CN114151203A - Sealing ring connecting structure - Google Patents
Sealing ring connecting structure Download PDFInfo
- Publication number
- CN114151203A CN114151203A CN202111223599.1A CN202111223599A CN114151203A CN 114151203 A CN114151203 A CN 114151203A CN 202111223599 A CN202111223599 A CN 202111223599A CN 114151203 A CN114151203 A CN 114151203A
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- Prior art keywords
- sealing ring
- casing
- cylinder
- boss
- hole
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/28—Arrangement of seals
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
Abstract
The invention discloses a sealing ring connecting structure, belongs to the technical field of a thermal compensation device of a sealing ring and a diffuser casing made of low-expansion materials, and solves the technical problem of mismatch of thermal expansion of the sealing ring and the diffuser casing made of the low-expansion materials. The thermal compensation device is suitable for thermal compensation of a honeycomb seal structure of a labyrinth, is arranged between an outlet of a press machine and a diffuser casing of a combustion chamber, and comprises a plurality of interference threaded holes formed in a mounting surface of a seal ring, wherein each interference threaded hole is provided with a cylinder with a shape matched with each other, and the cylinder penetrates through the interference threaded hole; the diffuser casing is provided with a boss corresponding to the interference threaded hole, the boss is provided with a long round hole, and the cylinder is arranged in the long round hole and can move and compensate in a mode of mutual movement when the casing and the sealing ring are heated in an inconsistent mode.
Description
Technical Field
The invention belongs to the technical field of casing thermal compensation devices with sealing rings and combustion chamber diffusers made of low-expansion materials, and particularly relates to a connecting structure of the sealing rings.
Background
The sealing structure of the air system at the diffuser casing of the combustion chamber of the aero-engine mostly adopts a labyrinth and honeycomb structure, the labyrinth is connected with the rotor, and the honeycomb is welded on a structural member to form a sealing ring and is connected with the diffuser casing. To ensure that the thermal seal gap is within a reasonable range, the seal ring is usually made of a low expansion alloy material. When the engine works in a hot state, the radial expansion amount of the diffuser casing is larger than that of the sealing ring, so that the diffuser casing can cause the radial expansion of the sealing ring, a sealing gap is not uniform in the radial direction, and the sealing of an air system is not facilitated.
A connecting structure needs to be provided for the labyrinth honeycomb seal, and the problems of expansion difference and thermal stress between the seal ring and the diffuser casing in a thermal state are solved.
In view of the above, the present invention is particularly proposed.
Disclosure of Invention
The invention aims to provide a sealing ring connecting structure, which belongs to the technical field of sealing rings made of low-expansion materials and diffuser casing thermal compensation devices and solves the technical problem of mismatch of thermal expansion of sealing rings made of low-expansion materials and a casing made of a special material. The technical scheme of the scheme has a plurality of technical beneficial effects, which are described as follows:
the sealing ring connecting structure is arranged between an outlet of a press machine and a casing of a diffuser of a combustion chamber, solves the problem of thermal expansion mismatching of a sealing ring made of low-expansion materials and a casing made of a dissimilar material, and comprises a plurality of interference threaded holes formed in a mounting surface of the sealing ring, cylinders with mutually matched shapes are assembled in each interference threaded hole, and the cylinders penetrate through the interference threaded holes;
the sealing ring is characterized in that a boss is arranged on the casing and corresponds to the interference threaded hole, a long round hole is formed in the boss, the cylinder can move in the long round hole, and compensation is performed in a mutual moving mode when the casing and the sealing ring are heated in an inconsistent mode.
Furthermore, a boss is arranged at a position, close to the cylinder, penetrating through the long round hole, so that the axial direction of the cylinder is limited; the round column is provided with a spherical structure at a position corresponding to the long round hole, and the spherical structure prevents the round column from being assembled in the long round hole due to the inclination of a universal angle so as to play a role of a universal joint.
Compared with the prior art, the technical scheme provided by the invention has the following beneficial effects:
the low-expansion alloy sealing ring connecting structure is provided only for the labyrinth honeycomb sealing of the upper casing of the engine, the problems of expansion difference and thermal stress between the sealing ring and the diffuser casing in a thermal state can be solved, the sealing structure is novel, the principle is simple, the reliability is high, and the cold and hot state sealing requirements of the diffuser of the combustion chamber of the aero-engine can be met. The cylinder moves in the long round hole and moves along the radial direction of the casing, so that thermal compensation of the casing in a thermal state is completed.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 shows an overall assembly structure of a sealing ring according to the present invention;
FIG. 2 is a schematic view of a single connection portion of the sealing ring according to the present invention;
FIG. 3 is an exploded view of a single attachment point of the packing ring;
wherein, 1, a boss; 2. a sealing ring; 3. a spherical structure; 4. a gasket; 5. a self-locking nut; 23. a long round hole; 18. a lug.
