with the casing by the second sealing ring. Rotate the locking nut to the end face of the part that needs to be pressed until it can no longer be pressed. The opening of the annular groove is closed to form a sealing cavity. C. Gas at a certain pressure is introduced into the sealing cavity through the air inlet valve, and the gas pressure causes the sealing ring on the part to return to its normal position.

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