CN109404057B - Labyrinth seal water path cooling device and method applied to thermoelectric turbine - Google Patents
Labyrinth seal water path cooling device and method applied to thermoelectric turbine Download PDFInfo
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- CN109404057B CN109404057B CN201811243972.8A CN201811243972A CN109404057B CN 109404057 B CN109404057 B CN 109404057B CN 201811243972 A CN201811243972 A CN 201811243972A CN 109404057 B CN109404057 B CN 109404057B
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- cavity
- labyrinth seal
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- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
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- 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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
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- 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
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a labyrinth seal water path cooling device and a cooling method applied to a metal fuel steam turbine. The invention axially arranges the ring channels with three similar inlets and outlets, so that cooling water can be fully cooled in the whole circumferential direction, and meanwhile, all the cooling water can pass through the labyrinth seal copper ring without a bypass, so that the heat exchange efficiency is greatly improved. The technology has the advantages of high cooling efficiency, few functional components, simple structure, small layout space and the like, and can ensure that the temperature and the pressure of the dead steam reaching the rear end motor meet the tolerance requirements of the water lubrication bearing on the basis of the technical indexes of the existing materials.
Description
Technical Field
The invention relates to a labyrinth seal water path cooling device and a cooling method applied to a metal fuel steam turbine.
Background
The steam turbine converts the available enthalpy of high-temperature steam into rotary mechanical energy through the turbine, can be applied to various underwater aircrafts such as aviation aircrafts, torpedoes and submarines and is a power device with high power density and high power output. Aiming at a metal fuel thermoelectric combined steam turbine prototype, the initial temperature of steam is required to be as high as possible so as to improve the power and efficiency of the steam turbine. But at the same time, the rear end motor adopts a water lubrication bearing supporting scheme, and exhaust steam with higher temperature and pressure is not allowed to enter the rear end motor.
Therefore, the labyrinth seal of the prototype needs to adopt the scheme of the stepped multi-seal tooth number, and simultaneously needs to carry out more sufficient cooling on the labyrinth seal, the heat dissipation requirement of the labyrinth seal cannot be met by the traditional surface local cooling mode, the heat exchange efficiency of the labyrinth seal needs to be increased by a more effective cooling scheme, and the temperature and the pressure when the dead steam reaches the rear end meet the tolerance requirement of the water lubrication bearing.
Disclosure of Invention
The technical problem solved by the invention is as follows: the invention aims at a metal fuel thermoelectric combined steam turbine prototype, and the steam initial temperature is required to be as high as possible so as to improve the power and the efficiency of the steam turbine. But at the same time, the rear end motor adopts a water lubrication bearing supporting scheme, and exhaust steam with higher temperature and pressure is not allowed to enter the rear end motor to be extracted. In order to solve the problems that the temperature and the pressure of the exhaust steam of the existing metal fuel steam turbine are high and a rear end motor cannot work normally, a combined cooling scheme is adopted to cool a multi-stage and stepped labyrinth seal, so that the temperature and the pressure of the exhaust steam reaching the rear end meet the tolerance requirement of a water lubrication bearing.
The technical scheme of the invention is as follows: a labyrinth seal water path cooling device applied to a thermoelectric turbine comprises a front shell, a nozzle, a turbine disc, a labyrinth seal copper ring and a rear shell; the front shell and the rear shell are coaxially and fixedly connected, and a cavity body is formed inside the front shell and the rear shell after the front shell and the rear shell are fixedly connected; the turbine disc is positioned in the cavity, and the axis of the turbine disc is superposed with the axis of the rear shell; the large-diameter end of the turbine disc is in clearance fit with the inner wall of the front shell; the labyrinth seal copper ring is sleeved on the turbine disc shaft, the outer wall of the labyrinth seal copper ring is in contact with the rear shell, the labyrinth seal copper ring is radially positioned through the rear shell, and the labyrinth seal copper ring is axially positioned through the nozzle; the nozzle and the front shell are connected with each other through the spigot, and are axially positioned through the front shell;
the labyrinth seal copper ring is integrally a hollow cylindrical body, the outer wall of the labyrinth seal copper ring is in a multi-stage shape, the multi-stage outer wall of the labyrinth seal copper ring is in contact with the inner wall of the rear shell, and an annular cavity formed between the outer wall of the labyrinth seal copper ring and the inner wall of the rear shell is defined as an E cavity; a plurality of annular grooves are formed in the circumferential direction of the inner wall of the labyrinth seal copper ring, and the annular grooves are not in contact with each other;
the rear shell is an annular piece, three cooling cavities of a cavity B, a cavity C and a cavity G are respectively arranged on the annular piece and are coaxially and annularly distributed, and the axial length of the cavity B is h after definitionBThe axial length of the C cavity is hCAnd the axial length of the G cavity is hGAnd h isB>hG＝hC(ii) a A through hole D is formed in the inner wall of the cavity C, a through hole F is formed in the inner wall of the cavity G, and the circumferential included angle between the two through holes is not more than 20 degrees;
the rear shell is radially provided with through holes which are respectively used as a water inlet A and a water outlet H, wherein the water inlet A is communicated with the cavity B, and the water outlet H is communicated with the cavity G; cooling water enters the cavity B after entering through the water inlet A, overflows after filling the cavity B and enters the cavity C; the cooling water in the cavity C enters the cavity E through the through hole D, surrounds a circle, enters the cavity G through the opening F, and enters the water channel of the front shell (1) through the water outlet H.
