EP3517736A1 - Rampe pour plaque de recouvrement d'aube directrice et embase d'aube mobile - Google Patents

Rampe pour plaque de recouvrement d'aube directrice et embase d'aube mobile Download PDF

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Publication number
EP3517736A1
EP3517736A1 EP19160922.1A EP19160922A EP3517736A1 EP 3517736 A1 EP3517736 A1 EP 3517736A1 EP 19160922 A EP19160922 A EP 19160922A EP 3517736 A1 EP3517736 A1 EP 3517736A1
Authority
EP
European Patent Office
Prior art keywords
blade
turbomachine
cover plate
rotor shaft
base plate
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Withdrawn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
EP19160922.1A
Other languages
German (de)
English (en)
Inventor
Markus Schlemmer
Martin Pernleitner
Manfred Dopfer
Marcus WÖHLER
Oliver Thiele
Bernd Kislinger
Norman Cleesattel
Christoph Lauer
Manfred Schill
Manuel Hein
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 EP3517736A1 publication Critical patent/EP3517736A1/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Withdrawn legal-status Critical Current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
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/06—Shutting-down
    • 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
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/24—Rotors for turbines
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • 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
    • F05D2260/90—Braking
    • 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
    • F05D2260/90—Braking
    • F05D2260/902—Braking using frictional mechanical forces

