EP2685047A1 - Aube/pale modulaire pour turbine à gaz et turbine à gaz avec une telle aube/pale - Google Patents

Aube/pale modulaire pour turbine à gaz et turbine à gaz avec une telle aube/pale Download PDF

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Publication number
EP2685047A1
EP2685047A1 EP12176275.1A EP12176275A EP2685047A1 EP 2685047 A1 EP2685047 A1 EP 2685047A1 EP 12176275 A EP12176275 A EP 12176275A EP 2685047 A1 EP2685047 A1 EP 2685047A1
Authority
EP
European Patent Office
Prior art keywords
blade
vane
modular
joint
inlay
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Withdrawn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
EP12176275.1A
Other languages
German (de)
English (en)
Inventor
Herbert Brandl
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 EP12176275.1A priority Critical patent/EP2685047A1/fr
Publication of EP2685047A1 publication Critical patent/EP2685047A1/fr
Withdrawn legal-status Critical Current

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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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/51—Building or constructing in particular ways in a modular way, e.g. using several identical or complementary parts or features

Definitions

  • the present invention relates to the technology of gas turbines. It refers to a modular vane/blade according to the preamble of claim 1. It further refers to a gas turbine with such a blade.
  • Fig. 1 which is a replica of Fig. 4 of document W02011 /058043 A1 , shows a modular turbine blade 10, where additional parts made of different material are joined with a central airfoil 11, said additional parts comprising a leading edge 13, a trailing edge 15 and a blade tip 12.
  • a buffer layer 14 may be provided between the leading edge part 13 and the central airfoil 11.
  • the blade airfoil element is constructed in different sections of different materials, especially also in the region of the blade airfoil.
  • the leading edge and the trailing edge of the rotor blade arrangement are formed totally of a material that is different from that of the remaining blade airfoil.
  • the regions which are formed of a different material extend downwards into the region of the blade airfoil element which is shrouded by the platform element, because the discontinuity which is associated with the transition between the regions of different material is then not exposed to the extreme temperature conditions which prevail in the region of the blade airfoil.
  • An aspect provides a modular vane/blade for a gas turbine which comprises the modular components of:
  • a further aspect provides that the runout is located above the essentially planar surface.
  • runout is located radially below the essentially planar surface.
  • a further aspect provides that the insert/inlay is joined to the platform.
  • a further aspect provides that the insert/inlay covers a portion of the basic element.
  • airfoil has a wall and the insert /inlay is a complete wall portion of the wall.
  • a further aspect provides that said joint is a welding joint.
  • a further aspect provides that said joint is a brazing joint.
  • a further aspect provides that said joint is a retainer joint.
  • Retainer joint in this case means a joint as disclosed in document US 5,797,725 A in Fig. 5 and 6 and col. 5 and 6 of the respective description.
  • An aspect provides a gas turbine according to the invention comprises a modular vane/blade according to the invention.
  • Fig. 2 shows a schematic drawing of a modular turbine vane design suitable for the present invention.
  • the vane 20 comprises an airfoil 18, an upper platform or shroud 19a and a lower platform 19b, which are separately manufactured by means of molding, or the like, are then put together, and finally joined by means of brazing, welding or a special retainer connection or joint as disclosed in document US 5,797,725 A in Fig. 5 and 6, and col. 5 and 6 of the respective description.
  • the separate manufacture so as to require joining defines the vane as a modular turbine vane.
  • the airfoil 18, which extends out from the essentially planar surface of the platform(s) comprises a main airfoil body (18a in Fig. 3-5 ) made of the first material, and one or more inserts/inlays made of a second, special material, which is/are suitable for high-temperature applications with reduced cooling air consumption compared to conventional vane/blade constructions.
  • the inserts/inlays are integrally joined with the main airfoil body, for example by means of brazing.
  • essentially planar surface is defined as a surface with contours typical of the surface of a platform of a blade/vane. Blade/vane surfaces typically range from planar to contoured surface.
  • An example of a contoured platform surface is provided in U.S. Patent Application No US2010/0143139 A1 .
  • a runout 23a-c is defined as a distal end of the insert/inlay 21 a-c that is closest to a platform.
  • a runout 23a-c is defined as a distal end of the insert/inlay 21 a-c that is closest to a platform.
  • the insert/inlay 21 a-c has two runouts 23a-c.
  • the runout 23a-c of exemplary embodiments are located in regions of low mechanical stress within said vane/blade, for example, by locating the runout 23a-c either below the essentially planar surface the platform 19a,b as shown in Figs 3 , 4 and 5 or having the runout 23 b,c located above the essentially planar surface of the platform 19a,b.
  • the essentially planar surface of the platform a,b is the reference point from which above and below are defined, wherein the direction of extension of the airfoil 11 is referred to as "above" while the direction into the platform 19 a,b, including through the platform 19a,b is referred to as " below”. Examples of runouts located below the essential plant surface as shown in Figs 3 , 4 and 5 .
  • Fig. 3 shows a side view ( Fig. 3a ) and a top view ( Fig. 3b ) of a vane 20a according to an embodiment of the invention.
  • an inlay/insert 21 a which is joined with a main airfoil body 18a by means of joint 22, makes up the leading edge of the airfoil.
  • the joint 22 is therefore established between the lower platform 19b and the inlay/insert 21 a, so that the lower runout 23a of the inlay/insert 21 lies well below the essentially planar (upper) surface of the lower platform 19b.
  • Fig. 4 shows a side view ( Fig. 4a ) and a top view ( Fig. 4b ) of a vane 20b according to another embodiment of the invention.
  • an inlay/insert 21 b covers the main airfoil body 18a at the leading edge.
  • "Covers" in this context, means compromises only a portion of the wall thickness of the airfoil as opposed to a complete wall portion that makes up the complete wall thickness of at least a portion of the airfoil.
  • a joint 22 is established between the lower platform 19b and the main airfoil body 18a.
  • the inlay/insert 21 b extends with its lower runout 23b well into the groove above said joint 22, so that again the runout is placed well below the platform's essentially planar surface.
  • Fig. 5 shows a side view ( Fig. 5a ) and a top view ( Fig. 5b ) of a vane 20c according to a further embodiment of the invention.
  • an inlay/insert 21 c which is joined with the main airfoil body 18a by means of joint 22, makes up the leading edge of the airfoil so as to be a complete wall portion of the airfoil.
  • the inlay/insert 21 c does not take part in the joint 22, but ends above joint 22, but with its runout 23c extending into the groove and in this way well below the platform's essentially planar surface, so that this embodiment can be considered a combination of the embodiments of Fig. 3 and 4 .

