DE10346240A1 - Component, e.g. blade, for gas turbine consists of two components connected via intermediate gap with metal oxide coating on one surface, to interrupt heat transfer from one component to second one - Google Patents

Component, e.g. blade, for gas turbine consists of two components connected via intermediate gap with metal oxide coating on one surface, to interrupt heat transfer from one component to second one Download PDF

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Publication number
DE10346240A1
DE10346240A1 DE2003146240 DE10346240A DE10346240A1 DE 10346240 A1 DE10346240 A1 DE 10346240A1 DE 2003146240 DE2003146240 DE 2003146240 DE 10346240 A DE10346240 A DE 10346240A DE 10346240 A1 DE10346240 A1 DE 10346240A1
Authority
DE
Germany
Prior art keywords
component
blade
gap
metal oxide
oxide coating
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.)
Withdrawn
Application number
DE2003146240
Other languages
German (de)
Inventor
Reinhard Fried
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 Technology 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 Technology AG filed Critical Alstom Technology AG
Priority to DE2003146240 priority Critical patent/DE10346240A1/en
Publication of DE10346240A1 publication Critical patent/DE10346240A1/en
Withdrawn legal-status Critical Current

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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2260/231—Preventing heat transfer

Landscapes

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

Abstract

The part has a first component (2), subjected to hot gases during operation, and a second component (3) fastened to the first. A gap (5) is formed in the outer wall (4) of the part (1) between the components. In at least one component, a surface area within the gap has a ceramic layer or metal oxide coating (6). The gap has a width of 1mu to 100mu . One component is cast on the second component, and the gap is formed automatically during cooling. The part is a blade, a heat shield, or a combustion chamber lining element. The first component is a main blade part, and the second component is a cover band, cover plate, blade foot, or blade fastener.
DE2003146240 2003-10-06 2003-10-06 Component, e.g. blade, for gas turbine consists of two components connected via intermediate gap with metal oxide coating on one surface, to interrupt heat transfer from one component to second one Withdrawn DE10346240A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE2003146240 DE10346240A1 (en) 2003-10-06 2003-10-06 Component, e.g. blade, for gas turbine consists of two components connected via intermediate gap with metal oxide coating on one surface, to interrupt heat transfer from one component to second one

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2003146240 DE10346240A1 (en) 2003-10-06 2003-10-06 Component, e.g. blade, for gas turbine consists of two components connected via intermediate gap with metal oxide coating on one surface, to interrupt heat transfer from one component to second one

Publications (1)

Publication Number Publication Date
DE10346240A1 true DE10346240A1 (en) 2005-04-21

Family

ID=34353329

Family Applications (1)

Application Number Title Priority Date Filing Date
DE2003146240 Withdrawn DE10346240A1 (en) 2003-10-06 2003-10-06 Component, e.g. blade, for gas turbine consists of two components connected via intermediate gap with metal oxide coating on one surface, to interrupt heat transfer from one component to second one

Country Status (1)

Country Link
DE (1) DE10346240A1 (en)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2295722A1 (en) * 2009-09-09 2011-03-16 Alstom Technology Ltd Blade of a Turbine
CN102869890A (en) * 2012-04-04 2013-01-09 弗拉斯季米尔·塞德拉切克 Method for fixing blade a blade ring by using fixed cable
EP2644828A1 (en) * 2012-03-29 2013-10-02 Siemens Aktiengesellschaft Modular turbine blade having a platform
EP2778347A1 (en) * 2013-03-11 2014-09-17 Siemens Aktiengesellschaft Rotor blade assembly, turbomachine comprising a rotor blade assembly and method of assembling a rotor blade assembly
WO2014158284A3 (en) * 2013-03-14 2014-12-04 Freeman Ted J Bi-cast turbine vane
CN106246232A (en) * 2015-06-12 2016-12-21 安萨尔多能源英国知识产权有限公司 For manufacturing method and the blade part assembly of blade part assembly
US9885245B2 (en) 2014-05-20 2018-02-06 Honeywell International Inc. Turbine nozzles and cooling systems for cooling slip joints therein
EP2412928A4 (en) * 2009-03-26 2018-02-28 IHI Corporation Cmc turbine stator vane
EP2412929A4 (en) * 2009-03-26 2018-02-28 IHI Corporation Cmc turbine stator vane
US9988932B2 (en) 2013-12-06 2018-06-05 Honeywell International Inc. Bi-cast turbine nozzles and methods for cooling slip joints therein