The further technical scheme of the invention is as follows: a method of labyrinth seal water path cooling for a thermoelectric turbine, comprising the steps of:
the method comprises the following steps: cooling water enters the cavity B through the water inlet A;
step two: when the cavity B is filled with cooling water, the cooling water overflows and enters the cavity C;
step three: cooling water in the cavity C enters the cavity E through the through hole D;
step four: cooling water in the cavity E enters the cavity G through the opening F;
step five: and cooling water in the cavity G enters a water channel of the front shell (1) through the water outlet H to finish cooling the labyrinth seal copper ring.
Effects of the invention
The invention has the technical effects that: the invention relates to a labyrinth seal cooling device and a cooling method applied to an underwater metal fuel steam turbine, which can greatly improve the heat exchange efficiency at the labyrinth seal position, fully take away the heat energy in each cavity of the labyrinth seal, and ensure that the temperature and the pressure when exhaust steam reaches the rear end meet the tolerance requirement of a water lubrication bearing.
Drawings
FIG. 1 is a schematic structural diagram of the present invention.
FIG. 2 is a schematic view of the cooling water path of the present invention (left view)
Description of reference numerals: 1-front housing; 2-a nozzle; 3-a turbine disk; 4-rear housing; 5-labyrinth sealing copper ring
Detailed Description
Referring to fig. 1-2, from the structural layout, the water path layout of the whole engine is mainly on the piece 4 (rear housing), the piece 5 (labyrinth seal copper ring), and the piece 1 (front housing).
Cooling water flows from the sea water pump to the waterway A and then enters the cavity B, and the cooling water rotates for a circle in the cavity B to cool the O-shaped ring for sealing fuel gas between the nozzle and the rear shell; then the cooling water enters a cavity C from the cavity B, and the cooling water in the cavity C enters an inner annular cavity E of a piece 5 (a labyrinth seal copper ring) through an opening D in a piece 4 (a rear shell); after one revolution of the E-chamber, it enters the G-chamber through opening F in element 4 (rear housing) and enters the waterway of element 1 (front housing) through the H-channel. In the design scheme of the water path, the annular channels with the similar inlets and the similar outlets are axially arranged for three times, so that cooling water can be fully cooled in the whole circumferential direction, and meanwhile, all the cooling water can pass through the labyrinth seal copper ring without being provided with a bypass, so that the heat exchange efficiency is greatly improved, the heat energy in each cavity of the labyrinth seal can be fully taken away, and the aim of reducing the temperature and the pressure of exhaust steam is fulfilled.
Claims (2)
1. A labyrinth seal water path cooling device applied to a thermoelectric turbine comprises a front shell (1), a nozzle (2), a turbine disc (3), a labyrinth seal copper ring (5) and a rear shell (4); the front shell (1) and the rear shell (4) are coaxially and fixedly connected, and a cavity is formed inside the front shell and the rear shell after the front shell and the rear shell are fixedly connected; the turbine disc (3) is positioned in the cavity, and the axis of the turbine disc (3) is overlapped with the axis of the rear shell; the large-diameter end of the turbine disc (3) is in clearance fit with the inner wall of the front shell (1); the labyrinth seal copper ring (5) is sleeved on the shaft of the turbine disc (3), the outer wall of the labyrinth seal copper ring is in contact with the rear shell (4), radial positioning is carried out through the rear shell (4), and axial positioning is carried out through the nozzle (2); the nozzle (2) is connected with the front shell (1) and is axially positioned by the front shell (1);
the labyrinth seal copper ring is characterized in that the labyrinth seal copper ring (5) is integrally a hollow cylindrical body, the outer wall is in a multi-stage shape, the outer wall of the multi-stage shape is in contact with the inner wall of the rear shell, and an annular cavity formed between the outer wall of the labyrinth seal copper ring (5) and the inner wall of the rear shell is defined as an E cavity; a plurality of annular grooves are formed in the circumferential direction of the inner wall of the labyrinth seal copper ring (5), and the annular grooves are not in contact with each other;
the rear shell (4) is an annular piece, three cooling cavities of a cavity B, a cavity C and a cavity G are respectively arranged on the annular piece and are coaxially and annularly distributed, and the axial length of the cavity B is defined as hBThe axial length of the C cavity is hCAnd the axial length of the G cavity is hGAnd h isB＞hG＝hC(ii) a The inner wall of the cavity C is provided with a through hole D, and the inner wall of the cavity G is provided with a through hole F;
the rear shell (4) is radially provided with through holes which are respectively used as a water inlet A and a water outlet H, wherein the water inlet A is communicated with the cavity B, and the water outlet H is communicated with the cavity G; cooling water enters the cavity B after entering through the water inlet A, overflows after filling the cavity B and enters the cavity C; the cooling water in the cavity C enters the cavity E through the through hole D, surrounds a circle, enters the cavity G through the opening F, and enters the water channel of the front shell (1) through the water outlet H.
