WO2013154621A3 - Rotor blade with one or more side wall microcooling circuits - Google Patents
Rotor blade with one or more side wall microcooling circuits Download PDFInfo
- Publication number
- WO2013154621A3 WO2013154621A3 PCT/US2013/020845 US2013020845W WO2013154621A3 WO 2013154621 A3 WO2013154621 A3 WO 2013154621A3 US 2013020845 W US2013020845 W US 2013020845W WO 2013154621 A3 WO2013154621 A3 WO 2013154621A3
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- side wall
- microcircuit
- cavity
- rotor blade
- tip
- 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
- 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
- F01D5/186—Film 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
- 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
- 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
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
-
- 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
- F05D2260/204—Heat transfer, e.g. cooling by the use of microcircuits
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A rotor blade (26) for a gas turbine engine (10) includes an airfoil (34) and a cooling microcircuit (36, 38, 40). The airfoil (34) includes a first side wall (42), a second side wall (44) and a tip endwall (50), where the first side wall (42) and the second side wall (44) extend to and cooperate to form the tip endwall (50), defining a main cavity (62) between the first side wall (42) and the second side wall (44). The cooling microcircuit (36, 38, 40) includes a microcircuit cavity (72), an inlet (74), a side wall outlet (76) and a tip outlet (78). The microcircuit cavity (72) is embedded within the first side wall (72), and the inlet (74) extends from the main cavity (62) to the microcircuit cavity (72). The side wall outlet (76) extends from the microcircuit cavity (72) to an exterior first side surface of the airfoil (42). The tip outlet (78) extends from the microcircuit cavity (72) to an exterior tip surface (52, 54) of the airfoil.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/416,822 US20130236329A1 (en) | 2012-03-09 | 2012-03-09 | Rotor blade with one or more side wall cooling circuits |
US13/416,822 | 2012-03-09 |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2013154621A2 WO2013154621A2 (en) | 2013-10-17 |
WO2013154621A3 true WO2013154621A3 (en) | 2013-12-27 |
Family
ID=48916164
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US2013/020845 WO2013154621A2 (en) | 2012-03-09 | 2013-01-09 | Rotor blade with one or more side wall cooling circuits |
Country Status (2)
Country | Link |
---|---|
US (1) | US20130236329A1 (en) |
WO (1) | WO2013154621A2 (en) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10317150B2 (en) * | 2016-11-21 | 2019-06-11 | United Technologies Corporation | Staged high temperature heat exchanger |
US10787932B2 (en) * | 2018-07-13 | 2020-09-29 | Honeywell International Inc. | Turbine blade with dust tolerant cooling system |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1022432A2 (en) * | 1999-01-21 | 2000-07-26 | ROLLS-ROYCE plc | Cooled aerofoil for a gas turbine engine |
EP1445424A2 (en) * | 2003-02-05 | 2004-08-11 | United Technologies Corporation | Microcircuit cooling for a turbine blade tip |
EP1882820A1 (en) * | 2006-07-18 | 2008-01-30 | United Technologies Corporation | Microcircuit cooling and blade tip blowing |
EP2031186A2 (en) * | 2007-08-27 | 2009-03-04 | United Technologies Corporation | Turbine engine blade cooling |
EP2374996A2 (en) * | 2010-03-29 | 2011-10-12 | United Technologies Corporation | Airfoil cooling arrangement, corresponding casting core mold insert and cooling method |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5702232A (en) * | 1994-12-13 | 1997-12-30 | United Technologies Corporation | Cooled airfoils for a gas turbine engine |
US6247896B1 (en) * | 1999-06-23 | 2001-06-19 | United Technologies Corporation | Method and apparatus for cooling an airfoil |
US7581928B1 (en) * | 2006-07-28 | 2009-09-01 | United Technologies Corporation | Serpentine microcircuits for hot gas migration |
-
2012
- 2012-03-09 US US13/416,822 patent/US20130236329A1/en not_active Abandoned
-
2013
- 2013-01-09 WO PCT/US2013/020845 patent/WO2013154621A2/en active Application Filing
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1022432A2 (en) * | 1999-01-21 | 2000-07-26 | ROLLS-ROYCE plc | Cooled aerofoil for a gas turbine engine |
EP1445424A2 (en) * | 2003-02-05 | 2004-08-11 | United Technologies Corporation | Microcircuit cooling for a turbine blade tip |
EP1882820A1 (en) * | 2006-07-18 | 2008-01-30 | United Technologies Corporation | Microcircuit cooling and blade tip blowing |
EP2031186A2 (en) * | 2007-08-27 | 2009-03-04 | United Technologies Corporation | Turbine engine blade cooling |
EP2374996A2 (en) * | 2010-03-29 | 2011-10-12 | United Technologies Corporation | Airfoil cooling arrangement, corresponding casting core mold insert and cooling method |
Also Published As
Publication number | Publication date |
---|---|
US20130236329A1 (en) | 2013-09-12 |
WO2013154621A2 (en) | 2013-10-17 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
WO2015057310A3 (en) | Platform cooling core for a gas turbine engine rotor blade | |
EP2851511A3 (en) | Turbine blades with tip portions having converging cooling holes | |
WO2012134833A3 (en) | High camber compressor rotor blade | |
GB2523961A (en) | Compressor blade for gas turbine engine | |
WO2014021981A3 (en) | Vortex generators for improved film effectiveness | |
WO2014058493A3 (en) | Suction side turbine blade tip cooling | |
WO2014175937A3 (en) | Gas turbine engine component having curved turbulator | |
WO2014039974A8 (en) | Low radius ratio fan for a gas turbine engine | |
WO2014042720A3 (en) | Gas turbine engine turbine blade airfoil profile | |
WO2015112240A3 (en) | Rotor blade platform cooling passage | |
EP2787174A3 (en) | Gas turbine engines with turbine airfoil cooling | |
MX2015007582A (en) | Turbomachine blade, corresponding turbomachine and method of manufacturing a turbine blade. | |
WO2013180792A3 (en) | Gas turbine engine airfoil trailing edge passage and core for making same | |
WO2014035517A3 (en) | Gas turbine engine turbine vane platform core | |
WO2014065916A3 (en) | Seal between blade and vane | |
WO2014092833A3 (en) | Gas turbine engine fan blade airfoil profile | |
SA515360834B1 (en) | Turbine blade | |
EP2586976A3 (en) | Turbine for a turbomachine | |
GB2472548A (en) | Turbine airfoil with metered cooling cavity | |
EP2540981A3 (en) | Turbine vane | |
WO2014186005A3 (en) | Gas turbine engine component with combined mate face and platform cooling | |
WO2015108592A3 (en) | Multi-material turbine airfoil | |
EP2597264A3 (en) | Aerofoil cooling arrangement | |
WO2014130116A3 (en) | Turbine blade apparatus | |
EP2738350A3 (en) | Turbine blade airfoils including showerhead film cooling systems, and methods for forming an improved showerhead film cooled airfoil of a turbine blade |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 13745205 Country of ref document: EP Kind code of ref document: A2 |
|
122 | Ep: pct application non-entry in european phase |
Ref document number: 13745205 Country of ref document: EP Kind code of ref document: A2 |