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MX2011009617A - Turbina de gas. - Google Patents

Turbina de gas.

Info

Publication number
MX2011009617A
MX2011009617A MX2011009617A MX2011009617A MX2011009617A MX 2011009617 A MX2011009617 A MX 2011009617A MX 2011009617 A MX2011009617 A MX 2011009617A MX 2011009617 A MX2011009617 A MX 2011009617A MX 2011009617 A MX2011009617 A MX 2011009617A
Authority
MX
Mexico
Prior art keywords
blade
rotor
inlet
cross
section area
Prior art date
Application number
MX2011009617A
Other languages
English (en)
Other versions
MX340308B (es
Inventor
Shailendra Naik
Ruben Valiente
Andre Saxer
Original Assignee
Alstom Technology Ltd
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 Alstom Technology Ltd filed Critical Alstom Technology Ltd
Publication of MX2011009617A publication Critical patent/MX2011009617A/es
Publication of MX340308B publication Critical patent/MX340308B/es

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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

La presente invención se refiere a una turbina de gas que comprende un rotor (11) y un álabe (10) con una superficie de sustentación (14), una raíz (12) del álabe provista para que sea recibida removiblemente por una muesca (31) en el rotor (11), y un núcleo (18) del álabe, hueco, que se extiende entre la raíz (12) del álabe y la punta (15) del álabe para el flujo de un fluido de enfriamiento, que se introduce al núcleo (18) del álabe a través de una entrada (20) del álabe en la raíz (12), y es suministrado por medio de un orificio (23) del rotor, que se extiende a través del rotor (11) y está en comunicación de fluido con la entrada (20) del álabe, por lo cual la entrada (20) tiene un área de sección transversal que excede el área de sección transversal del orificio (23) del rotor en al menos una dirección, el orificio del rotor tiene una salida (24) del orificio del rotor con la forma del difusor, de tal modo que el área de sección transversal de la salida (24) del orificio del rotor en la interconexión entre el orificio (23) del rotor y la entrada (20) cubra el área de sección transversal de la entrada (20).
MX2011009617A 2009-03-23 2010-03-22 Turbina de gas. MX340308B (es)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP09155854A EP2236746A1 (en) 2009-03-23 2009-03-23 Gas turbine
PCT/EP2010/053670 WO2010108879A1 (en) 2009-03-23 2010-03-22 Gas turbine

Publications (2)

Publication Number Publication Date
MX2011009617A true MX2011009617A (es) 2011-09-29
MX340308B MX340308B (es) 2016-07-05

Family

ID=40875154

Family Applications (1)

Application Number Title Priority Date Filing Date
MX2011009617A MX340308B (es) 2009-03-23 2010-03-22 Turbina de gas.

Country Status (7)

Country Link
US (1) US9341069B2 (es)
EP (2) EP2236746A1 (es)
KR (1) KR101613866B1 (es)
MX (1) MX340308B (es)
RU (1) RU2531839C2 (es)
SG (1) SG174494A1 (es)
WO (1) WO2010108879A1 (es)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH704716A1 (de) * 2011-03-22 2012-09-28 Alstom Technology Ltd Rotorscheibe für eine Turbine sowie Rotor und Turbine mit einer solchen Rotorscheibe.
EP2535515A1 (en) * 2011-06-16 2012-12-19 Siemens Aktiengesellschaft Rotor blade root section with cooling passage and method for supplying cooling fluid to a rotor blade
EP2725191B1 (en) 2012-10-23 2016-03-16 Alstom Technology Ltd Gas turbine and turbine blade for such a gas turbine
EP3080400B1 (en) 2013-12-12 2019-04-10 United Technologies Corporation Gas turbine engine rotor and corresponding method of cooling
EP3059394B1 (en) * 2015-02-18 2019-10-30 Ansaldo Energia Switzerland AG Turbine blade and set of turbine blades
DE102016124806A1 (de) * 2016-12-19 2018-06-21 Rolls-Royce Deutschland Ltd & Co Kg Turbinen-Laufschaufelanordnung für eine Gasturbine und Verfahren zum Bereitstellen von Dichtluft in einer Turbinen-Laufschaufelanordnung
US11008872B2 (en) 2018-12-14 2021-05-18 Raytheon Technologies Corporation Extension air feed hole blockage preventer for a gas turbine engine
US11073024B2 (en) 2018-12-14 2021-07-27 Raytheon Technologies Corporation Shape recessed surface cooling air feed hole blockage preventer for a gas turbine engine
US11078796B2 (en) 2018-12-14 2021-08-03 Raytheon Technologies Corporation Redundant entry cooling air feed hole blockage preventer for a gas turbine engine

