CN117249000A - Lubricating oil sealing system of gas turbine - Google Patents
Lubricating oil sealing system of gas turbine Download PDFInfo
- Publication number
- CN117249000A CN117249000A CN202311195421.XA CN202311195421A CN117249000A CN 117249000 A CN117249000 A CN 117249000A CN 202311195421 A CN202311195421 A CN 202311195421A CN 117249000 A CN117249000 A CN 117249000A
- Authority
- CN
- China
- Prior art keywords
- shell
- air
- housing
- rear end
- gas turbine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000007789 sealing Methods 0.000 title claims abstract description 25
- 239000010687 lubricating oil Substances 0.000 title claims abstract description 23
- 244000126211 Hericium coralloides Species 0.000 claims abstract description 20
- 239000010723 turbine oil Substances 0.000 claims description 4
- 238000009826 distribution Methods 0.000 claims 1
- 239000003921 oil Substances 0.000 abstract description 10
- 239000007789 gas Substances 0.000 description 14
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 4
- 229910002804 graphite Inorganic materials 0.000 description 3
- 239000010439 graphite Substances 0.000 description 3
- 230000001939 inductive effect Effects 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004939 coking Methods 0.000 description 1
- 230000002542 deteriorative effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000005272 metallurgy Methods 0.000 description 1
- 239000010705 motor oil Substances 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
-
- 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
- F02C7/06—Arrangements of bearings; Lubricating
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
- F01D25/183—Sealing means
-
- 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
Abstract
The invention provides a lubricating oil sealing system of a gas turbine, which comprises a main gas-introducing pipe, a front shell, a middle shell, a front shell A, a front shell B, a middle shell, a wheel disc, a secondary gas-introducing pipe, a front end comb tooth seal and a rear end comb tooth seal, wherein the front end comb tooth seal is arranged on the front shell B; the main gas-introducing pipe is connected with the middle shell and the middle housing; the secondary air-entraining pipe is arranged at the bypass of the main air-entraining pipe and is connected between two comb teeth seals at the rear end of the oil-lubricating cavity, and air with certain pressure is supplied to the rear end of the oil-lubricating cavity through the secondary air-entraining pipe; the front shell is connected with the middle shell; the front housing is provided with a front housing A and a front housing B on the outer side, and a main air bleed pipe and an internal air bleed flow path supply air with certain pressure to the front end of the oil slide cavity; the front end and the rear end of the lubricating oil cavity are respectively provided with a front end comb tooth seal and a rear end comb tooth seal. The invention has simple structure, is not easy to damage, does not need to replace parts, can stably run for a long time, and improves the safety and the economy of the unit.
Description
Technical Field
The invention belongs to the field of gas turbine lubricating oil sealing, and particularly relates to a gas turbine lubricating oil sealing system.
Background
The gas turbine has the advantages of high power density, high starting speed, flexible fuel and the like, is widely applied to the fields of power generation of industrial and offshore platforms, natural gas transportation, petrochemical industry, metallurgy and the like, and can also be used as a main power device of an airplane, a ship and a ground vehicle.
Modern high performance gas turbines employ bearings to balance the shaft support and component axial forces. The gas turbine uses lubricating oil to lubricate the bearing, and a sealing structure is needed to be used in the lubricating oil cavity so as to prevent the lubricating oil from leaking, deteriorating and coking. At present, the gas turbine is tightly sealed with the movable ring by installing graphite sealing rings at two ends of the lubricating oil cavity, the graphite sealing rings are in extrusion friction with the movable ring, the gas turbine is easy to damage and needs to be replaced regularly, the working state of the graphite rings is greatly influenced by the pressure difference at two sides, and the pressure difference at two sides is small when the gas turbine runs under low working conditions, so that the lubricating oil is easy to leak. Therefore, the lubricating oil sealing system is designed simply and efficiently, and has important significance for safe and efficient operation.
Disclosure of Invention
The invention aims to provide a gas turbine lubricating oil sealing system which supplies air with certain pressure to the front end of a lubricating oil cavity through a main air-guiding pipe and an internal air-guiding flow path, supplies air with certain pressure to the rear end of the lubricating oil cavity through a secondary air-guiding pipe, and arranges two or more comb teeth for sealing at two ends so as to realize sealing of the lubricating oil cavity.
