GB201112880D0 - Blade cooling and sealing system - Google Patents
Blade cooling and sealing systemInfo
- Publication number
- GB201112880D0 GB201112880D0 GB201112880A GB201112880A GB201112880D0 GB 201112880 D0 GB201112880 D0 GB 201112880D0 GB 201112880 A GB201112880 A GB 201112880A GB 201112880 A GB201112880 A GB 201112880A GB 201112880 D0 GB201112880 D0 GB 201112880D0
- Authority
- GB
- United Kingdom
- Prior art keywords
- component
- flow passage
- internal
- passage
- cooling
- 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.)
- Ceased
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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- 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
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped
-
- 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
- F05D2260/60—Fluid transfer
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A cooled component (60) for a gas turbine engine (10), for example a turbine rotor blade, is provided. The component has an internal cooling flow passage (70). Cooling air is passed through the internal cooling flow passage to remove heat from the component and thereby reduce its temperature. The cooling air is bled from the internal cooling passage after it has passed through a portion of the passage into an internal bleed flow passage (80). This bled air is then used in a seal. Thus, some of the cooling air that enters the internal cooling flow passage is used both to cool the component and to form a seal, for example with another component.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB201112880A GB201112880D0 (en) | 2011-07-27 | 2011-07-27 | Blade cooling and sealing system |
EP20120175968 EP2551458A2 (en) | 2011-07-27 | 2012-07-11 | Blade Cooling and Sealing System |
US13/546,678 US20130028735A1 (en) | 2011-07-27 | 2012-07-11 | Blade cooling and sealing system |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB201112880A GB201112880D0 (en) | 2011-07-27 | 2011-07-27 | Blade cooling and sealing system |
Publications (1)
Publication Number | Publication Date |
---|---|
GB201112880D0 true GB201112880D0 (en) | 2011-09-07 |
Family
ID=44652373
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB201112880A Ceased GB201112880D0 (en) | 2011-07-27 | 2011-07-27 | Blade cooling and sealing system |
Country Status (3)
Country | Link |
---|---|
US (1) | US20130028735A1 (en) |
EP (1) | EP2551458A2 (en) |
GB (1) | GB201112880D0 (en) |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9771816B2 (en) | 2014-05-07 | 2017-09-26 | General Electric Company | Blade cooling circuit feed duct, exhaust duct, and related cooling structure |
US9638045B2 (en) | 2014-05-28 | 2017-05-02 | General Electric Company | Cooling structure for stationary blade |
US10132182B2 (en) * | 2014-11-12 | 2018-11-20 | United Technologies Corporation | Platforms with leading edge features |
US20160146016A1 (en) * | 2014-11-24 | 2016-05-26 | General Electric Company | Rotor rim impingement cooling |
WO2016135779A1 (en) | 2015-02-26 | 2016-09-01 | 株式会社 東芝 | Turbine rotor blade and turbine |
FR3034129B1 (en) * | 2015-03-27 | 2019-05-17 | Safran Aircraft Engines | MOBILE TURBINE AUB WITH IMPROVED DESIGN FOR AN AIRCRAFT TURBOMACHINE |
US9822653B2 (en) | 2015-07-16 | 2017-11-21 | General Electric Company | Cooling structure for stationary blade |
US9909436B2 (en) | 2015-07-16 | 2018-03-06 | General Electric Company | Cooling structure for stationary blade |
CN113623072A (en) * | 2021-08-23 | 2021-11-09 | 中国科学院工程热物理研究所 | Rear-stage disc edge cooling structure for high-pressure-ratio axial-flow compressor |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1551678A (en) * | 1978-03-20 | 1979-08-30 | Rolls Royce | Cooled rotor blade for a gas turbine engine |
US4666368A (en) * | 1986-05-01 | 1987-05-19 | General Electric Company | Swirl nozzle for a cooling system in gas turbine engines |
US5358374A (en) * | 1993-07-21 | 1994-10-25 | General Electric Company | Turbine nozzle backflow inhibitor |
JP3416447B2 (en) * | 1997-03-11 | 2003-06-16 | 三菱重工業株式会社 | Gas turbine blade cooling air supply system |
US7547191B2 (en) * | 2006-08-24 | 2009-06-16 | Siemens Energy, Inc. | Turbine airfoil cooling system with perimeter cooling and rim cavity purge channels |
US7819629B2 (en) * | 2007-02-15 | 2010-10-26 | Siemens Energy, Inc. | Blade for a gas turbine |
EP2003291B1 (en) * | 2007-06-15 | 2017-08-09 | Ansaldo Energia Switzerland AG | Cast turbine blade and method of manufacture |
US8133024B1 (en) * | 2009-06-23 | 2012-03-13 | Florida Turbine Technologies, Inc. | Turbine blade with root corner cooling |
US8821111B2 (en) * | 2010-12-14 | 2014-09-02 | Siemens Energy, Inc. | Gas turbine vane with cooling channel end turn structure |
-
2011
- 2011-07-27 GB GB201112880A patent/GB201112880D0/en not_active Ceased
-
2012
- 2012-07-11 EP EP20120175968 patent/EP2551458A2/en not_active Withdrawn
- 2012-07-11 US US13/546,678 patent/US20130028735A1/en not_active Abandoned
Also Published As
Publication number | Publication date |
---|---|
EP2551458A2 (en) | 2013-01-30 |
US20130028735A1 (en) | 2013-01-31 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
AT | Applications terminated before publication under section 16(1) |