CN212318096U - Self-lubricating contact type composite sealing device for high-temperature part of gas turbine engine - Google Patents
Self-lubricating contact type composite sealing device for high-temperature part of gas turbine engine Download PDFInfo
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- CN212318096U CN212318096U CN202021275329.6U CN202021275329U CN212318096U CN 212318096 U CN212318096 U CN 212318096U CN 202021275329 U CN202021275329 U CN 202021275329U CN 212318096 U CN212318096 U CN 212318096U
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- 238000007789 sealing Methods 0.000 title claims abstract description 144
- 239000002131 composite material Substances 0.000 title claims abstract description 19
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 77
- 229910002804 graphite Inorganic materials 0.000 claims abstract description 62
- 239000010439 graphite Substances 0.000 claims abstract description 62
- 230000001050 lubricating effect Effects 0.000 claims description 37
- 238000003825 pressing Methods 0.000 claims description 26
- 239000003974 emollient agent Substances 0.000 claims description 8
- 239000011248 coating agent Substances 0.000 claims description 5
- 238000000576 coating method Methods 0.000 claims description 5
- 238000007667 floating Methods 0.000 claims description 5
- 150000001875 compounds Chemical class 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 11
- 238000005461 lubrication Methods 0.000 abstract description 3
- 239000000314 lubricant Substances 0.000 description 12
- 230000009471 action Effects 0.000 description 4
- 238000009434 installation Methods 0.000 description 4
- 230000002035 prolonged effect Effects 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 3
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 125000004122 cyclic group Chemical group 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000000737 periodic effect Effects 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 238000001816 cooling Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- GUJOJGAPFQRJSV-UHFFFAOYSA-N dialuminum;dioxosilane;oxygen(2-);hydrate Chemical compound O.[O-2].[O-2].[O-2].[Al+3].[Al+3].O=[Si]=O.O=[Si]=O.O=[Si]=O.O=[Si]=O GUJOJGAPFQRJSV-UHFFFAOYSA-N 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052901 montmorillonite Inorganic materials 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
- 239000004753 textile Substances 0.000 description 1
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Abstract
The utility model discloses a gas turbine engine high temperature position's self-lubricating contact composite sealing device has solved the poor technical problem of gas turbine engine high temperature position seal structure effect in the current aerospace. The utility model discloses a set up the sealed inner ring at gas turbine engine high temperature position, sealed inner ring's periphery is provided with and compresses tightly the subassembly, compresses tightly and is provided with fingertip sealing ring and graphite lubrication piece in the subassembly, and the outer wall sliding fit of the inner wall of fingertip sealing ring and sealed inner ring compresses tightly and is provided with the elastic support piece who presses graphite lubrication piece to sealed inner ring outer wall in the subassembly. The utility model is not only simple in structure, with low costs, longe-lived, sealed validity is high moreover, sealed efficient, has overcome the great difficult problem of contact seal self-lubricating, especially has important using value at aerospace gas turbine engine hot junction position sealing orientation.
Description
Technical Field
The utility model belongs to the technical field of contact composite seal device, especially, refer to the self-lubricating contact composite seal device at gas turbine engine high temperature position.
Background
The contact type sealing is an advanced and efficient sealing method in mechanical sealing, is developed rapidly, is widely applied to industries such as military industry, dies, hydraulic pressure, textile machinery and the like, and is also commonly used in gas turbine engines in the aerospace field. The contact seal is in dynamic contact with the lining through the seal ring, so that the purpose of sealing is achieved, the advantage of reducing the air leakage area is achieved, the sealing effect is good, the applicability to materials and sealing part structures is strong, and the sealing effect is better than that of non-contact seal.
The existing contact type seal mainly comprises an expansion ring seal, a brush seal, a fingertip structure seal and the like, and the sealing process is as follows: the expansion ring, the brush type sealing assembly or the fingertip sealing piece assembly are fixed or limited on an expansion ring seat or a support ring by a pressing part, and the inner wall of the expansion ring, the inner wall of the brush type sealing assembly and the inner wall of the fingertip sealing piece are in contact with a bushing or a shaft to be sealed to form contact type sealing. In order to improve the wear resistance of the sealing structure, the bushing or the shaft is coated with a wear resistant coating, and the air leakage amount of the air flow of the sealing structure depends on the air leakage area, the pressure difference at two ends of the air leakage and the density of the air.