2. The method for cooling a labyrinth-seal water path of a thermoelectric turbine as claimed in claim 1, comprising the steps of:
the method comprises the following steps: cooling water enters the cavity B through the water inlet A;
step two: when the cavity B is filled with cooling water, the cooling water overflows and enters the cavity C;
step three: cooling water in the cavity C enters the cavity E through the through hole D;
step four: cooling water in the cavity E enters the cavity G through the opening F;
step five: and cooling water in the cavity G enters a water channel of the front shell (1) through the water outlet H to finish cooling the labyrinth seal copper ring (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811243972.8A CN109404057B (en) | 2018-10-24 | 2018-10-24 | Labyrinth seal water path cooling device and method applied to thermoelectric turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811243972.8A CN109404057B (en) | 2018-10-24 | 2018-10-24 | Labyrinth seal water path cooling device and method applied to thermoelectric turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109404057A CN109404057A (en) | 2019-03-01 |
| CN109404057B true CN109404057B (en) | 2021-09-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201811243972.8A Active CN109404057B (en) | 2018-10-24 | 2018-10-24 | Labyrinth seal water path cooling device and method applied to thermoelectric turbine |
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Family Cites Families (16)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US4465429A (en) * | 1982-02-01 | 1984-08-14 | Westinghouse Electric Corp. | Steam turbine with superheated blade disc cavities |
| JPH06129260A (en) * | 1992-10-19 | 1994-05-10 | Tonen Chem Corp | Cleaning method for cooling air-passage in gas turbine rotor |
| DE4435322B4 (en) * | 1994-10-01 | 2005-05-04 | Alstom | Method and device for shaft seal and for cooling on the exhaust side of an axial flowed gas turbine |
| US5738488A (en) * | 1996-11-12 | 1998-04-14 | General Electric Co. | Gland for transferring cooling medium to the rotor of a gas turbine |
| GB0117110D0 (en) * | 2001-07-13 | 2001-09-05 | Siemens Ag | Coolable segment for a turbomachinery and combustion turbine |
| JP2010019190A (en) * | 2008-07-11 | 2010-01-28 | Toshiba Corp | Steam turbine and method of cooling steam turbine |
| FR2946687B1 (en) * | 2009-06-10 | 2011-07-01 | Snecma | TURBOMACHINE COMPRISING IMPROVED MEANS FOR ADJUSTING THE FLOW RATE OF A COOLING AIR FLOW TAKEN AT HIGH PRESSURE COMPRESSOR OUTPUT |
| JP5558120B2 (en) * | 2010-01-12 | 2014-07-23 | 株式会社東芝 | Steam turbine rotor cooling device and steam turbine provided with this cooling device |
| ITCO20110036A1 (en) * | 2011-09-07 | 2013-03-08 | Nuovo Pignone Spa | GASKET FOR A ROTATING MACHINE |
| US9353647B2 (en) * | 2012-04-27 | 2016-05-31 | General Electric Company | Wide discourager tooth |
| DE102013011350A1 (en) * | 2013-07-08 | 2015-01-22 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine with high pressure turbine cooling system |
| KR101817460B1 (en) * | 2014-06-04 | 2018-01-10 | 미츠비시 히타치 파워 시스템즈 가부시키가이샤 | Gas turbine |
| CN106224294A (en) * | 2016-08-30 | 2016-12-14 | 四川三维鼓风机有限公司 | Sealing cooling structure for superhigh temperature blower fan |
| CN205977817U (en) * | 2016-08-30 | 2017-02-22 | 四川三维鼓风机有限公司 | A seal cooling structure for ultra -temperature fan |
| CN108005727B (en) * | 2016-10-27 | 2019-12-20 | 北京精密机电控制设备研究所 | Ultrahigh-speed turbine applicable to high-temperature high-back-pressure dry gas sealing structure |
| EP3342991B1 (en) * | 2016-12-30 | 2020-10-14 | Ansaldo Energia IP UK Limited | Baffles for cooling in a gas turbine |
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