EP1605138A3 - Cooled rotor blade with leading edge impingement cooling - Google Patents

Cooled rotor blade with leading edge impingement cooling Download PDF

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Publication number
EP1605138A3
EP1605138A3 EP05253261A EP05253261A EP1605138A3 EP 1605138 A3 EP1605138 A3 EP 1605138A3 EP 05253261 A EP05253261 A EP 05253261A EP 05253261 A EP05253261 A EP 05253261A EP 1605138 A3 EP1605138 A3 EP 1605138A3
Authority
EP
European Patent Office
Prior art keywords
radial passage
rib
rotor blade
leading edge
root
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
Application number
EP05253261A
Other languages
German (de)
French (fr)
Other versions
EP1605138A2 (en
EP1605138B1 (en
Inventor
Jeffrey R. Levine
Edward Pietraszkiewicz
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP1605138A2 publication Critical patent/EP1605138A2/en
Publication of EP1605138A3 publication Critical patent/EP1605138A3/en
Application granted granted Critical
Publication of EP1605138B1 publication Critical patent/EP1605138B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • 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

Abstract

A rotor blade (14) is provided having a hollow airfoil (22) and a root (20). The hollow airfoil (22) has a cavity defined by a suction side wall (38), a pressure side wall (36), a leading edge (32), a trailing edge (34), a base (28), and a tip (30). An internal passage configuration (40) is disposed within the cavity. The configuration includes a first radial passage (48), a second radial passage (50), and a rib (53) disposed between and separating the first radial passage (48) and second radial passage (50). A plurality of crossover apertures (52) are disposed within the rib (53). A portion of the plurality of crossover apertures (52) are oblong having a length (70) extending through the rib (53), and a height (74) and a width (72). The height (74) of each oblong aperture (52) is greater than the width (72). In some embodiments, the oblong crossover apertures (52) are aligned heightwise along the rib (53). The root (20) includes a conduit (42) that is operable to permit airflow through the root (20) and into the first radial passage (48).
Figure imgaf001
EP05253261A 2004-05-27 2005-05-27 Cooled rotor blade with leading edge impingement cooling Active EP1605138B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US855076 1992-03-23
US10/855,076 US20050265840A1 (en) 2004-05-27 2004-05-27 Cooled rotor blade with leading edge impingement cooling

Publications (3)

Publication Number Publication Date
EP1605138A2 EP1605138A2 (en) 2005-12-14
EP1605138A3 true EP1605138A3 (en) 2007-10-03
EP1605138B1 EP1605138B1 (en) 2010-06-30

Family

ID=34941473

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05253261A Active EP1605138B1 (en) 2004-05-27 2005-05-27 Cooled rotor blade with leading edge impingement cooling

Country Status (4)

Country Link
US (1) US20050265840A1 (en)
EP (1) EP1605138B1 (en)
JP (1) JP2005337257A (en)
DE (1) DE602005022018D1 (en)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7217094B2 (en) * 2004-10-18 2007-05-15 United Technologies Corporation Airfoil with large fillet and micro-circuit cooling
FR2918105B1 (en) * 2007-06-27 2013-12-27 Snecma TURBOMACHINE COOLED AUBE COMPRISING VARIABLE IMPACT REMOTE COOLING HOLES.
US8840370B2 (en) 2011-11-04 2014-09-23 General Electric Company Bucket assembly for turbine system
JP2013100765A (en) * 2011-11-08 2013-05-23 Ihi Corp Impingement cooling mechanism, turbine blade, and combustor
US9151173B2 (en) * 2011-12-15 2015-10-06 General Electric Company Use of multi-faceted impingement openings for increasing heat transfer characteristics on gas turbine components
EP2828484B1 (en) * 2012-03-22 2019-05-08 Ansaldo Energia IP UK Limited Turbine blade
US9279331B2 (en) 2012-04-23 2016-03-08 United Technologies Corporation Gas turbine engine airfoil with dirt purge feature and core for making same
JP5567180B1 (en) * 2013-05-20 2014-08-06 川崎重工業株式会社 Turbine blade cooling structure
US10012090B2 (en) * 2014-07-25 2018-07-03 United Technologies Corporation Airfoil cooling apparatus
US20180298763A1 (en) * 2014-11-11 2018-10-18 Siemens Aktiengesellschaft Turbine blade with axial tip cooling circuit
KR101906701B1 (en) * 2017-01-03 2018-10-10 두산중공업 주식회사 Gas turbine blade
US10787932B2 (en) * 2018-07-13 2020-09-29 Honeywell International Inc. Turbine blade with dust tolerant cooling system
US10895168B2 (en) * 2019-05-30 2021-01-19 Solar Turbines Incorporated Turbine blade with serpentine channels

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5688104A (en) * 1993-11-24 1997-11-18 United Technologies Corporation Airfoil having expanded wall portions to accommodate film cooling holes
EP1022434A2 (en) * 1999-01-25 2000-07-26 General Electric Company Gas turbine blade cooling configuration
EP1035302A2 (en) * 1999-03-05 2000-09-13 General Electric Company Multiple impingement airfoil cooling
EP1088964A2 (en) * 1999-09-30 2001-04-04 General Electric Company Slotted impingement cooling of airfoil leading edge
EP1213442A1 (en) * 2000-12-05 2002-06-12 United Technologies Corporation Coolable airfoil structure
US20030044277A1 (en) * 2001-08-28 2003-03-06 Snecma Moteurs Gas turbine blade cooling circuits
EP1496203A1 (en) * 2003-07-11 2005-01-12 Rolls-Royce Deutschland Ltd & Co KG Turbine blade with impingement cooling

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3619082A (en) * 1968-07-05 1971-11-09 Gen Motors Corp Turbine blade
US3767322A (en) * 1971-07-30 1973-10-23 Westinghouse Electric Corp Internal cooling for turbine vanes
US5387086A (en) * 1993-07-19 1995-02-07 General Electric Company Gas turbine blade with improved cooling

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5688104A (en) * 1993-11-24 1997-11-18 United Technologies Corporation Airfoil having expanded wall portions to accommodate film cooling holes
EP1022434A2 (en) * 1999-01-25 2000-07-26 General Electric Company Gas turbine blade cooling configuration
EP1035302A2 (en) * 1999-03-05 2000-09-13 General Electric Company Multiple impingement airfoil cooling
EP1088964A2 (en) * 1999-09-30 2001-04-04 General Electric Company Slotted impingement cooling of airfoil leading edge
EP1213442A1 (en) * 2000-12-05 2002-06-12 United Technologies Corporation Coolable airfoil structure
US20030044277A1 (en) * 2001-08-28 2003-03-06 Snecma Moteurs Gas turbine blade cooling circuits
EP1496203A1 (en) * 2003-07-11 2005-01-12 Rolls-Royce Deutschland Ltd & Co KG Turbine blade with impingement cooling

Also Published As

Publication number Publication date
JP2005337257A (en) 2005-12-08
EP1605138A2 (en) 2005-12-14
DE602005022018D1 (en) 2010-08-12
US20050265840A1 (en) 2005-12-01
EP1605138B1 (en) 2010-06-30

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