However, when the contact type sealing structure works, friction exists between the bushing or the shaft and the expansion ring, so that the contact type sealing structure is suitable for environments with low relative linear velocity or oil, such as oil retaining sealing of a bearing casing. Therefore, the existing contact type seal has a plurality of defects, firstly, the structure is complex, the cost is high, and the service life is limited when no lubricating environment exists; secondly, more limiting and pressing parts are needed, and sealing failure is easy to occur; thirdly, the difficulty of the manufacturing technology is high, the manufacturing technology is limited outside the aerospace system, the application range is small, and the technology maturity is low; fourthly, the limitation of the working conditions and the structures of the using parts has large requirement difference on materials and sizes, and the standardization and the serialization cannot be formed.
Disclosure of Invention
Not enough to among the above-mentioned background art, the utility model provides a gas turbine engine high temperature position's self-lubricating contact composite seal device has solved the poor technical problem of gas turbine engine high temperature position seal structure effect in the current aerospace.
The technical scheme of the utility model is realized like this: the self-lubricating contact type composite sealing device for the high-temperature part of the gas turbine engine comprises a sealing inner ring arranged at the high-temperature part of the gas turbine engine, and the sealing inner ring follows up when the high-temperature part of the gas turbine engine rotates or stretches. The periphery of the inner sealing ring is provided with a pressing assembly, a fingertip sealing ring and a graphite lubricating piece are arranged in the pressing assembly, the inner wall of the fingertip sealing ring is in sliding fit with the outer wall of the inner sealing ring, a contact type sealing structure is further formed, and an elastic supporting piece for pressing the graphite lubricating piece to the outer wall of the inner sealing ring is arranged in the pressing assembly. When the inner sealing ring is arranged on the turbine shaft, the turbine shaft and the inner sealing ring generate reciprocating axial deformation due to the thermal deformation and cold recovery of the turbine shaft, the inner sealing ring moves back and forth along with the inner sealing ring, namely the graphite lubricating piece moves relative to the outer wall of the inner sealing ring, the graphite lubricating piece is rubbed with the outer wall of the inner sealing ring under the action of the elastic supporting piece, and graphite powder falls off from the graphite lubricating piece. Graphite powder is attached to the outer surface of the inner sealing ring, and is transferred to a part where the fingertip sealing ring is in contact with the inner sealing ring through the movement or deformation circulation of the inner sealing ring, so that a lubricating layer is formed at the part. The utility model discloses not only effectively solved brush sealed, the sealed self-lubricating problem of fingertip, moreover through setting up elastic support piece, graphite lubrastrip and fingertip seal ring, effectively reduced the gas leakage area, promoted sealed effect. In addition, the sealing contact part is of an elastic structure, so that the installation difficulty is reduced; meanwhile, the service life and the reliability of fingertip sealing are improved, and the use cost is reduced.
Further, the outer surface of the sealing inner ring is provided with a wear-resistant coating, so that the service life is further prolonged.
Furthermore, the pressing assembly comprises a pressing ring surrounding the sealing inner ring, one side of the pressing ring is connected with a sealing outer ring with an L-shaped cross section, the cross section of the pressing ring after being connected with the sealing outer ring is groove-shaped, and a notch of the groove shape faces the sealing inner ring.
Furthermore, the fingertip sealing ring and the graphite lubricating piece are arranged in the groove opening, the inner wall of the fingertip sealing ring extends out of the groove opening to be in abutting connection with the outer wall of the inner sealing ring, and the graphite lubricating piece is in floating fit with the outer wall of the inner sealing ring under the abutting pressure of the elastic supporting piece.
Furthermore, the number of the fingertip sealing rings is two, the two fingertip sealing rings are arranged on two sides of the notch at intervals, and the fingertip sealing pressing ring and the graphite lubricating piece are arranged between the two fingertip sealing rings.
Further, the elastic support is arranged between the inner wall of the fingertip sealing pressing ring and the outer wall of the graphite lubricating piece.
Furthermore, the graphite lubricating piece is annular and is sleeved on the periphery of the sealing inner ring.
Furthermore, the graphite lubricating part comprises a plurality of sections of graphite blocks which are clamped with each other, so that the reliability of friction of the graphite lubricating part and the fingertip sealing ring is guaranteed, the air leakage area is effectively reduced, and the sealing effect is improved. The multi-section combined graphite lubricating piece is automatically attached to the center under the action of the elastic supporting piece, graphite powder falls off through friction, the montmorillonite ink powder is transmitted to the fingertip sealing ring through the working mode of cyclic extension of the sealing inner ring, and the self-lubricating integrated design is formed in the fingertip sealing ring and the sealing inner ring working area. The automatic centripetal adhesion of the graphite lubricating part is completely realized, the graphite is continuously rubbed to fall off, the fallen graphite powder is transferred to the contact part of the fingertip sealing ring and the inner sealing ring through the periodic displacement of the inner sealing ring, the self-lubrication of the part is formed, the automatic linkage design is realized at multiple positions, the structure is simple, the sealing is stable and reliable, and the design system has the advancement in the field.