Detailed Description
The embodiments of the present invention are described below with reference to specific embodiments, and other advantages and effects of the present invention will be easily understood by those skilled in the art from the disclosure of the present specification. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. The invention is capable of other and different embodiments and of being practiced or of being carried out in various ways, and its several details are capable of modification in various respects, all without departing from the spirit and scope of the present invention. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the disclosure, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. Additionally, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present invention, and the drawings only show the components related to the present invention rather than the number, shape and size of the components in practical implementation, and the type, quantity and proportion of the components in practical implementation can be changed freely, and the layout of the components can be more complicated.
In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that aspects may be practiced without these specific details. In order that those skilled in the art will better understand the disclosure, the invention will be described in further detail with reference to the accompanying drawings and specific embodiments. The terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
The connection structure of the sealing ring 2 shown in fig. 1 and 2 is installed between an outlet of a press machine and a casing of a diffuser of a combustion chamber, and solves the problem of thermal expansion mismatching between the sealing ring 2 made of low-expansion materials and the casing made of different materials, and comprises that a plurality of interference threaded holes are formed in the installation surface of the sealing ring 2, each interference threaded hole is provided with a cylinder with mutually matched shapes, and the cylinder penetrates through the interference threaded holes;
the boss 1 is arranged on the casing and corresponds to the interference threaded hole, the long round hole 23 is formed in the boss 1, the cylinder can move in the long round hole 23, and compensation is performed in a mutual moving mode when the casing and the sealing ring 2 are heated in an inconsistent mode. That is, the thermal compensation of the casing is accomplished by the movement of the cylinder within the oblong hole 23.
The cylinder can move in the long circular hole 23, so that the problem that the sealing ring 2 made of low-expansion material is not matched with a casing made of special material in thermal expansion can be solved, the casing does not move in a cold state, and can move in a radial direction in a hot state, namely, the cylinder moves upwards or downwards in the direction of the position shown in figure 1. Aiming at the domestic engine, the sealing ring 2 and the combustion chamber diffuser casing are made of the same material or different materials with small difference of thermal expansion coefficients, a welding or common bolt pressing structure is generally adopted, the assembly sealing is aimed at the different materials with large difference of thermal expansion systems, and because the relative displacement is large under the high-temperature environment, the structure solves the problem of thermal expansion mismatching, reduces the assembly stress, ensures the sealing performance and realizes quick installation.
As a specific embodiment provided by the present disclosure, as shown in fig. 3, a boss 1 is disposed at a position where the neighboring cylinder passes through the oblong hole 23, so as to limit the axial direction of the cylinder, promote the cylinder to move in the oblong hole 23, and avoid the situation of locking, which causes the cylinder to be unable to move in the oblong hole 23 and lose the function of thermal compensation.
And a spherical structure 3 is arranged on the cylinder and at a position corresponding to the long round hole 23, and the spherical structure 3 is a ball stud. The spherical structure 3 prevents the cylinder from being unable to fit in the oblong hole 23 due to the inclination of the universal angle, to function as a universal joint, being movable axially and radially.
As the concrete implementation mode that the present case provided, still include self-locking nut 5 and install gasket 4 on the cylinder, self-locking nut 5 is used for cooperating the ring 2 that obturages and fasten the cylinder, prevents that the cylinder from rotating, for example, the power of axial direction, lock nut gives gasket 4, and radial prevention from rotating is the frictional force between gasket 4 and the nut down prevents rotating. The gasket 4 is used for preventing the casing and the sealing ring 2 from generating relative displacement due to thermal deformation, so that the self-locking nut 5 is loosened to fasten the self-locking nut 5.
The gasket 4 is arranged in the long round hole 23, the shape of the gasket 4 is matched with that of the spherical structure 3, the long round hole 23 is arranged in the long round structure, and the long round hole 23 can move up and down along a cylinder, namely, the long round hole 23 can move in the radial direction of the casing and can move up and down by taking the direction shown in the figure as reference.
As the specific implementation mode that the present case provided, a side of gasket 4 is provided with the lug, and the lug closely contacts with lock nut, produces circumference revolving force when the engine vibrations or inflation, through lug and lock nut contact, can offset circumference revolving force, avoids lock nut not hard up for improve cylindrical fastening force.