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FR989719A (fr) * 1944-03-03 1951-09-12 Rateau Soc Perfectionnements aux procédés de fabrication des roues de turbo-machines et rouesainsi obtenues
US2657902A (en) * 1947-12-17 1953-11-03 Packard Motor Car Co Turbine rotor for turbojet engines
US2648520A (en) * 1949-08-02 1953-08-11 Heinz E Schmitt Air-cooled turbine blade
US2951340A (en) * 1956-01-03 1960-09-06 Curtiss Wright Corp Gas turbine with control mechanism for turbine cooling air
GB868788A (en) * 1956-11-20 1961-05-25 Robert Pouit Improvements in gas turbine installations
US3370830A (en) * 1966-12-12 1968-02-27 Gen Motors Corp Turbine cooling
FR2152437B1 (es) * 1971-09-15 1974-05-31 Snecma
US3749514A (en) * 1971-09-30 1973-07-31 United Aircraft Corp Blade attachment
US3918835A (en) * 1974-12-19 1975-11-11 United Technologies Corp Centrifugal cooling air filter
US4017209A (en) * 1975-12-15 1977-04-12 United Technologies Corporation Turbine rotor construction
GB1551678A (en) * 1978-03-20 1979-08-30 Rolls Royce Cooled rotor blade for a gas turbine engine
US4344738A (en) * 1979-12-17 1982-08-17 United Technologies Corporation Rotor disk structure
US4501053A (en) * 1982-06-14 1985-02-26 United Technologies Corporation Method of making rotor blade for a rotary machine
JPS5951103A (ja) * 1982-09-20 1984-03-24 Fuji Electric Co Ltd タ−ビン動翼及び円板の冷却装置
US4820123A (en) * 1988-04-25 1989-04-11 United Technologies Corporation Dirt removal means for air cooled blades
US4820122A (en) * 1988-04-25 1989-04-11 United Technologies Corporation Dirt removal means for air cooled blades
US5503527A (en) 1994-12-19 1996-04-02 General Electric Company Turbine blade having tip slot
GB9615394D0 (en) * 1996-07-23 1996-09-04 Rolls Royce Plc Gas turbine engine rotor disc with cooling fluid passage
EP1041246A1 (de) 1999-03-29 2000-10-04 Siemens Aktiengesellschaft Kühlmitteldurchströmte, gegossene Gasturbinenschaufel sowie Vorrichtung und Verfahren zur Herstellung eines Verteilerraums der Gasturbinenschaufel
DE10064269A1 (de) 2000-12-22 2002-07-04 Alstom Switzerland Ltd Komponente einer Strömungsmaschine mit Inspektionsöffnung
US6735956B2 (en) * 2001-10-26 2004-05-18 Pratt & Whitney Canada Corp. High pressure turbine blade cooling scoop
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DE10331635B4 (de) * 2003-07-12 2014-02-13 Alstom Technology Ltd. Gekühlte Schaufel für eine Gasturbine
US7059825B2 (en) * 2004-05-27 2006-06-13 United Technologies Corporation Cooled rotor blade
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US7632071B2 (en) * 2005-12-15 2009-12-15 United Technologies Corporation Cooled turbine blade
RU2323343C2 (ru) * 2006-03-20 2008-04-27 Федеральное государственное унитарное предприятие "Московское машиностроительное производственное предприятие "САЛЮТ" (ФГУП "ММПП "САЛЮТ") Охлаждаемая лопатка турбомашины
US7762774B2 (en) * 2006-12-15 2010-07-27 Siemens Energy, Inc. Cooling arrangement for a tapered turbine blade

Also Published As

Publication number Publication date
EP2411629A1 (en) 2012-02-01
US20120087782A1 (en) 2012-04-12
MX340308B (es) 2016-07-05
RU2531839C2 (ru) 2014-10-27
RU2011142732A (ru) 2013-04-27
EP2411629B1 (en) 2018-03-07
KR101613866B1 (ko) 2016-04-20
SG174494A1 (en) 2011-10-28
EP2236746A1 (en) 2010-10-06
US9341069B2 (en) 2016-05-17
KR20120005444A (ko) 2012-01-16
WO2010108879A1 (en) 2010-09-30

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