Further, the elastic supporting piece is an elastic ring which is pressed between the inner wall of the fingertip sealing pressing ring and the outer wall of the graphite lubricating piece.
Further, when the gas turbine engine with the turbine shaft having the internal air-entraining function is used, the air-entraining holes leading to the graphite lubricating piece are formed in the side wall of the sealing inner ring, an air sealing structure can be formed between the graphite lubricating piece and the sealing inner ring, the structure is favorable for reducing the air leakage area, increasing the friction falling amount of the superfine graphite powder, increasing the transmission amount of the graphite powder to the contact positions of the fingertip sealing rings at two ends and the sealing inner ring, and reducing the interference of the multi-section combined graphite lubricating piece in a free floating state on the sealing inner ring. When the gas turbine engine is in a stable working state, the sealing system can also form a stable state, and the service life of the whole system is prolonged while the sealing effect is improved.
The utility model adopts the contact type composite seal with the self-lubricating function aiming at the high temperature part of the gas turbine engine for aerospace, an independent lubricating system is not needed, the self-lubricating system has simple and reliable structure, self-sealing property, a plurality of sealing structures are saved, and sealing failure is effectively avoided; in addition, the sealing structure is a non-rigid structure, so that the mounting in use is convenient; the sealing inner ring can move for a certain distance relatively, the use of the hot end part is more met, and the thermal deformation of parts at the inner ring installation part is effectively supported. The utility model is not only simple in structure, with low costs, longe-lived, sealed validity is high moreover, sealed efficient, has overcome the great difficult problem of contact seal self-lubricating, especially has important using value at aerospace gas turbine engine hot junction position sealing orientation.
Drawings
In order to illustrate the embodiments of the present invention more clearly, the drawings that are needed in the description of the embodiments will be briefly described below, and it is obvious that the drawings in the description below are only some embodiments of the present invention, and that other drawings can be obtained by those skilled in the art without inventive work.
FIG. 1 is a schematic sectional view of the present invention;
FIG. 2 is a sectional view of the present invention when the engine is cold;
FIG. 3 is a cross-sectional view of the present invention with the engine in a hot state;
FIG. 4 is a front view of the graphite lubricant of example 1;
FIG. 5 is a front view of the graphite lubricant of example 2;
FIG. 6 is a left side view of FIG. 5;
FIG. 7 is a front view of the resilient support;
FIG. 8 is a left side view of FIG. 7;
in the figure: 1. sealing the inner ring; 2. a wear-resistant coating; 3. a compression ring; 4. a fingertip sealing ring; 5. Sealing the outer ring; 6. a fingertip seal compression ring; 7. an elastic support member; 8. a graphite lubricant; 9. and an air guide hole.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without any creative effort belong to the protection scope of the present invention.
The periphery of sealed inner ring 1 is provided with compresses tightly the subassembly, compresses tightly and is provided with fingertip sealing ring 4 and annular graphite emollient 8 in the subassembly, and the inner wall of fingertip sealing ring 4 and the outer wall sliding fit of sealed inner ring 1 further form contact seal structure, compress tightly and be provided with in the subassembly and press graphite emollient 8 to the elastic support piece 7 of sealed inner ring 1 outer wall.
During operation, as shown in fig. 2 and 3, due to the thermal deformation and the cold recovery of the turbine shaft, the turbine shaft and the inner seal ring 1 both generate reciprocating axial deformation, the inner seal ring 1 reciprocates along with the turbine shaft, that is, the graphite lubricant piece 8 moves relative to the outer wall of the inner seal ring 1, and under the action of the elastic support piece 7, the graphite lubricant piece 8 is subjected to the pre-tightening force of the elastic support piece 7 to generate friction with the outer wall of the inner seal ring 1, so that the graphite lubricant piece 8 falls off graphite powder.