Definitions

  • the invention relates to a blade for a turbomachine and an assembly for a turbomachine.
  • Turbomachines such as aeroengines and stationary gas turbines
  • a rotor having a plurality of blades and at least one axially adjacent row of blades.
  • the vanes serve to optimize the flow conditions for the blades; In the main flow direction vanes and blades are arranged one behind the other.
  • the term "vane” or “vane segment” is to be understood in the context of the present invention wide, especially in the sense of "stator”. Thus, this term also encompasses flow-deflecting profiles disposed axially behind the last row of blades of a low-pressure turbine as part of a so-called turbine exhaust casing, and flow-deflecting profiles arranged as components of a turbine casing between two turbine regions, such as low-pressure turbine and high-pressure turbine.
  • a vane row may include a radially inner and a radially outer shroud as well as a plurality of vane blades disposed therebetween;
  • the terms "radial” or “radial”, “axial” or “axial” and “circumferential” refer in this document - unless otherwise stated - always on the axis of rotation of a (existing or intended) rotor shaft which is surrounded by the vane row.
  • the axis of rotation corresponds to the so-called machine axis of the turbomachine.
  • the vane row may be composed of a plurality of vane segments, each of which may include a radially inner and / or a radially outer cover plate and a vane blade or a plurality of vane blades.
  • the radially inner cover plates together form the inner shroud and the radially outer cover plates form the outer shroud; the shrouds are preferably each formed as a closed ring which forms a radial boundary for the main gas flow.
  • the rotor blades can analogously have a base plate which is set up, for example via a rotor disk plugged or inserted blade root to be attached to a rotor shaft or to be.
  • a base plate has a projection in the axial direction, which is adapted to reduce a radial leakage flow together with a projection of the shroud of a row of guide vanes.
  • the present invention therefore has the object to provide a technique with which the negative effects of such a rotor shaft break are reduced.
  • a vane segment for a turbomachine according to the invention has at least one vane with a radially inner cover plate;
  • the attribute "radially inner” refers to an intended or already realized arrangement of the vane segment in a turbomachine (or on its axis of rotation).
  • the cover plate has a cover plate surface, which is adapted to be arranged in the turbomachine of the guide vane segment, in particular upstream, facing blade row or to be. In this case, the cover plate surface extends substantially along a (imaginary) conical surface, whose cone axis coincides with the axis of rotation of a rotor shaft.
  • the vane segment is thus adapted to be assembled with one or more further vane segments and thereby form an annular vane row whose central axis coincides with the axis of rotation of the rotor shaft.
  • the cover plate surface in the axial direction of a, in particular upstream adjacent, blade row faces and extends along the conical surface (which is preferably the lateral surface of a straight circular cone), that is formed conically to the axis of rotation.
  • the cover plate surface is preferably - viewed in a direction provided for the main flow direction - arranged on the front side of the cover plate.
  • a guide blade segment for a turbomachine according to the invention also has a radially outer cover plate;
  • the attribute "radially outer” here refers to an intended or already realized arrangement of the vane segment in a turbomachine (and its axis of rotation).
  • At least one vane blade is preferably arranged between the radially inner and a radially outer cover plate.
  • a turbomachine blade comprises a base plate in a radially inner region (e.g., one-third, one-fourth, or one-fifth of an extension of the blade facing the rotor shaft in the radial direction); this base plate has a base plate surface, which is adapted to be arranged in the turbomachine a shroud facing one of the blade adjacent vane row and thereby to extend substantially along a (imaginary) conical surface; whose cone axis coincides with the axis of rotation of a rotor shaft.
  • the base plate surface is preferably - viewed in an intended main flow direction - arranged on the back of the base plate.
  • An assembly according to the invention for a turbomachine and a turbomachine according to the invention each have a stator segment for a turbomachine according to the invention disclosed in one embodiment of the invention and a blade according to one of the embodiments disclosed in this document, wherein the blade is preferably arranged axially in front of the stator blade segment ,
  • a guide blade segment for a turbomachine according to the invention and a rotor blade according to the invention each have a ramp surface which can cause the rotor to brake when the rotor shaft breaks.
  • Particularly advantageous for this purpose are the use of a combination of a stator segment for a turbomachine according to the invention and a rotor blade according to the invention, in which the cover plate surface and the base plate surface run each other at a rotor shaft break (in which they are arranged for example substantially at the same radial distance from the rotor shaft ); It is particularly advantageous if the respective conical surface areas have substantially the same opening angle. In this case, high frictional forces can be generated in a rotor shaft break and resulting emergence of the base plate surface on the adjacent cover plate surface, which cause a corresponding deceleration.
  • the conical surface areas along which the (mentioned) cover plate surface of the guide blade segment and the (mentioned) base plate surface of the blade run have substantially the same opening angles.
  • the cover plate surface and the base plate surface are arranged in a turbomachine according to the invention substantially at the same radial distance from the rotor shaft.
  • the cover plate surface of a guide blade segment for a turbomachine according to the invention is oriented radially inwards, that is to say it is arranged to be (obliquely) facing the rotor shaft in a turbomachine.
  • the cover plate surface thus abuts against an outer surface of a cone with said conical surface.
  • the base plate surface of a blade according to the invention is advantageously directed radially outward, so arranged to be arranged facing away in a turbomachine rotor shaft.
  • the base plate surface thus abuts against an inner surface of a cone with said conical surface.
