EP2878769A1 - Aube rotorique d'une turbine à gaz avec des léchettes d'étanchéité de plateforme - Google Patents

Aube rotorique d'une turbine à gaz avec des léchettes d'étanchéité de plateforme Download PDF

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Publication number
EP2878769A1
EP2878769A1 EP14193984.3A EP14193984A EP2878769A1 EP 2878769 A1 EP2878769 A1 EP 2878769A1 EP 14193984 A EP14193984 A EP 14193984A EP 2878769 A1 EP2878769 A1 EP 2878769A1
Authority
EP
European Patent Office
Prior art keywords
sealing rib
radial height
maximum radial
circumferential
edge
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Withdrawn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
EP14193984.3A
Other languages
German (de)
English (en)
Inventor
Alexander Böck
Sven Schmid
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines 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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP2878769A1 publication Critical patent/EP2878769A1/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Withdrawn legal-status Critical Current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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F05D2230/11—Manufacture by removing material by electrochemical methods
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making

Definitions

  • the present invention relates to a blade for a turbine or compressor stage of a gas turbine, a gas turbine, in particular an aircraft engine gas turbine, with such a blade and a method for producing such a blade.
  • the EP 2 402 559 A1 therefore proposes, in a shroud pocket delimited circumferentially by two opposing z-shaped ribs, to arrange at least one reinforcing rib which extends substantially in the direction of the maximum or the principal axis of inertia of the blade or its radially outer portion.
  • An object of an embodiment of the present invention is to provide a gas turbine, in particular, to reduce at least one of the disadvantages explained above.
  • Claims 8, 9 provide a gas turbine with a corresponding blade or a method for producing a corresponding blade under protection.
  • Advantageous embodiments of the invention are the subject of the dependent claims.
  • a gas turbine in particular an aircraft engine gas turbine, one or more turbine stages and one or more compressor stages, each having one or more circumferentially distributed blades on.
  • the blades can be detachably or non-detachably, in particular cohesively, connected to a rotor of the gas turbine or be formed integrally with this or be.
  • At least one of these blades has a radially outer shroud.
  • the shroud may be integrally formed with an airfoil of the blade, in particular ur- and / or reshaped, or materially connected, in particular welded or be.
  • the shroud has two edges which face each other in the circumferential direction. These are z-shaped in one embodiment.
  • the shrouds in the circumferential direction of adjacent blades touch each other along their edges.
  • the shroud On its radially outer, blade-side facing away from the outer surface, the shroud has a sealing rib arrangement with at least three sealing ribs, in particular a first sealing rib, one of these adjacent second sealing rib and one of the second sealing rib adjacent, the first sealing rib opposite third sealing rib.
  • the sealing rib arrangement can also have one or more further sealing ribs, in particular a fourth sealing rib adjacent to the third sealing rib, a fourth sealing rib adjacent to the second sealing rib, the fifth sealing rib opposite the third sealing rib, etc.
  • the first sealing rib is a leading edge closest sealing rib, in another embodiment, a trailing edge downstream seal rib.
  • the sealing rib arrangement is opposite a housing sealing surface of the gas turbine.
  • the sealing ribs extend in one embodiment, at least substantially, in the circumferential direction. In one embodiment, different, in particular in the axial direction adjacent sealing ribs, different radial heights, in particular, to follow a divergent or convergent flow channel in which the blade is located.
  • Each two adjacent sealing ribs in the axial direction are each connected to each other by a groove bottom.
  • one or both sealing ribs, in particular in a, in particular rounded, edge pass into the groove base, which additionally or alternatively in at least one meridian section, in particular all meridian sections, in the axial direction may have an at least substantially constant radial height.
  • the first and second sealing rib are connected by a groove bottom, which is referred to below as the first groove bottom, the second and third sealing rib by a groove bottom, which is hereinafter referred to as a second groove bottom.
  • a groove bottom between a further sealing rib and one of these adjacent sealing rib, in particular a groove bottom, the third and one of the third sealing rib adjacent, the second sealing rib opposite fourth sealing rib or such a fourth sealing rib and the fourth sealing rib adjacent, the third sealing rib opposite fifth Sealing rib connects, is referred to in each case as another groove bottom.
  • At least the first and second groove base in one embodiment also at least one, in particular all other groove bases, each have a region of maximum radial height in the circumferential direction.
  • radial height is meant in the present case in particular a distance to a rotational axis of the gas turbine or to a blade root of the blade.