A lubricating oil sealing system of a gas turbine comprises a main gas-introducing pipe, a front shell, a middle shell, a front shell A, a front shell B, a middle shell, a wheel disc, a secondary gas-introducing pipe, a front end comb tooth seal and a rear end comb tooth seal; the main gas-introducing pipe is connected with the middle shell and the middle housing; the secondary air-entraining pipe is arranged at the bypass of the main air-entraining pipe and is connected between two comb teeth seals at the rear end of the oil-lubricating cavity, and air with certain pressure is supplied to the rear end of the oil-lubricating cavity through the secondary air-entraining pipe; the front shell is connected with the middle shell; the front housing is provided with a front housing A and a front housing B on the outer side, and a main air bleed pipe and an internal air bleed flow path supply air with certain pressure to the front end of the oil slide cavity; the front end and the rear end of the lubricating oil cavity are respectively provided with a front end comb tooth seal and a rear end comb tooth seal.
Further, the intermediate housing and the intermediate housing form an axial inboard bleed air flow path, and the front housing a and the front housing B form a radial inboard bleed air flow path.
Further, axial through holes are uniformly distributed in the circumferential directions of the front shell and the middle shell, and the diameters, positions and angles of the through holes of the front shell and the middle shell are consistent.
Further, radial through holes are circumferentially and uniformly distributed in the front part of the front shell.
Further, the front cover shell A and the front cover shell B are circumferentially and uniformly distributed with through holes.
Further, the wheel disc forms a closed chamber with the front cover a and the front cover B.
Further, the front end comb tooth seal and the rear end comb tooth seal are not less than two.
The invention has the beneficial effects that: compared with the mode that graphite sealing rings and movable rings are arranged at two ends of an oil sliding cavity to seal the oil sliding, the invention supplies air with certain pressure to the front end of the oil sliding cavity through the main air-guiding pipe and the built-in air-guiding flow path, supplies air with certain pressure to the rear end of the oil sliding cavity through the secondary air-guiding pipe, and arranges two or more comb teeth for sealing at two ends so as to realize the sealing of the oil sliding cavity and prevent the leakage of the oil sliding. The invention has simple structure, is not easy to damage, does not need to replace parts, can stably run for a long time, and improves the safety and the economy of the unit.
Drawings
FIG. 1 is a schematic diagram of a gas turbine engine oil system according to the present invention;
FIG. 2 is an enlarged view of a portion of the seal structure at the front end of the oil-lubricated cavity of the present invention, shown at position 11 in FIG. 1;
FIG. 3 is an enlarged view of a portion of the rear seal of the oil-bearing chamber of the present invention at position 12 of FIG. 1.
In the figure: 1-main air-inducing pipe, 2-middle housing, 3-middle housing, 4-front housing, 5-front housing A, 6-front housing B, 7-wheel disc, 8-shaft, 9-secondary air-inducing pipe, 10-rear housing, 11-front end seal and 12-rear end seal.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
As shown in fig. 1-3, a gas turbine oil seal system includes a main bleed duct 1, a front casing 4, a middle casing 3, a front casing A5, a front casing B6, a middle casing 2, a disk 7, a secondary bleed duct 9, a front end comb seal 11, and a rear end comb seal 12; the main gas-introducing pipe 1 is connected with the middle shell 3 and the middle housing 2; the secondary air-guiding pipe 9 is arranged at the bypass of the main air-guiding pipe 1 and is connected between two comb teeth seals at the rear end of the oil-sliding cavity, and air with certain pressure is supplied to the rear end of the oil-sliding cavity through the secondary air-guiding pipe 9 to play a role in sealing gas; the front shell 4 is connected with the middle shell 3; the front housing 4 is provided with a front housing A5 and a front housing B6 at the outer side, and the main air bleed pipe 1 and the built-in air bleed flow path supply air with certain pressure to the front end of the oil slide cavity; the front end and the rear end of the oil-sliding cavity are respectively provided with a front end comb tooth seal 11 and a rear end comb tooth seal 12.