It should be noted that, according to the structure of the present invention, the cylinder is fixed, and the sealing ring 2 is made of a low expansion material, so that the casing moves up and down along the cylinder in a thermal state, thereby performing thermal compensation on the thermal state casing.
Detailed description of the preferred embodiments
FIG. 1 is a gas turbine engine low expansion alloy sealing ring overall assembly structure, and a plurality of spherical structures 3 that are evenly distributed in the circumferential direction are assembled on a sealing ring 2 through interference threads, and the spherical structures 3 on the assembly pass through a gasket 4 arranged in a long circular hole 23 of a boss 1 and are fixed by a self-locking nut 5. 1. A boss; 2. a sealing ring; 3. a spherical structure; 4. a gasket; 5. a self-locking nut; 23. a long round hole; 18. a lug;
fig. 2 is a structural scheme of a single connecting part of a low-expansion alloy sealing ring of a gas turbine engine, and particularly describes a structural scheme that a spherical structure 3 is assembled on the sealing ring 2 through interference threads, penetrates through a gasket 4 arranged in an oblong hole 23 of a boss 1, and is fixed by a self-locking nut 5. When the spherical structure 3 is assembled, the hole step 8 of the sealing ring 2 and the middle boss 11 of the spherical structure 3 ensure that the spherical structure can be assembled at a proper position on the sealing ring through interference threads, and after the assembly, the right end face of the boss 11 of the spherical structure 3 is required to be lower than the right end matching surface of the sealing ring; the sealing ring 2 assembled with the spherical structure 3 is guided and assembled on the boss mounting edge through the radial spigot 13 of the boss 1, and the spherical structure is ensured to be assembled into the long round hole 23 of the boss without interference; the gasket 4 is sleeved from the right end of the spherical structure 3 according to the correct direction matched with the long round hole 23 of the boss 1 and is arranged between the long round hole 23 of the boss 1 and the spherical structure 3; the self-locking nut 5 is screwed and fixed from the right end of the spherical structure 3 according to the required screwing torque.
Fig. 3 depicts a detailed structure of each part of a single connection part of a low-expansion alloy sealing ring of a gas turbine engine through an explosion diagram, and the whole structure is characterized by comprising a boss 1, a low-expansion alloy sealing ring 2, a spherical structure 3, a gasket 4, a self-locking nut 5, a radial matching surface 6 of the sealing ring, an interference internal thread 7 of the sealing ring, a hole step 8 of the sealing ring, an interference external thread 9 of the spherical structure, a ball head 10 of the spherical structure, a boss 11 of the spherical structure, a common external thread 12 of the spherical structure, a radial matching surface 13 of the boss, four-corner rounding 14 of a boss slotted hole, a circumferential plane matching surface 15 of the boss slotted hole, a chamfer/rounding 16 of an external profile of the gasket, a radial end surface 17 of an external profile of the gasket, a lug 18, a circumferential plane matching surface 19 of an external profile of the gasket, and an internal cylindrical surface 20 of the gasket.
During cold assembly, firstly, the spherical structure 3 is assembled on the sealing ring 2 through interference threads in a cooling mode, the assembly position between the sealing ring orifice step 8 and the spherical structure middle boss 11 is ensured through the sealing ring orifice step 8 during assembly, and the right end face of the spherical structure boss is checked to be lower than the right end matching face of the sealing ring after assembly; then the assembly is guided and assembled on the boss mounting edge through the boss radial spigot matching surface 13, and the spherical structure 3 is ensured to be assembled into the boss long circular hole 23 without interference; then, sleeving the gasket 4 from the right end of the spherical structure 3 according to the correct direction and installing the gasket between the boss long round hole 23 and the spherical structure ball head 10; and finally, screwing and fixing the self-locking nut 5 according to the required tightening torque.
During thermal state work, because the sizes and temperatures of the boss 1 and the sealing ring 2 are close, but the thermal expansion coefficient of the mounting edge of the boss is high, and the thermal expansion coefficient of the sealing ring is low, relative displacement trend exists between the boss and the sealing ring in the radial direction, namely corresponding acting force exists. This excessive force, on the one hand, can cause the radial displacement of the packing ring to be large and deviate from the design requirements, and, on the other hand, can reduce the strength and reliability of the structure. In order to reduce and control the acting force, a radial sliding gap 21 is arranged at the joint of the two, small-gap positioning is adopted in the circumferential direction, the self-locking nut with reasonable design is used for tightening the torque, and the radial acting force is reduced while the centering of the sealing ring is ensured. Furthermore, in order to prevent the sealing ring and the boss from being relatively displaced and drive the self-locking nut to rotate to cause the locking structure to be invalid, the small clearance fit of the gasket and the circumferential direction of the boss long circular hole is designed into a plane fit structure.