  • a groove base in the circumferential direction has two opposing flanks which merge into one another in an edge, in particular this edge can be a circumferential region of maximum radial height in the sense of the present invention. If, in another embodiment, a groove base in the circumferential direction has two opposing flanks which merge into two plateaus in two edges, then in particular this plateau can be a circumferential region of maximum radial height in the sense of the present invention.
  • a circumferential region of maximum radial height of a groove bottom is arranged in the circumferential direction at a circumferential position. If the circumferential area of maximum radial height is an edge in which two opposing flanks merge, the circumferential position of this edge may be the circumferential position of the circumferential area of maximum radial height. If the circumferential area of maximum radial height is a plateau into which two opposing flanks merge into two edges, in particular the circumferential position of the leading edge near edge, the leading edge distal edge, or the middle between both edges can be the circumferential position of the circumferential area of maximum radial height in the sense of the present invention Be invention.
  • the circumferential position of the circumferential portion of the maximum radial height of the first groove bottom is referred to as the first circumferential position for discrimination, the circumferential position of the circumferential portion of the maximum radial height of the second groove bottom as the second circumferential position, the circumferential position of the circumferential portion of the maximum radial height of another groove base as a corresponding circumferential position.
  • the first and second circumferential positions are different.
  • the circumferential area of the maximum radial height of the first groove bottom is offset from the circumferential area of the maximum radial height of the second groove base in the circumferential direction.
  • one or more further circumferential positions may be different from the first and / or second circumferential position, or a circumferential region of maximum radial height of at least one further groove base may be offset in the circumferential direction against the circumferential region of maximum radial height of the first and / or second groove base.
  • the circumferential positions of the circumferential areas of maximum radial height of all groove bottoms are different from one another or the circumferential regions of maximum radial height of all groove bottoms are offset from one another in the circumferential direction.
  • a stiffening rib within the sealing rib arrangement available are provided, which is inclined at least partially against the axis of rotation, in particular, to counteract a distortion of the shroud due to centrifugal forces.
  • first and second groove bottom are each formed like a ridge, wherein the ridges are circumferentially offset from each other, this results in a stiffening rib on both groove grounds, which diagonally intersects the second rib arranged therebetween and simply through each opposing, offset in the circumferential direction grinding of the first and second groove bottom can be made.
  • a circumferential position of a circumferential area of maximum radial height of a leading edge remote groove bottom is offset from a circumferential position of a circumferential area of maximum radial height of a leading edge near groove bottom in the circumferential direction from a rear edge to a leading edge of the blade.
  • the circumferential region of the maximum radial height of the second, more downstream groove base relative to the peripheral region of maximum radial height of the first upstream groove base may be circumferentially offset to a leading edge of the rotor blade.
  • the peripheral portions of the maximum radial height may be circumferentially offset from each other so as to form a continuous diagonal rib crossing the peripheral ribs of the rib assembly.
  • one or more, in particular all groove bases of the sealing rib arrangement each have a first flank and a second flank opposite thereto.
  • the first flank increases in the circumferential direction to the peripheral region of maximum radial height
  • the second edge decreases in the circumferential direction from the peripheral region of maximum radial height starting from.
  • the first and second flanks may merge into one another, in particular rounded edges, or transition into two, in particular rounded, edges into a plateau of at least substantially constant radial height, as explained above.
  • the first flank may in particular rise from a first edge of the shroud, the second flank additionally or alternatively fall down to a second edge of the shroud opposite the first edge in the circumferential direction.
  • the processing in particular the entry or exit of a tool in or out of the groove can be improved.
  • the radial height of the first and / or second edge in the circumferential direction monotonically, in particular strictly monotone, change, in other words, the first edge, in particular from the first edge, to the peripheral region of maximum radial height monotone, in particular increase strictly monotonically and / or the second edge of the peripheral region of maximum radial height, in particular down to the second edge, monotonically, in particular strictly monotonically decrease.
  • the first and / or second flank may be linear or straight in the circumferential direction.
  • the groove bottoms are circumferentially offset from each other peripheral areas maximum radial height in particular for machining, in particular by machining with geometrically undefined cutting edge, preferably grinding, honing, lapping and / or jets.