Wherein, the middle shell 3 and the middle housing 2 form an axial intra-machine bleed air flow path, so that air flows forwards along the axial direction; the front case 4 forms a radial inboard bleed air flow path with the front cover A5 and the front cover B6, and causes air to flow radially toward the axial center.
Wherein, 10 axial through holes are evenly distributed in the circumferential direction of the front shell 4 and the middle shell 3, and the diameters, positions and angles of the through holes of the front shell 4 and the middle shell 3 are consistent, so that air can smoothly pass through the front shell and the middle shell and transition to the radial internal air-entraining flow path.
Wherein, radial through holes are uniformly distributed on the front part of the front shell 4 in the circumferential direction and serve as a part of a radial intra-machine flow path.
Wherein, the front cover shell A5 and the front cover shell B6 are evenly distributed with 6 through holes along the circumference, so that air flows to form a closed cavity by the wheel disc and the front cover shell.
The wheel disc 7, the front cover shell A5 and the front cover shell B6 form a closed cavity, so that the air pressure in the cavity is high, and the air sealing function is achieved.
Wherein, the front end comb tooth seal 11 and the rear end comb tooth seal 12 are not less than two, and each comb tooth seal comprises 6 seal teeth.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. The lubricating oil sealing system of the gas turbine is characterized by comprising a main gas-guiding pipe (1), a front shell (4), a middle shell (3), a front shell A (5), a front shell B (6), a middle shell (2), a wheel disc (7), a secondary gas-guiding pipe (9), a front end comb tooth seal (11) and a rear end comb tooth seal (12); the main air-entraining pipe (1) is connected with the middle shell (3) and the middle housing (2); the secondary air-entraining pipe (9) is arranged at a bypass of the main air-entraining pipe (1) and is connected between two comb teeth seals at the rear end of the oil-lubricating cavity, and air with certain pressure is supplied to the rear end of the oil-lubricating cavity through the secondary air-entraining pipe (9); the front shell (4) is connected with the middle shell (3); the front housing (4) is provided with a front housing A (5) and a front housing B (6) at the outer side, and the main air-entraining pipe (1) and the built-in air-entraining flow path supply air with certain pressure to the front end of the oil-lubricating cavity; the front end and the rear end of the lubricating oil cavity are respectively provided with a front end comb tooth seal (11) and a rear end comb tooth seal (12).
2. A gas turbine lubricating oil sealing system according to claim 1, characterised in that the intermediate housing (3) forms an axial inboard bleed air flow path with the intermediate casing (2) and the front housing (4) forms a radial inboard bleed air flow path with the front casing a (5) and the front casing B (6).
3. A gas turbine lubricating oil sealing system according to claim 1, characterized in that the front housing (4) and the intermediate housing (3) are circumferentially and evenly distributed with axial through holes, and the through hole diameters, positions and angular distributions of the front housing (4) and the intermediate housing (3) are kept consistent.
4. A gas turbine oil sealing system according to claim 1, wherein the front part of the front housing (4) is circumferentially evenly distributed with radial through holes.
5. A gas turbine lubricating oil sealing system according to claim 1, characterised in that the front casing a (5) and the front casing B (6) are evenly circumferentially distributed through holes.
6. A gas turbine oil sealing system according to claim 1, characterized in that the wheel disc (7) forms a closed chamber with the front casing a (5) and the front casing B (6).
7. A gas turbine oil sealing system according to claim 1, wherein the front end comb seal (11) and the rear end comb seal (12) are not less than two.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311195421.XA CN117249000A (en) | 2023-09-17 | 2023-09-17 | Lubricating oil sealing system of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311195421.XA CN117249000A (en) | 2023-09-17 | 2023-09-17 | Lubricating oil sealing system of gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117249000A true CN117249000A (en) | 2023-12-19 |
Family
ID=89134284
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311195421.XA Pending CN117249000A (en) | 2023-09-17 | 2023-09-17 | Lubricating oil sealing system of gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117249000A (en) |
-
2023
- 2023-09-17 CN CN202311195421.XA patent/CN117249000A/en active Pending
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
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