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE864176C (en) * 1946-11-27 1953-01-22 Svenska Rotor Maskiner Ab Arrangement on blade rims for gas and steam turbines to utilize leakage flow energy
US4260326A (en) * 1973-07-26 1981-04-07 Rolls-Royce Limited Blade for a gas turbine engine
DE19734273A1 (en) * 1997-08-07 1999-02-11 Siemens Ag Heat resistant vane

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE864176C (en) * 1946-11-27 1953-01-22 Svenska Rotor Maskiner Ab Arrangement on blade rims for gas and steam turbines to utilize leakage flow energy
US4260326A (en) * 1973-07-26 1981-04-07 Rolls-Royce Limited Blade for a gas turbine engine
DE19734273A1 (en) * 1997-08-07 1999-02-11 Siemens Ag Heat resistant vane

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2412928A4 (en) * 2009-03-26 2018-02-28 IHI Corporation Cmc turbine stator vane
EP2412929A4 (en) * 2009-03-26 2018-02-28 IHI Corporation Cmc turbine stator vane
JP2011058497A (en) * 2009-09-09 2011-03-24 Alstom Technology Ltd Blade of turbine
US8801381B2 (en) 2009-09-09 2014-08-12 Alstom Technology Ltd. Turbine blade
EP2295722A1 (en) * 2009-09-09 2011-03-16 Alstom Technology Ltd Blade of a Turbine
EP2644828A1 (en) * 2012-03-29 2013-10-02 Siemens Aktiengesellschaft Modular turbine blade having a platform
WO2013144270A1 (en) * 2012-03-29 2013-10-03 Siemens Aktiengesellschaft Modular turbine blade having a platform
CN102869890A (en) * 2012-04-04 2013-01-09 弗拉斯季米尔·塞德拉切克 Method for fixing blade a blade ring by using fixed cable
WO2013150336A1 (en) * 2012-04-04 2013-10-10 Vlastimil Sedlacek Method of securing of blades in blade ring with securing wire
WO2014139714A1 (en) * 2013-03-11 2014-09-18 Siemens Aktiengesellschaft Rotor blade assembly, turbomachine comprising a rotor blade assembly and method of assembling a rotor blade assembly
EP2778347A1 (en) * 2013-03-11 2014-09-17 Siemens Aktiengesellschaft Rotor blade assembly, turbomachine comprising a rotor blade assembly and method of assembling a rotor blade assembly
US9803486B2 (en) 2013-03-14 2017-10-31 Rolls-Royce North American Technologies Inc. Bi-cast turbine vane
WO2014158284A3 (en) * 2013-03-14 2014-12-04 Freeman Ted J Bi-cast turbine vane
US10612402B2 (en) 2013-03-14 2020-04-07 Rolls-Royce North American Technologies Inc. Method of assembly of bi-cast turbine vane
US9988932B2 (en) 2013-12-06 2018-06-05 Honeywell International Inc. Bi-cast turbine nozzles and methods for cooling slip joints therein
US9885245B2 (en) 2014-05-20 2018-02-06 Honeywell International Inc. Turbine nozzles and cooling systems for cooling slip joints therein
CN106246232A (en) * 2015-06-12 2016-12-21 安萨尔多能源英国知识产权有限公司 For manufacturing method and the blade part assembly of blade part assembly

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Legal Events

Date Code Title Description
OM8 Search report available as to paragraph 43 lit. 1 sentence 1 patent law
8139 Disposal/non-payment of the annual fee