EP0623189A1 - Coolable outer air seal assembly for a turbine. - Google Patents
Coolable outer air seal assembly for a turbine.Info
- Publication number
- EP0623189A1 EP0623189A1 EP94902351A EP94902351A EP0623189A1 EP 0623189 A1 EP0623189 A1 EP 0623189A1 EP 94902351 A EP94902351 A EP 94902351A EP 94902351 A EP94902351 A EP 94902351A EP 0623189 A1 EP0623189 A1 EP 0623189A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- cooling
- substrate
- cavity
- segment
- air seal
- 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.)
- Granted
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
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
L'invention concerne un ensemble d'étanchéité d'air externe (44) refroidi par refroidissements à choc et pelliculaire combinés. Plusieurs caractéristiques de construction sont présentées dont la projection du fluide de refroidissement contre un côté radialement externe d'un ensemble d'étanchéité d'air externe (44) et l'éjection d'un film de fluide de refroidissement sur une surface radialement interne (52) de l'ensemble d'étanchéité d'air externe (44). Dans un mode particulier de réalisation, un ensemble d'étanchéité d'air externe (44) est constitué d'un substrat (54), d'une couche à ouvertures (56) placée à l'extérieur du substrat (54), et d'une couche de matériau abrasable (58) s'étendant radialement vers l'intérieur du substrat (54) et définissant une surface d'écoulement (52). Le fluide de refroidissement est acheminé dans une cavité (66) par des ouvertures (72), et vient heurter la surface externe du substrat (54). Une pluralité d'orifices de refroidissement pelliculaire (70) qui s'étend à travers le substrat (54) et la couche abrasable (58), assure une communication fluidique entre la cavité (66) et la voie d'écoulement (14). Lesdits orifices de refroidissement (76) sont orientés de manière à éjecter le liquide de refroidissement sous forme pelliculaire sur la surfce d'écoulement (52). Dans un autre mode de réalisation, la cavité (66) comprend une chambre (112) s'étendant longitudinalement, située dans une partie évasée (108) de l'étanchéité d'air (46) afin d'en améliorer le refroidissement et de réduire les contraintes à l'intérieur de celle-ci.An external air seal assembly (44) cooled by combined shock and film cooling. Several construction features are shown including the spraying of coolant against a radially outer side of an outer air seal assembly (44) and the ejection of a film of coolant onto a radially inner surface ( 52) of the outer air seal assembly (44). In a particular embodiment, an external air seal assembly (44) consists of a substrate (54), an apertured layer (56) placed outside the substrate (54), and a layer of abradable material (58) extending radially inward from the substrate (54) and defining a flow surface (52). The cooling fluid is routed into a cavity (66) through openings (72), and strikes the outer surface of the substrate (54). A plurality of film cooling ports (70), which extend through the substrate (54) and the abradable layer (58), provide fluid communication between the cavity (66) and the flow path (14). Said cooling orifices (76) are oriented so as to eject the cooling liquid in film form onto the flow surface (52). In another embodiment, the cavity (66) includes a longitudinally extending chamber (112) located in a flared portion (108) of the air seal (46) to improve cooling and reduce the stresses inside it.
