EP1138878A3 - Flat freestanding gas turbine element - Google Patents

Flat freestanding gas turbine element Download PDF

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Publication number
EP1138878A3
EP1138878A3 EP01108008A EP01108008A EP1138878A3 EP 1138878 A3 EP1138878 A3 EP 1138878A3 EP 01108008 A EP01108008 A EP 01108008A EP 01108008 A EP01108008 A EP 01108008A EP 1138878 A3 EP1138878 A3 EP 1138878A3
Authority
EP
European Patent Office
Prior art keywords
cooling
gas turbine
hot gas
turbine element
plenum
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
EP01108008A
Other languages
German (de)
French (fr)
Other versions
EP1138878A2 (en
EP1138878B1 (en
Inventor
Alexander Dr. Beeck
Christoph Nagler
Mark Richter
Klaus Semmler
Lothar Schneider
Joerg Dr. Stengele
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.)
General Electric Technology GmbH
Original Assignee
Alstom Schweiz AG
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 Schweiz AG filed Critical Alstom Schweiz AG
Publication of EP1138878A2 publication Critical patent/EP1138878A2/en
Publication of EP1138878A3 publication Critical patent/EP1138878A3/en
Application granted granted Critical
Publication of EP1138878B1 publication Critical patent/EP1138878B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • B22C9/103—Multipart cores
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—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
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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

Plattenförmiger, auskragender Bauteilabschnitt (1) einer Gasturbine oder dergleichen, mit einer von Heißgas beaufschlagten Oberfläche (2) und mit Kühlbohrungen (12), die von einem Kühlmedium durchströmbar sind. Eine effektive Kühlung gelingt dadurch, dass wenigstens ein ausschließlich dem Bauteilabschnitt (1) zugeordnetes Plenum (10; 30; 50) vorgesehen ist, das unmittelbar benachbart zu der von Heißgas beaufschlagten Oberfläche (2) angeordnet ist und von dem Kühlmedium konvektiv durchströmbar ist, und dass zur Ausbildung eines Kühlfilms die Kühlbohrungen als Ausblaseöffnungen (12; 52) ausgebildet sind, die von dem Plenum (10; 30, 50) ausgehen und an der von Heißgas beaufschlagten Oberfläche (2) münden.

Figure 00000001
Plate-shaped, projecting component section (1) of a gas turbine or the like, with a surface (2) acted upon by hot gas and with cooling bores (12) through which a cooling medium can flow. Effective cooling is achieved by providing at least one plenum (10; 30; 50) exclusively assigned to the component section (1), which is arranged directly adjacent to the surface (2) exposed to hot gas and through which the cooling medium can flow through convectively, and that to form a cooling film, the cooling bores are designed as blow-out openings (12; 52) which start from the plenum (10; 30, 50) and open on the surface (2) exposed to hot gas.
Figure 00000001
EP01108008A 2000-03-31 2001-03-29 Gas turbine component Expired - Lifetime EP1138878B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10016081 2000-03-31
DE10016081A DE10016081A1 (en) 2000-03-31 2000-03-31 Plate-shaped, projecting component section of a gas turbine

Publications (3)

Publication Number Publication Date
EP1138878A2 EP1138878A2 (en) 2001-10-04
EP1138878A3 true EP1138878A3 (en) 2003-10-01
EP1138878B1 EP1138878B1 (en) 2008-05-14

Family

ID=7637140

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01108008A Expired - Lifetime EP1138878B1 (en) 2000-03-31 2001-03-29 Gas turbine component

Country Status (3)