  • a groove bottom in one embodiment can also be contoured by machining with a geometrically determined cutting edge, preferably filing, milling and / or sawing, by, in particular thermal and / or electrochemical, ablation, in particular die sinking, and / or Archetypes, in particular casting.
  • Fig. 1A shows in a plan view in the radial direction from the outside a shroud 1 of a blade of a turbine stages of an aircraft engine gas turbine according to an embodiment of the present invention, the Fig. 1B to 1D Sections along the lines BB ( Fig. 1B ), CC ( Fig. 1C ) or DD ( Fig. 1D ) in Fig. 1A ,
  • the radially outer shroud is formed integrally with a blade 2 of the blade, which in Fig. 1B to 1D partially shown. It has two edges (top, bottom in Fig. 1 ), which in the circumferential direction (vertically in Fig. 1 ) are opposite and Z-shaped.
  • the shroud On its radially outer, blade-side facing away lateral surface (right in Fig. 1B to 1D ), the shroud has a sealing rib arrangement with a first, front edge next or upstream (left in Fig. 1A ) Sealing rib 3.1, one of these adjacent second sealing rib 3.2, one of the second sealing rib adjacent, the first sealing rib opposite third sealing rib 3.3 and the third sealing rib adjacent, the second sealing rib opposite another, hinterkanten consideringe or strömungsabissertigste (right in Fig. 1A ) Sealing rib 3.4.
  • the sealing ribs extend in the circumferential direction (vertically in Fig. 1 ).
  • the first and second sealing rib are connected by a first groove bottom 10, the second and third sealing rib by a second groove bottom 20, the third and further sealing rib by a further groove bottom 30th
  • the groove bottoms each have a first flank 11, 21 and 31, and a second flank 12, 22 and 32, which is in opposite directions for this purpose.
  • the first flank increases in the circumferential direction (from top to bottom in Fig. 1B to 1D ) from a first edge of the shroud (at the top of FIG Fig. 1 ) linearly to an edge 13, 23 and 33, respectively, in which it merges into the second flank, which in opposite directions up to a second edge of the shroud opposite the first edge in the circumferential direction (bottom in FIG Fig. 1 ) decreases linearly.
  • these edges 13, 23, 33 each form a circumferential region of maximum radial height of the respective groove base 10, 20 and 30, respectively.
  • edges or peripheral regions of maximum radial height 13, 23 and 33 of the first, second and further groove base are offset from each other in the circumferential direction, as shown in particular the synopsis of the sections 1B, 1C and 1D.
  • the second circumferential position of the peripheral portion 23 of the second groove bottom is against the first circumferential position of the peripheral portion 13 of the leading edge next groove base in the circumferential direction from a rear edge to a leading edge of the blade (from top to bottom in FIG Fig. 1 ), as shown in particular by the synopsis of sections 1B and 1C.
  • the further circumferential position of the further peripheral region 33 of the front edge remote groove bottom 30 is offset in the same way against the second circumferential position of the peripheral region 23 of the groove base in the circumferential direction, as shown in particular by the synopsis of the sections 1C and 1D.
  • the circumferential areas of maximum radial height 13, 23 and 33 of the three adjacent groove bases 10, 20 and 30 lie on a straight line.
  • FIG. 2B to 2D show in Fig. 1B to 1D Similarly, sections through a blade according to an alternative embodiment of the present invention, the a plan view in the radial direction from the outside Fig. 1A equivalent. Corresponding elements are denoted by identical reference numerals, so that reference is made to the above description and will be discussed below only the differences.
  • Fig. 2 In the execution of Fig. 2 go the first and second flanks 11, 12; 21, 22 and 31, 32 in each case in two edges in a plateau 13, 23 and 33 constant, maximum radial height, which thus each forms the peripheral region of maximum radial height in the sense of the present invention.
  • Its circumferential position may, in particular, the circumferential position of the front edge closer (in Fig. 2 lower edge), the leading edge farther edge (in Fig. 2 above) or the middle between both edges.
  • the second circumferential position of the peripheral portion 23 of the second groove bottom is against the first circumferential position of the peripheral portion 13 of the leading edge nearest groove bottom in the circumferential direction from a rear edge to a leading edge of the blade (from top to bottom in FIG Fig. 2 ), as shown in particular by the synopsis of sections 2B and 2C.
  • the further circumferential position of the further peripheral region 33 of the front edge remote groove bottom 30 is offset in the same way against the second circumferential position of the circumferential region 23 of the groove base in the circumferential direction, as shown in particular the synopsis of the sections 2C and 2D.
  • the circumferential areas of maximum radial height 13, 23 and 33 of the three adjacent groove bottoms 10, 20 and 30 are again on a straight line.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP14193984.3A 2013-11-27 2014-11-20 Aube rotorique d'une turbine à gaz avec des léchettes d'étanchéité de plateforme Withdrawn EP2878769A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102013224199.2A DE102013224199A1 (de) 2013-11-27 2013-11-27 Gasturbinen-Laufschaufel