  • the conical surface along which the cover plate surface extends is angled relative to the axis of rotation of the rotor shaft by at most 80 °, more preferably at most 60 °, even more preferably at most 50 °.
  • the associated cone thus has an opening angle of at most 160 °, 120 ° or 100 °.
  • the conical surface along which the baseplate surface of a blade according to the invention passes is preferably angled with respect to the axis of the rotor shaft by at most 80 °, more preferably at most 60 °, even more preferably at most 50 °; the associated cone thus has an opening angle of at most 160 °, 120 ° or 100 °.
  • the guide vanes and rotor blades of the turbomachine according to the invention are preferably configured in such a way that in the event of a shaft break and a concomitant translatory displacement of the blade row in the axial direction to the rear, i. in the flow direction, first the cover plate surface of the radially inner cover plate of the vane segment comes into contact with the base plate surface of the base plate of the moving blade.
  • the rotational energy of the broken off part of the rotor in a predetermined component section of the turbomachine can be reduced, i. be converted into frictional heat.
  • the surface used for this purpose is formed relatively large compared to the prior art due to the inclination of the cover plate surface and / or base plate surface to the axis of rotation.
  • a part of the force with which the broken off part of the rotor is pressed axially backwards by the flow acting on the rotor blades is deflected in the radial direction on emergence onto the cover plate surfaces of the guide blade segments due to the previously described inclination of the contact surfaces ,
  • the guide vanes can be designed more easily, without the risk that they also break off in a wave breakage.
  • a vane segment 10 according to one embodiment of the present invention is illustrated.
  • the vane segment 10 comprises an outer cover plate 12 and an inner cover plate 13, which respectively describe segments of nested cover bands with the same central axis; Between the outer cover plate 12 and the inner cover plate 13, a plurality of blades 11 is arranged.
  • the vane segment 10 is configured to form, together with other (not shown), analogously formed stator blade segments, a row of guide vanes which runs as a ring around a rotary shaft or machine axis of the turbomachine. Its axis of rotation is substantially coincident with a central axis of the vane row, and with respect to it, the blades 11 extend substantially radially.
  • the radially inner cover plate 13 has, on its side facing the central axis, a fastening element 15 for fastening at least one seal, which may in particular comprise at least one sealing ring.
  • the cover plate 13 has a cover plate surface 14, which is adapted to be arranged in the turbomachine facing the blade segment 10 axially adjacent blade.
  • the shroud surface 14 is tapered conically, thus extends substantially along an (imaginary) conical surface around the central axis (not shown) (and thus about the axis of rotation of the rotor shaft); this will be determined by the Figures 2 and 3 clarified.
  • FIG. 3 schematically shows an arrangement of an exemplary vane segment 10 for a turbomachine according to the invention and an exemplary rotor blade 20 according to the invention in a sectional illustration;
  • This arrangement may be, for example, in a turbomachine according to the invention are present, in particular in a turbine region of the same.
  • the blade 20 is connected to a rotor shaft 30 and adapted to rotate with the rotor shaft about its axis of rotation A.
  • This axis of rotation is also a central axis of the arrangement shown, with respect to which the blade 10 and the blades 11 of the blade segment are substantially radially aligned.
  • the direction R of a planned main flow runs in the illustration of FIG. 2 left to right.
  • the vane segment 10 has a radially inner cover plate 13, a radially outer cover plate 12 and an airfoil 11 therebetween.
  • a sealing element 16 is preferably radially displaceable, in particular by means of a memory-centering suspension attached:
  • the rotor blade 20 has, in a radially inner region, a base plate 23, from which a rotor blade 21 extends radially outward.
  • the base plate has on the (in the axial direction) the guide vane segment 10 side facing a projection 26, which together with the inner cover plate 13 of the vane segment reduces an adverse radial flow.
  • the inner cover plate 13 of the vane segment 10 has a cover plate surface 14 which faces a base plate surface 24 of the base plate 23 of the blade 20; Both surfaces are arranged substantially at the same radial distance from the rotor shaft 30.
  • the base plate surface 24 is arranged on a rear side of the base plate 23 and the cover plate surface 14 on a front side of the cover plate 13. At a fraction of the Rotor shaft can thus accumulate the base plate surface 24 on the cover plate surface 14, so that the rotor is advantageously braked.
  • the cover plate surface 14 and the base plate surface 24 are each arranged along (imaginary) conical surface areas; in the circular enlargement section is shown by a parallel P to the axis of rotation A, that the cover plate surface 14 and the base plate surface 24 are angled relative to the axis of rotation A by the angle ⁇ and ⁇ ;
  • ⁇ and ⁇ are each at most 80 °, more preferably at most 60 °, even more preferably at most 50 °. It is particularly advantageous if ⁇ and ⁇ are substantially the same size; As a result, both surfaces have a particularly large contact surface in the event of their emergence on each other, resulting in a particularly large braking friction effect.
  • FIG. 3 is the arrangement according to the FIG. 2 illustrated with the (imaginary) conical surfaces:
  • the cover plate surface 14 extends along the conical surface K 1 , which has an opening angle of 2 ⁇ .
  • the base plate surface 24 extends analogously along the conical surface K 2 , which has an opening angle of 2 ⁇ . In the illustrated example, this is ⁇ ⁇ , wherein these two angles could be designed in a modified embodiment substantially the same.
  • a vane segment 10 for a turbomachine comprises a radially inner cover plate 13 with a cover plate surface 14 which is adapted to be arranged in the turbomachine facing a blade 20 adjacent the bucket segment and thereby to extend substantially along a conical surface K 1 , the cone axis coincides with the axis of rotation A of a rotor shaft 30.
  • a rotor blade 20 for a turbomachine has in a radially inner region a base plate 23 with a base plate surface 24 which is adapted to be arranged in the turbomachine a shroud facing one of the blade adjacent vane row 10 and thereby in Substantially to extend along a conical surface K 2 , whose cone axis coincides with the axis of rotation A of a rotor shaft 30.