Country Link
US (1) US6565317B2 (en)
EP (1) EP1138878B1 (en)
DE (2) DE10016081A1 (en)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6887033B1 (en) * 2003-11-10 2005-05-03 General Electric Company Cooling system for nozzle segment platform edges
US7004720B2 (en) * 2003-12-17 2006-02-28 Pratt & Whitney Canada Corp. Cooled turbine vane platform
US7625172B2 (en) * 2006-04-26 2009-12-01 United Technologies Corporation Vane platform cooling
US10189100B2 (en) 2008-07-29 2019-01-29 Pratt & Whitney Canada Corp. Method for wire electro-discharge machining a part
CH700320A1 (en) 2009-01-30 2010-07-30 Alstom Technology Ltd Method for producing a component of a gas turbine.
US8925201B2 (en) * 2009-06-29 2015-01-06 Pratt & Whitney Canada Corp. Method and apparatus for providing rotor discs
US20130094971A1 (en) * 2011-10-12 2013-04-18 General Electric Company Hot gas path component for turbine system
CA2898822A1 (en) 2013-03-13 2014-10-09 Rolls-Royce Corporation Trenched cooling hole arrangement for a ceramic matrix composite vane
US11118474B2 (en) 2017-10-09 2021-09-14 Raytheon Technologies Corporation Vane cooling structures

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2316440A1 (en) * 1975-06-30 1977-01-28 Gen Electric Gas turbine inlet duct wall cooling system - has outer passageways supplied with cool air from compressor
US4017213A (en) * 1975-10-14 1977-04-12 United Technologies Corporation Turbomachinery vane or blade with cooled platforms
US4353679A (en) * 1976-07-29 1982-10-12 General Electric Company Fluid-cooled element
US4616976A (en) * 1981-07-07 1986-10-14 Rolls-Royce Plc Cooled vane or blade for a gas turbine engine
US5197852A (en) * 1990-05-31 1993-03-30 General Electric Company Nozzle band overhang cooling
US5344283A (en) * 1993-01-21 1994-09-06 United Technologies Corporation Turbine vane having dedicated inner platform cooling
US5413458A (en) * 1994-03-29 1995-05-09 United Technologies Corporation Turbine vane with a platform cavity having a double feed for cooling fluid
US5460486A (en) * 1992-11-19 1995-10-24 Bmw Rolls-Royce Gmbh Gas turbine blade having improved thermal stress cooling ducts
US5823741A (en) * 1996-09-25 1998-10-20 General Electric Co. Cooling joint connection for abutting segments in a gas turbine engine

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2643049A1 (en) * 1975-10-14 1977-04-21 United Technologies Corp SHOVEL WITH COOLED PLATFORM FOR A FLOW MACHINE
JPH03213602A (en) * 1990-01-08 1991-09-19 General Electric Co <Ge> Self cooling type joint connecting structure to connect contact segment of gas turbine engine
JP3495579B2 (en) 1997-10-28 2004-02-09 三菱重工業株式会社 Gas turbine stationary blade

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2316440A1 (en) * 1975-06-30 1977-01-28 Gen Electric Gas turbine inlet duct wall cooling system - has outer passageways supplied with cool air from compressor
US4017213A (en) * 1975-10-14 1977-04-12 United Technologies Corporation Turbomachinery vane or blade with cooled platforms
US4353679A (en) * 1976-07-29 1982-10-12 General Electric Company Fluid-cooled element
US4616976A (en) * 1981-07-07 1986-10-14 Rolls-Royce Plc Cooled vane or blade for a gas turbine engine
US5197852A (en) * 1990-05-31 1993-03-30 General Electric Company Nozzle band overhang cooling
US5460486A (en) * 1992-11-19 1995-10-24 Bmw Rolls-Royce Gmbh Gas turbine blade having improved thermal stress cooling ducts
US5344283A (en) * 1993-01-21 1994-09-06 United Technologies Corporation Turbine vane having dedicated inner platform cooling
US5413458A (en) * 1994-03-29 1995-05-09 United Technologies Corporation Turbine vane with a platform cavity having a double feed for cooling fluid
US5823741A (en) * 1996-09-25 1998-10-20 General Electric Co. Cooling joint connection for abutting segments in a gas turbine engine

Also Published As

Publication number Publication date
DE50113955D1 (en) 2008-06-26
EP1138878A2 (en) 2001-10-04
US6565317B2 (en) 2003-05-20
US20010036407A1 (en) 2001-11-01
DE10016081A1 (en) 2001-10-04
EP1138878B1 (en) 2008-05-14

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