Publications (1)

Publication Number Publication Date
EP2878769A1 true EP2878769A1 (fr) 2015-06-03

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP14193984.3A Withdrawn EP2878769A1 (fr) 2013-11-27 2014-11-20 Aube rotorique d'une turbine à gaz avec des léchettes d'étanchéité de plateforme

Country Status (3)

Country Link
US (1) US9739156B2 (fr)
EP (1) EP2878769A1 (fr)
DE (1) DE102013224199A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3176388A1 (fr) * 2015-12-04 2017-06-07 MTU Aero Engines GmbH Segment d'aube directrice à sécurité radiale

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11105209B2 (en) 2018-08-28 2021-08-31 General Electric Company Turbine blade tip shroud
US11156110B1 (en) 2020-08-04 2021-10-26 General Electric Company Rotor assembly for a turbine section of a gas turbine engine
US11655719B2 (en) 2021-04-16 2023-05-23 General Electric Company Airfoil assembly

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH10306702A (ja) * 1997-05-08 1998-11-17 Mitsubishi Heavy Ind Ltd ガスタービン翼
US20050079058A1 (en) * 2003-10-09 2005-04-14 Pratt & Whitney Canada Corp. Shrouded turbine blades with locally increased contact faces
EP1830037A2 (fr) * 2006-03-02 2007-09-05 Hitachi, Ltd. Aube de turbine à vapeur
DE102009030566A1 (de) * 2009-06-26 2010-12-30 Mtu Aero Engines Gmbh Deckbandsegment zur Anordnung an einer Schaufel
EP2402559A1 (fr) 2010-07-01 2012-01-04 MTU Aero Engines AG Aube de turbine avec plateforme d'extrémité
US20120195766A1 (en) * 2011-02-02 2012-08-02 Snecma Cmc turbine engine blades and a rotor wheel for a turbine engine and a turbine engine integrating them
FR2985759A1 (fr) * 2012-01-17 2013-07-19 Snecma Aube mobile de turbomachine
US20130259699A1 (en) * 2010-11-22 2013-10-03 Snecma Movable blade for a turbomachine
WO2014137479A1 (fr) * 2013-03-07 2014-09-12 Shaffer Don L Aubes carénées de moteur à turbine à gaz et procédés correspondants