Description
Claims
Applications Claiming Priority (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US98081592A | 1992-11-24 | 1992-11-24 | |
US980815 | 1992-11-24 | ||
US2792993A | 1993-03-08 | 1993-03-08 | |
US27929 | 1993-03-08 | ||
PCT/US1993/011350 WO1994012775A1 (en) | 1992-11-24 | 1993-11-22 | Coolable outer air seal assembly for a turbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0623189A1 true EP0623189A1 (en) | 1994-11-09 |
EP0623189B1 EP0623189B1 (en) | 1997-04-02 |
Family
ID=26703047
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP94902351A Expired - Lifetime EP0623189B1 (en) | 1992-11-24 | 1993-11-22 | Coolable outer air seal assembly for a turbine |
Country Status (4)
Country | Link |
---|---|
EP (1) | EP0623189B1 (en) |
JP (1) | JPH07503298A (en) |
DE (1) | DE69309437T2 (en) |
WO (1) | WO1994012775A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20140366545A1 (en) * | 2012-02-29 | 2014-12-18 | Ihi Corporation | Gas turbine engine |
Families Citing this family (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6146091A (en) * | 1998-03-03 | 2000-11-14 | Mitsubishi Heavy Industries, Ltd. | Gas turbine cooling structure |
US6196792B1 (en) * | 1999-01-29 | 2001-03-06 | General Electric Company | Preferentially cooled turbine shroud |
FR2803871B1 (en) * | 2000-01-13 | 2002-06-07 | Snecma Moteurs | DIAMETER ADJUSTMENT ARRANGEMENT OF A GAS TURBINE STATOR |
EP1124039A1 (en) * | 2000-02-09 | 2001-08-16 | General Electric Company | Impingement cooling apparatus for a gas turbine shroud system |
GB0029337D0 (en) * | 2000-12-01 | 2001-01-17 | Rolls Royce Plc | A seal segment for a turbine |
US7377742B2 (en) * | 2005-10-14 | 2008-05-27 | General Electric Company | Turbine shroud assembly and method for assembling a gas turbine engine |
US8105014B2 (en) | 2009-03-30 | 2012-01-31 | United Technologies Corporation | Gas turbine engine article having columnar microstructure |
GB201012783D0 (en) | 2010-07-30 | 2010-09-15 | Rolls Royce Plc | Turbine stage shroud segment |
GB201014802D0 (en) * | 2010-09-07 | 2010-10-20 | Rolls Royce Plc | Turbine stage shroud segment |
JP5597174B2 (en) * | 2011-09-20 | 2014-10-01 | 株式会社日立製作所 | Member having abradable coating and gas turbine |
US8683814B2 (en) | 2012-02-15 | 2014-04-01 | United Technologies Corporation | Gas turbine engine component with impingement and lobed cooling hole |
US8572983B2 (en) * | 2012-02-15 | 2013-11-05 | United Technologies Corporation | Gas turbine engine component with impingement and diffusive cooling |
US9103225B2 (en) * | 2012-06-04 | 2015-08-11 | United Technologies Corporation | Blade outer air seal with cored passages |
US20140127006A1 (en) * | 2012-11-05 | 2014-05-08 | United Technologies Corporation | Blade outer air seal |
EP3183431B1 (en) * | 2014-08-22 | 2018-10-10 | Siemens Aktiengesellschaft | Shroud cooling system for shrouds adjacent to airfoils within gas turbine engines |
US10526897B2 (en) * | 2015-09-30 | 2020-01-07 | United Technologies Corporation | Cooling passages for gas turbine engine component |
US10626751B2 (en) | 2017-05-30 | 2020-04-21 | United Technologies Corporation | Turbine cooling air metering arrangement |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3365172A (en) * | 1966-11-02 | 1968-01-23 | Gen Electric | Air cooled shroud seal |
US3728039A (en) * | 1966-11-02 | 1973-04-17 | Gen Electric | Fluid cooled porous stator structure |
US3825364A (en) * | 1972-06-09 | 1974-07-23 | Gen Electric | Porous abradable turbine shroud |
US4650395A (en) * | 1984-12-21 | 1987-03-17 | United Technologies Corporation | Coolable seal segment for a rotary machine |
-
1993
- 1993-11-22 EP EP94902351A patent/EP0623189B1/en not_active Expired - Lifetime
- 1993-11-22 DE DE69309437T patent/DE69309437T2/en not_active Expired - Lifetime
- 1993-11-22 JP JP6513316A patent/JPH07503298A/en active Pending
- 1993-11-22 WO PCT/US1993/011350 patent/WO1994012775A1/en active IP Right Grant
Non-Patent Citations (1)
Title |
---|
See references of WO9412775A1 * |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20140366545A1 (en) * | 2012-02-29 | 2014-12-18 | Ihi Corporation | Gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
JPH07503298A (en) | 1995-04-06 |
DE69309437D1 (en) | 1997-05-07 |
EP0623189B1 (en) | 1997-04-02 |
WO1994012775A1 (en) | 1994-06-09 |
DE69309437T2 (en) | 1997-11-06 |
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