RU2012158336A - TURBINE UNIT AND METHOD FOR REDUCING A FLUID FLOW BETWEEN TURBINE ELEMENTS - Google Patents
TURBINE UNIT AND METHOD FOR REDUCING A FLUID FLOW BETWEEN TURBINE ELEMENTS Download PDFInfo
- Publication number
- RU2012158336A RU2012158336A RU2012158336/06A RU2012158336A RU2012158336A RU 2012158336 A RU2012158336 A RU 2012158336A RU 2012158336/06 A RU2012158336/06 A RU 2012158336/06A RU 2012158336 A RU2012158336 A RU 2012158336A RU 2012158336 A RU2012158336 A RU 2012158336A
- Authority
- RU
- Russia
- Prior art keywords
- fluid
- flow
- stator
- rotor
- passage
- Prior art date
Links
Classifications
-
- 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
- F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
-
- 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
- F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
- F01D11/06—Control thereof
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
Abstract
1. Узел турбины, содержащий: статор,ротор, расположенный смежно со статором, ипроход, выполненный в элементе, соединенном с ротором, для получения потока текучей среды с созданием между ротором и статором завесы из текучей среды, уменьшающей поток текучей среды между статором и ротором.2. Узел по п.1, в котором указанный элемент содержит крышку.3. Узел по п.2, в котором завеса из текучей среды направлена от выступа, выполненного в крышке.4. Узел по п.1, в котором проход выполнен с возможностью принятия потока текучей среды из источника текучей среды, обеспечивающего подачу текучей среды, для регулирования температуры частей узла турбины.5. Узел по п.1, в котором проход содержит сужающийся проход для увеличения скорости потока текучей среды в проходе, для создания завесы из текучей среды.6. Узел по п.1, в котором проход выполнен с возможностью направления завесы из текучей среды под углом относительно оси турбины.7. Узел по п.1, в котором уменьшенный поток текучей среды содержит уменьшенный поток охлаждающего воздуха, проходящий через радиально внутренние части статора и ротора.8. Узел по п.7, в которой завеса из текучей среды создана из потока охлаждающего воздуха.9. Способ уменьшения потока текучей среды между элементами турбины, включающий:обеспечение протекания горячего газа через статор,обеспечение протекания горячего газ через ротор, расположенный смежно со статором,обеспечение протекания потока охлаждающего воздуха через радиально внутренние части статора и ротора иобеспечение протекания текучей среды из элемента на роторе к статору для уменьшения протечки потока охлаждающего воздуха и потока горячего газа межд1. A turbine assembly containing: a stator, a rotor located adjacent to the stator, and a passage made in an element connected to the rotor to obtain a fluid flow with the creation of a fluid curtain between the rotor and the stator, reducing the fluid flow between the stator and the rotor .2. An assembly according to claim 1, wherein said element comprises a cover. The assembly of claim 2, wherein the fluid curtain is directed away from a protrusion formed in the cover. The assembly of claim 1, wherein the passage is configured to receive a fluid flow from a fluid source providing a fluid supply to control the temperature of portions of the turbine assembly. The assembly of claim 1, wherein the passageway comprises a tapered passageway for increasing the flow rate of fluid in the passageway to create a curtain of fluid. The assembly according to claim 1, in which the passage is configured to direct the curtain of fluid at an angle relative to the axis of the turbine. The assembly of claim 1, wherein the reduced fluid flow comprises a reduced cooling air flow through the radially internal portions of the stator and rotor. The assembly of claim 7, wherein the fluid curtain is formed from a stream of cooling air. A method of reducing the flow of a fluid medium between the elements of a turbine, including: ensuring the flow of hot gas through the stator, ensuring the flow of hot gas through the rotor located adjacent to the stator, ensuring the flow of cooling air through the radially internal parts of the stator and the rotor, and ensuring the flow of fluid from the element on the rotor to the stator to reduce the leakage of the cooling air flow and the flow of hot gas between