The graphite powder is attached to the outer surface of the inner sealing ring 1, and is transferred to a part where the fingertip sealing ring 4 is in contact with the inner sealing ring 1 through the movement or deformation cycle of the inner sealing ring 1, so that a lubricating layer is formed at the part. The utility model discloses not only effectively solved brush sealed, the sealed self-lubricating problem of fingertip, moreover through setting up elastic support element 7, graphite lubrastrip 8 and fingertip seal ring 4, effectively reduced the gas leakage area, promoted sealed effect. In addition, the sealing contact part is of an elastic structure, so that the installation difficulty is reduced; meanwhile, the service life and the reliability of fingertip sealing are improved, and the use cost is reduced.
Specifically, the pressing assembly comprises a pressing ring 3 surrounding the sealing inner ring 1, one side of the pressing ring 3 is connected with a sealing outer ring 5 with an L-shaped cross section, the cross section of the pressing ring 3 and the sealing outer ring 3 after connection is groove-shaped, and a groove opening of the groove shape faces the sealing inner ring 1. The fingertip sealing ring 4 and the graphite lubricating piece 8 are arranged in the groove opening, the inner wall of the fingertip sealing ring 4 extends out of the groove opening to be in abutting connection with the outer wall of the inner sealing ring 1, and the graphite lubricating piece 8 is in floating fit with the outer wall of the inner sealing ring 1 under the abutting pressure of the elastic supporting piece 7.
The number of the fingertip sealing rings 4 is two, the two fingertip sealing rings 4 are arranged on two sides of the groove opening at intervals, and the fingertip sealing pressing ring 6 and the graphite lubricating piece 8 are arranged between the two fingertip sealing rings 4. The elastic support 7 is arranged between the inner wall of the fingertip seal pressing ring 6 and the outer wall of the graphite lubricating piece 8.
Further, the outer surface of the sealing inner ring 1 is provided with the wear-resistant coating 2, so that the service life is prolonged.
Further, as shown in fig. 4, the graphite lubricant piece 8 is annular and is sleeved on the periphery of the inner sealing ring 1, so that the self-lubricating effect is improved.
The utility model discloses realized completely that graphite emollient 8 is automatic to paste tightly entad, formed contact piston ring seal structure, friction graphite drops, through sealed inner ring 1 periodic displacement, the graphite powder that the transmission drops to fingertip seal ring 4 and sealed inner ring 1 contact site, when realizing sealing, forms this position and lasts the self-lubricating. The automatic linkage design at multiple positions has the advantages of simple structure, stable and reliable sealing, and the design system has the advancement in the field.
Further, as shown in fig. 7 and 8, the elastic supporting member 7 is an elastic ring which is pressed between the inner wall of the fingertip sealing compression ring 6 and the outer wall of the graphite lubricating piece 8, and the elastic ring comprises two half rings which are buckled with each other, so that the installation and the disassembly are convenient. The amount of shedding of graphite powder can be controlled through the pretightning force of adjusting the elastic ring, and the elastic ring makes the graphite emollient 8 of multistage combination automatic centripetal the subsides tightly, realizes that graphite powder lasts to shed, guarantees that the self-lubricating function does not become invalid, and the structure has very high controllability and reliability.
Between the two fingertip seal rings 4, the graphite lubricant 8 is in a free suspension state, the pretightening force generated by the elastic support 7 is attached to the outer wall of the seal inner ring 1, and the central line of the graphite lubricant 8 coincides with the central line of the seal inner ring 1 in the axial direction. When the inner seal ring 1 deflects or deforms along with parts such as a turbine shaft of the gas turbine engine in the working state of the gas turbine engine, the graphite lubricating piece 8 with the split multi-section structure has self-adaptive capacity, deflects or deforms along with the inner seal ring 1 within the design value range of deflection or deformation allowed by the inner seal ring 1, the air leakage area is effectively reduced, and the sealing efficiency is improved.
The other structure of this embodiment is the same as embodiment 1.
In embodiment 3, when the self-lubricating contact type composite sealing device for the high-temperature portion of the gas turbine engine is used for the gas turbine engine having the turbine shaft with the internal air-entraining function, as shown in fig. 1, the air-entraining holes 9 leading to the graphite lubricant 8 are formed in the side wall of the inner seal ring 1, so that an air-sealing structure can be formed between the graphite lubricant 8 and the inner seal ring 1, and the structure is favorable for reducing the air leakage area, increasing the friction and dropping amount of the ultrafine graphite powder, increasing the transmission amount of the graphite powder to the contact positions of the fingertip seal rings 4 and the inner seal ring 1 at the two ends, and reducing the interference of the graphite lubricant 8 in the multi-section combination in the free floating state on the inner seal ring 1. When the gas turbine engine is in a stable working state, the sealing system can also form a stable state, and the service life of the whole system is prolonged while the sealing effect is improved.