Family Cites Families (38)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2749026A (en) * 1951-02-27 1956-06-05 United Aircraft Corp Stator construction for compressors
CH355327A (de) * 1959-07-27 1961-06-30 Bbc Brown Boveri & Cie Axialturbine, insbesondere Gasturbine
US3251601A (en) * 1963-03-20 1966-05-17 Gen Motors Corp Labyrinth seal
US3339933A (en) * 1965-02-24 1967-09-05 Gen Electric Rotary seal
US3537713A (en) * 1968-02-21 1970-11-03 Garrett Corp Wear-resistant labyrinth seal
US4460185A (en) * 1982-08-23 1984-07-17 General Electric Company Seal including a non-metallic abradable material
US4512712A (en) * 1983-08-01 1985-04-23 United Technologies Corporation Turbine stator assembly
JPS6123804A (ja) * 1984-07-10 1986-02-01 Hitachi Ltd タ−ビン段落構造
US4836561A (en) * 1987-02-17 1989-06-06 University Of New Mexico Wavy-tilt-dam seal ring
JPH07229403A (ja) * 1994-02-21 1995-08-29 Hitachi Ltd タービン動翼の先端部連結装置
GB2290833B (en) * 1994-07-02 1998-08-05 Rolls Royce Plc Turbine blade
GB9419712D0 (en) * 1994-09-30 1994-11-16 Rolls Royce Plc A turbomachine aerofoil and a method of production
FR2732416B1 (fr) * 1995-03-29 1997-04-30 Snecma Agencement de raccordement de deux secteurs angulaires de turbomachine et joint concu pour servir dans cet agencement
GB2307520B (en) * 1995-11-14 1999-07-07 Rolls Royce Plc A gas turbine engine
US5833518A (en) * 1996-08-02 1998-11-10 Flowserve Management Company Method for forming a wavy face ring
US6425736B1 (en) * 1999-08-09 2002-07-30 United Technologies Corporation Stator assembly for a rotary machine and method for making the stator assembly
DE10047307A1 (de) * 2000-09-25 2002-08-01 Alstom Switzerland Ltd Dichtungsanordnung
US6454526B1 (en) * 2000-09-28 2002-09-24 Siemens Westinghouse Power Corporation Cooled turbine vane with endcaps
US6896483B2 (en) * 2001-07-02 2005-05-24 Allison Advanced Development Company Blade track assembly
JP2003214113A (ja) * 2002-01-28 2003-07-30 Toshiba Corp 地熱タービン
US6648332B1 (en) * 2002-07-29 2003-11-18 General Electric Company Steam turbine packing casing horizontal joint seals and methods of forming the seals
DE10250779A1 (de) * 2002-10-30 2004-05-19 Alstom (Switzerland) Ltd. Notkühlsystem für ein hitzebelastetes Bauteil
JP4254352B2 (ja) * 2003-06-04 2009-04-15 株式会社Ｉｈｉ タービンブレード
DE10348290A1 (de) * 2003-10-17 2005-05-12 Mtu Aero Engines Gmbh Dichtungsanordnung für eine Gasturbine
DE10360164A1 (de) * 2003-12-20 2005-07-21 Mtu Aero Engines Gmbh Gasturbinenbauteil
DE102004025321A1 (de) 2004-05-19 2005-12-08 Alstom Technology Ltd Strömungsmaschinenschaufel
GB2422641B (en) * 2005-01-28 2007-11-14 Rolls Royce Plc Vane for a gas turbine engine
GB2434842A (en) * 2006-02-02 2007-08-08 Rolls Royce Plc Cooling arrangement for a turbine blade shroud
US8016565B2 (en) * 2007-05-31 2011-09-13 General Electric Company Methods and apparatus for assembling gas turbine engines
JP4991663B2 (ja) * 2007-09-11 2012-08-01 株式会社日立製作所 蒸気タービン動翼組立体
FR2933884B1 (fr) * 2008-07-16 2012-07-27 Snecma Procede de fabrication d'une piece d'aubage.
US20130259691A1 (en) * 2009-07-17 2013-10-03 General Electric Company Perforated turbine bucket tip cover
JP5526223B2 (ja) * 2010-03-29 2014-06-18 株式会社日立製作所 Ｎｉ基合金、並びにそれを用いたガスタービン動翼及び静翼
US8002286B1 (en) * 2010-06-14 2011-08-23 Florida Turbine Technologies, Inc. Aerodynamically mistuned labyrinth seal
US9115591B2 (en) * 2011-08-30 2015-08-25 United Technologies Corporation Universal seal
DE102012201052A1 (de) * 2012-01-25 2013-07-25 Mtu Aero Engines Gmbh Mehrteilige Elektrodenanordnung und Verfahren zur elektrochemischen Bearbeitung von Schaufeln mit Deckbändern
US9022390B2 (en) * 2012-09-05 2015-05-05 United Technologies Corporation Threaded seal for a gas turbine engine
ES2935815T3 (es) * 2013-09-06 2023-03-10 MTU Aero Engines AG (Des)montaje de un rotor de una turbina de gas, en particular delantero

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH10306702A (ja) * 1997-05-08 1998-11-17 Mitsubishi Heavy Ind Ltd ガスタービン翼
US20050079058A1 (en) * 2003-10-09 2005-04-14 Pratt & Whitney Canada Corp. Shrouded turbine blades with locally increased contact faces
EP1830037A2 (fr) * 2006-03-02 2007-09-05 Hitachi, Ltd. Aube de turbine à vapeur
DE102009030566A1 (de) * 2009-06-26 2010-12-30 Mtu Aero Engines Gmbh Deckbandsegment zur Anordnung an einer Schaufel
EP2402559A1 (fr) 2010-07-01 2012-01-04 MTU Aero Engines AG Aube de turbine avec plateforme d'extrémité
US20130259699A1 (en) * 2010-11-22 2013-10-03 Snecma Movable blade for a turbomachine
US20120195766A1 (en) * 2011-02-02 2012-08-02 Snecma Cmc turbine engine blades and a rotor wheel for a turbine engine and a turbine engine integrating them
FR2985759A1 (fr) * 2012-01-17 2013-07-19 Snecma Aube mobile de turbomachine
WO2014137479A1 (fr) * 2013-03-07 2014-09-12 Shaffer Don L Aubes carénées de moteur à turbine à gaz et procédés correspondants

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3176388A1 (fr) * 2015-12-04 2017-06-07 MTU Aero Engines GmbH Segment d'aube directrice à sécurité radiale
DE102015224378A1 (de) * 2015-12-04 2017-06-08 MTU Aero Engines AG Leitschaufelsegment mit Radialsicherung
US10370989B2 (en) 2015-12-04 2019-08-06 MTU Aero Engines AG Guide vane segment with radical securing elements

Also Published As

Publication number Publication date
DE102013224199A1 (de) 2015-05-28
US20150167477A1 (en) 2015-06-18
US9739156B2 (en) 2017-08-22

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