Claims (16)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/343,145 US20130170960A1 (en) | 2012-01-04 | 2012-01-04 | Turbine assembly and method for reducing fluid flow between turbine components |
US13/343,145 | 2012-01-04 |
Publications (1)
Publication Number | Publication Date |
---|---|
RU2012158336A true RU2012158336A (en) | 2014-07-10 |
Family
ID=47602971
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
RU2012158336/06A RU2012158336A (en) | 2012-01-04 | 2012-12-27 | TURBINE UNIT AND METHOD FOR REDUCING A FLUID FLOW BETWEEN TURBINE ELEMENTS |
Country Status (5)
Country | Link |
---|---|
US (1) | US20130170960A1 (en) |
EP (1) | EP2613006A1 (en) |
JP (1) | JP2013139815A (en) |
CN (1) | CN103195500A (en) |
RU (1) | RU2012158336A (en) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2837856B1 (en) * | 2013-08-14 | 2016-10-26 | General Electric Technology GmbH | Fluid seal arrangement and method for constricting a leakage flow through a leakage gap |
EP3009613B1 (en) * | 2014-08-19 | 2019-01-30 | United Technologies Corporation | Contactless seals for gas turbine engines |
EP3073056B1 (en) * | 2015-03-25 | 2018-01-03 | Ansaldo Energia IP UK Limited | Wire seal |
Family Cites Families (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1819864A (en) * | 1930-03-24 | 1931-08-18 | Gen Electric | Elastic fluid turbine |
US2489683A (en) * | 1943-11-19 | 1949-11-29 | Edward A Stalker | Turbine |
US3291447A (en) * | 1965-02-15 | 1966-12-13 | Gen Electric | Steam turbine rotor cooling |
FR2732405B1 (en) * | 1982-03-23 | 1997-05-30 | Snecma | DEVICE FOR COOLING THE ROTOR OF A GAS TURBINE |
US5018943A (en) * | 1989-04-17 | 1991-05-28 | General Electric Company | Boltless balance weight for turbine rotors |
US5232335A (en) * | 1991-10-30 | 1993-08-03 | General Electric Company | Interstage thermal shield retention system |
EP0777818B1 (en) * | 1994-08-24 | 1998-10-14 | Westinghouse Electric Corporation | Gas turbine blade with cooled platform |
US5575616A (en) * | 1994-10-11 | 1996-11-19 | General Electric Company | Turbine cooling flow modulation apparatus |
JP3495579B2 (en) * | 1997-10-28 | 2004-02-09 | 三菱重工業株式会社 | Gas turbine stationary blade |
US6481959B1 (en) * | 2001-04-26 | 2002-11-19 | Honeywell International, Inc. | Gas turbine disk cavity ingestion inhibitor |
GB0513468D0 (en) * | 2005-07-01 | 2005-08-10 | Rolls Royce Plc | A mounting arrangement for turbine blades |
GB0515868D0 (en) * | 2005-08-02 | 2005-09-07 | Rolls Royce Plc | Cooling arrangement |
US8708652B2 (en) * | 2007-06-27 | 2014-04-29 | United Technologies Corporation | Cover plate for turbine rotor having enclosed pump for cooling air |
US8206114B2 (en) * | 2008-04-29 | 2012-06-26 | United Technologies Corporation | Gas turbine engine systems involving turbine blade platforms with cooling holes |
US8262342B2 (en) * | 2008-07-10 | 2012-09-11 | Honeywell International Inc. | Gas turbine engine assemblies with recirculated hot gas ingestion |
US8616832B2 (en) * | 2009-11-30 | 2013-12-31 | Honeywell International Inc. | Turbine assemblies with impingement cooling |
GB2477736B (en) * | 2010-02-10 | 2014-04-09 | Rolls Royce Plc | A seal arrangement |
-
2012
- 2012-01-04 US US13/343,145 patent/US20130170960A1/en not_active Abandoned
- 2012-12-18 EP EP12197661.7A patent/EP2613006A1/en not_active Withdrawn
- 2012-12-27 JP JP2012283893A patent/JP2013139815A/en active Pending
- 2012-12-27 RU RU2012158336/06A patent/RU2012158336A/en not_active Application Discontinuation
-
2013
- 2013-01-04 CN CN2013100012894A patent/CN103195500A/en active Pending
Also Published As
Publication number | Publication date |
---|---|
JP2013139815A (en) | 2013-07-18 |
CN103195500A (en) | 2013-07-10 |
US20130170960A1 (en) | 2013-07-04 |
EP2613006A1 (en) | 2013-07-10 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
FA93 | Acknowledgement of application withdrawn (no request for examination) |
Effective date: 20151228 |