The invention adopts the radial spigot matching 22 to guide assembly and assist centering during cold-state assembly, the spherical structure 3 is arranged to facilitate assembly, radial constraint is released by arranging the radial gap 21 between the boss long circular hole 23 and the gasket 4, and proper self-locking nut tightening torque is designed to ensure that the friction force generated by tightening on the boss mounting edge keeps approximate balance with the thermal-state acting force between the boss long circular hole and the gasket, the acting force can be reduced to a reasonable level, the radial deformation of the sealing ring is controlled, and the strength and the reliability of the structure are ensured; meanwhile, plane matching structures with small gaps are arranged on the boss long circular hole 23 and the two side faces of the gasket 4, so that the boss and the sealing ring still have high coaxiality when the boss and the sealing ring are subjected to radial relative displacement in a thermal state, the self-locking nut is prevented from locking failure due to rotation of the gasket, and the sealing function of the structure is finally realized.
The products provided by the present invention are described in detail above. The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the core concepts of the present invention. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the invention without departing from the inventive concept, and those improvements and modifications also fall within the scope of the claims of the invention.
Claims (6)
1. A sealing ring connecting structure is suitable for thermal compensation of a honeycomb sealing structure and is installed between an outlet of a press machine and a casing of a diffuser of a combustion chamber, and is characterized by comprising a plurality of interference threaded holes formed in the installation surface of the sealing ring, wherein cylinders with mutually adaptive shapes are assembled in each interference threaded hole, and the cylinders penetrate through the interference threaded holes;
the sealing ring is characterized in that a boss is arranged on the casing and corresponds to the interference threaded hole, a long round hole is formed in the boss, the cylinder can move in the long round hole, and compensation is performed in a mutual moving mode when the casing and the sealing ring are heated in an inconsistent mode.
2. The sealing ring connecting structure according to claim 1, wherein a boss is provided adjacent to a position where the cylinder passes through the oblong hole, so as to limit the axial direction of the cylinder;
the round column is provided with a spherical structure at a position corresponding to the long round hole, and the spherical structure prevents the round column from being assembled in the long round hole due to the inclination of a universal angle so as to play a role of a universal joint.
3. The seal ring connection structure of claim 2, further comprising a self-locking nut for engaging the seal ring to secure the cylinder.
4. The seal ring connection structure of claim 3, further comprising a gasket mounted on the cylinder for preventing relative displacement of the casing and the seal ring due to thermal deformation, so that the self-locking nut is loosened for tightening the self-locking nut.
5. The seal ring connection structure of claim 4, wherein the gasket is mounted in the oblong hole and is matched in shape to the spherical structure, the oblong hole is arranged in an oblong structure, and the oblong hole can move relative to the cylinder in a radial direction of the casing when the casing is in a hot state so as to thermally compensate the casing.
6. The packing ring connecting structure according to claim 5, wherein a lug is provided on one side of the gasket, the lug is in close contact with the lock nut, and when the engine vibrates or expands, a circumferential rotational force is generated, and by the contact of the lug with the lock nut, the circumferential rotational force can be cancelled, and the lock nut is prevented from loosening, so that the fastening force of the cylinder can be increased.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111223599.1A CN114151203B (en) | 2021-10-20 | 2021-10-20 | Sealing ring connecting structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111223599.1A CN114151203B (en) | 2021-10-20 | 2021-10-20 | Sealing ring connecting structure |
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| CN114151203A true CN114151203A (en) | 2022-03-08 |
| CN114151203B CN114151203B (en) | 2023-08-18 |
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| CN202111223599.1A Active CN114151203B (en) | 2021-10-20 | 2021-10-20 | Sealing ring connecting structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116000604A (en) * | 2022-12-31 | 2023-04-25 | 中国航发沈阳发动机研究所 | Turbine disc of aero-engine and front sealing disc assembly device and method thereof |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116000604A (en) * | 2022-12-31 | 2023-04-25 | 中国航发沈阳发动机研究所 | Turbine disc of aero-engine and front sealing disc assembly device and method thereof |
| CN116000604B (en) * | 2022-12-31 | 2023-11-28 | 中国航发沈阳发动机研究所 | Turbine disc of aero-engine and front sealing disc assembly device and method thereof |
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| Publication number | Publication date |
|---|---|
| CN114151203B (en) | 2023-08-18 |
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