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  • Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12176275.1A 2012-07-13 2012-07-13 Aube/pale modulaire pour turbine à gaz et turbine à gaz avec une telle aube/pale Withdrawn EP2685047A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP12176275.1A EP2685047A1 (fr) 2012-07-13 2012-07-13 Aube/pale modulaire pour turbine à gaz et turbine à gaz avec une telle aube/pale

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12176275.1A EP2685047A1 (fr) 2012-07-13 2012-07-13 Aube/pale modulaire pour turbine à gaz et turbine à gaz avec une telle aube/pale

Publications (1)

Publication Number Publication Date
EP2685047A1 true EP2685047A1 (fr) 2014-01-15

Family

ID=46578852

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12176275.1A Withdrawn EP2685047A1 (fr) 2012-07-13 2012-07-13 Aube/pale modulaire pour turbine à gaz et turbine à gaz avec une telle aube/pale

Country Status (1)

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EP (1) EP2685047A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10801340B2 (en) 2014-10-24 2020-10-13 Raytheon Technologies Corporation Multi-piece turbine airfoil

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4650399A (en) * 1982-06-14 1987-03-17 United Technologies Corporation Rotor blade for a rotary machine
US5348446A (en) 1993-04-28 1994-09-20 General Electric Company Bimetallic turbine airfoil
US5797725A (en) 1997-05-23 1998-08-25 Allison Advanced Development Company Gas turbine engine vane and method of manufacture
US20060228211A1 (en) * 2005-04-07 2006-10-12 Siemens Westinghouse Power Corporation Multi-piece turbine vane assembly
US20100012450A1 (en) 2008-07-16 2010-01-21 Mando Corporation Floating piston valve of amplitude selective shock absorber
US20100080687A1 (en) * 2008-09-26 2010-04-01 Siemens Power Generation, Inc. Multiple Piece Turbine Engine Airfoil with a Structural Spar
EP2189626A1 (fr) 2008-11-20 2010-05-26 Alstom Technology Ltd Agencement d'aube de rotor, en particulier d'une turbine à gaz
US20100143139A1 (en) 2008-12-09 2010-06-10 Vidhu Shekhar Pandey Banked platform turbine blade
WO2011058043A1 (fr) 2009-11-12 2011-05-19 Siemens Aktiengesellschaft Composant de turbine modulaire et procédé pour sa fabrication
EP2362067A2 (fr) * 2010-02-26 2011-08-31 United Technologies Corporation Aube de soufflante de métal hybride

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4650399A (en) * 1982-06-14 1987-03-17 United Technologies Corporation Rotor blade for a rotary machine
US5348446A (en) 1993-04-28 1994-09-20 General Electric Company Bimetallic turbine airfoil
US5797725A (en) 1997-05-23 1998-08-25 Allison Advanced Development Company Gas turbine engine vane and method of manufacture
US20060228211A1 (en) * 2005-04-07 2006-10-12 Siemens Westinghouse Power Corporation Multi-piece turbine vane assembly
US20100012450A1 (en) 2008-07-16 2010-01-21 Mando Corporation Floating piston valve of amplitude selective shock absorber
US20100080687A1 (en) * 2008-09-26 2010-04-01 Siemens Power Generation, Inc. Multiple Piece Turbine Engine Airfoil with a Structural Spar
EP2189626A1 (fr) 2008-11-20 2010-05-26 Alstom Technology Ltd Agencement d'aube de rotor, en particulier d'une turbine à gaz
US20100143139A1 (en) 2008-12-09 2010-06-10 Vidhu Shekhar Pandey Banked platform turbine blade
WO2011058043A1 (fr) 2009-11-12 2011-05-19 Siemens Aktiengesellschaft Composant de turbine modulaire et procédé pour sa fabrication
EP2362067A2 (fr) * 2010-02-26 2011-08-31 United Technologies Corporation Aube de soufflante de métal hybride

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10801340B2 (en) 2014-10-24 2020-10-13 Raytheon Technologies Corporation Multi-piece turbine airfoil

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