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)
EP19160922.1A 2015-12-04 2016-11-30 Rampe pour plaque de recouvrement d'aube directrice et embase d'aube mobile Withdrawn EP3517736A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102015224259.5A DE102015224259A1 (de) 2015-12-04 2015-12-04 Auflauffläche für Leitschaufeldeck- und Laufschaufelgrundplatte
EP16201364.3A EP3246521B1 (fr) 2015-12-04 2016-11-30 Rampe pour plaque de recouvrement d'aube directrice et embase d'aube mobile

Related Parent Applications (2)

Application Number Title Priority Date Filing Date
EP16201364.3A Division-Into EP3246521B1 (fr) 2015-12-04 2016-11-30 Rampe pour plaque de recouvrement d'aube directrice et embase d'aube mobile
EP16201364.3A Division EP3246521B1 (fr) 2015-12-04 2016-11-30 Rampe pour plaque de recouvrement d'aube directrice et embase d'aube mobile

Publications (1)

Publication Number Publication Date
EP3517736A1 true EP3517736A1 (fr) 2019-07-31

Family

ID=57442553

Family Applications (2)

Application Number Title Priority Date Filing Date
EP19160922.1A Withdrawn EP3517736A1 (fr) 2015-12-04 2016-11-30 Rampe pour plaque de recouvrement d'aube directrice et embase d'aube mobile
EP16201364.3A Active EP3246521B1 (fr) 2015-12-04 2016-11-30 Rampe pour plaque de recouvrement d'aube directrice et embase d'aube mobile

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP16201364.3A Active EP3246521B1 (fr) 2015-12-04 2016-11-30 Rampe pour plaque de recouvrement d'aube directrice et embase d'aube mobile

Country Status (4)

Country Link
US (1) US10655483B2 (fr)
EP (2) EP3517736A1 (fr)
DE (1) DE102015224259A1 (fr)
ES (1) ES2726713T3 (fr)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070243061A1 (en) 2006-04-18 2007-10-18 Taylor Mark D Seal between rotor blade platforms and stator vane platforms, a rotor blade and a stator vane
DE102008011746A1 (de) 2008-02-28 2009-09-03 Mtu Aero Engines Gmbh Vorrichtung und Verfahren zur Umleitung eines Leckagestroms
EP2236748A2 (fr) 2009-04-01 2010-10-06 Rolls-Royce Plc Agencement de rotor pour turbine à gaz
US20140205443A1 (en) 2013-01-23 2014-07-24 Siemens Aktiengesellschaft Seal assembly including grooves in an aft facing side of a platform in a gas turbine engine
US20150040567A1 (en) * 2013-08-08 2015-02-12 General Electric Company Systems and Methods for Reducing or Limiting One or More Flows Between a Hot Gas Path and a Wheel Space of a Turbine
WO2015119699A2 (fr) * 2013-12-05 2015-08-13 United Technologies Corporation Joint rotor-stator de turbomachine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7179049B2 (en) * 2004-12-10 2007-02-20 Pratt & Whitney Canada Corp. Gas turbine gas path contour
US8282346B2 (en) * 2009-04-06 2012-10-09 General Electric Company Methods, systems and/or apparatus relating to seals for turbine engines
US8721291B2 (en) 2011-07-12 2014-05-13 Siemens Energy, Inc. Flow directing member for gas turbine engine
DE102014205986B4 (de) 2014-03-31 2021-03-18 MTU Aero Engines AG Leitschaufelkranz und Strömungsmaschine
US10145246B2 (en) * 2014-09-04 2018-12-04 United Technologies Corporation Staggered crossovers for airfoils
US11021976B2 (en) * 2014-12-22 2021-06-01 Raytheon Technologies Corporation Hardware geometry for increasing part overlap and maintaining clearance

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070243061A1 (en) 2006-04-18 2007-10-18 Taylor Mark D Seal between rotor blade platforms and stator vane platforms, a rotor blade and a stator vane
DE102008011746A1 (de) 2008-02-28 2009-09-03 Mtu Aero Engines Gmbh Vorrichtung und Verfahren zur Umleitung eines Leckagestroms
EP2236748A2 (fr) 2009-04-01 2010-10-06 Rolls-Royce Plc Agencement de rotor pour turbine à gaz
US20140205443A1 (en) 2013-01-23 2014-07-24 Siemens Aktiengesellschaft Seal assembly including grooves in an aft facing side of a platform in a gas turbine engine
US20150040567A1 (en) * 2013-08-08 2015-02-12 General Electric Company Systems and Methods for Reducing or Limiting One or More Flows Between a Hot Gas Path and a Wheel Space of a Turbine
WO2015119699A2 (fr) * 2013-12-05 2015-08-13 United Technologies Corporation Joint rotor-stator de turbomachine

Also Published As

Publication number Publication date
EP3246521B1 (fr) 2019-04-24
DE102015224259A1 (de) 2017-06-08
EP3246521A1 (fr) 2017-11-22
US10655483B2 (en) 2020-05-19
ES2726713T3 (es) 2019-10-08
US20170159464A1 (en) 2017-06-08

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