The other structure of this embodiment is the same as embodiment 1 or 2.
The present invention is not exhaustive and is well known to those skilled in the art.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. Gas turbine engine high temperature position's compound sealing device of self-lubricating contact, including setting up sealed inner ring (1) at gas turbine engine high temperature position, its characterized in that: the periphery of sealed inner ring (1) is provided with compresses tightly the subassembly, compresses tightly and is provided with fingertip sealing ring (4) and graphite emollient (8) in the subassembly, and the inner wall of fingertip sealing ring (4) and the outer wall sliding fit of sealed inner ring (1) compress tightly and be provided with in the subassembly and press to elastic support piece (7) of sealed inner ring (1) outer wall with graphite emollient (8).
2. The gas turbine engine high temperature site self-lubricating contact composite seal assembly of claim 1, wherein: the outer surface of the sealing inner ring (1) is provided with a wear-resistant coating (2).
3. The gas turbine engine high-temperature portion self-lubricating contact-type composite seal device according to claim 1 or 2, characterized in that: the pressing assembly comprises a pressing ring (3) surrounding the sealing inner ring (1), one side of the pressing ring (3) is connected with a sealing outer ring (5) with an L-shaped cross section, the cross section of the pressing ring (3) and the sealing outer ring (5) after connection is groove-shaped, and the groove opening of the groove shape faces the sealing inner ring (1).
4. The gas turbine engine high temperature site self-lubricating contact composite seal assembly of claim 3, wherein: the fingertip sealing ring (4) and the graphite lubricating piece (8) are arranged in the groove opening, the inner wall of the fingertip sealing ring (4) extends out of the groove opening and is connected with the outer wall of the sealing inner ring (1) in a jacking mode, and the graphite lubricating piece (8) is in floating fit with the outer wall of the sealing inner ring (1) under the jacking pressure of the elastic supporting piece (7).
5. The gas turbine engine high temperature site self-lubricating contact composite seal assembly of claim 4, wherein: the two fingertip sealing rings (4) are arranged at intervals, the two fingertip sealing rings (4) are arranged on two sides of the groove opening, and a fingertip sealing pressing ring (6) and the graphite lubricating piece (8) are arranged between the two fingertip sealing rings (4).
6. The gas turbine engine high temperature site self-lubricating contact composite seal assembly of claim 5, wherein: the elastic supporting piece (7) is arranged between the inner wall of the fingertip sealing pressing ring (6) and the outer wall of the graphite lubricating piece (8).
7. The gas turbine engine high temperature site self-lubricating contact composite seal assembly according to any one of claims 1-2, 4-6, wherein: the graphite lubricating piece (8) is annular and is sleeved on the periphery of the sealing inner ring (1).
8. The gas turbine engine high temperature site self-lubricating contact composite seal assembly of claim 7, wherein: the graphite lubricating piece (8) comprises a plurality of sections of graphite blocks which are clamped with each other.
9. The gas turbine engine hot spot self-lubricating contact composite seal assembly according to any one of claims 1-2, 4-6, 8, wherein: the elastic supporting piece (7) is an elastic ring which is pressed between the inner wall of the fingertip sealing pressing ring (6) and the outer wall of the graphite lubricating piece (8).
10. The gas turbine engine high temperature site self-lubricating contact composite seal assembly of claim 9, wherein: and the side wall of the sealing inner ring (1) is provided with a gas introducing hole (9) leading to the graphite lubricating piece (8).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021275329.6U CN212318096U (en) | 2020-07-03 | 2020-07-03 | Self-lubricating contact type composite sealing device for high-temperature part of gas turbine engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021275329.6U CN212318096U (en) | 2020-07-03 | 2020-07-03 | Self-lubricating contact type composite sealing device for high-temperature part of gas turbine engine |
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| CN212318096U true CN212318096U (en) | 2021-01-08 |
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| CN202021275329.6U Active CN212318096U (en) | 2020-07-03 | 2020-07-03 | Self-lubricating contact type composite sealing device for high-temperature part of gas turbine engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112780775A (en) * | 2021-03-23 | 2021-05-11 | 苏州孚杰机械有限公司 | Novel high-temperature sealing device |
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2020
- 2020-07-03 CN CN202021275329.6U patent/CN212318096U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112780775A (en) * | 2021-03-23 | 2021-05-11 | 苏州孚杰机械有限公司 | Novel high-temperature sealing device |
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