WO2009157817A1 - Ensemble aube, procédé de fabrication associé, et turbomachine équipée de cet ensemble aube - Google Patents

Ensemble aube, procédé de fabrication associé, et turbomachine équipée de cet ensemble aube Download PDF

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Publication number
WO2009157817A1
WO2009157817A1 PCT/SE2008/000413 SE2008000413W WO2009157817A1 WO 2009157817 A1 WO2009157817 A1 WO 2009157817A1 SE 2008000413 W SE2008000413 W SE 2008000413W WO 2009157817 A1 WO2009157817 A1 WO 2009157817A1
Authority
WO
WIPO (PCT)
Prior art keywords
vane
case
head portion
elliptically shaped
elliptical
Prior art date
Application number
PCT/SE2008/000413
Other languages
English (en)
Inventor
Henrik Gustavsson
Original Assignee
Volvo Aero Corporation
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 Volvo Aero Corporation filed Critical Volvo Aero Corporation
Priority to PCT/SE2008/000413 priority Critical patent/WO2009157817A1/fr
Publication of WO2009157817A1 publication Critical patent/WO2009157817A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
    • 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
    • F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2101/00—Articles made by soldering, welding or cutting
    • B23K2101/001—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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • 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
    • F05D2250/70—Shape

Definitions

  • the invention relates to a vane assembly for a turbo-machine and a turbo-machine with a vane assembly according to the preambles of the independent claims.
  • Turbo-machines are generally known in the art. Turbo-machines can be employed e.g. as compressors, turbines, gas turbine engines and the like.
  • a turbo machine can be a single-stage machine or a multi-stage machine.
  • a single stage of the turbo-machine comprises a pair of a guide vane arrangement with a multitude of vanes and a rotor blade arrangement with a multitude of blades.
  • the rotor blades are arranged on a rotatable shaft.
  • the guide vanes are fixedly connected to the housing of the turbo machine and guide the fluid flow to the rotor blades so that the fluid flow impinges on the rotor blades under an optimum angle.
  • each stage the vanes in the stages of a turbo-machine transform the enthalpy per stage totally or nearly totally into kinetic energy of the fluid.
  • the rotor blades transform the kinetic energy of the impinging fluid flow into a circumferential force due to the deviation which the rotor blades exert on the impinging fluid flow.
  • US 4,940,386 A1 discloses a multiple flow turbojet engine.
  • the guide vanes of the fan outlet are arranged between an inner case and an outer case.
  • An outer ring is shrunk onto the case at the fan outlet.
  • the outer ring provides slots for receiving the head parts of the guide vanes.
  • the head parts are covered with elastomeric end caps with circumferential lips which engage with the slots in the outer ring and which attach the vanes to the outer ring.
  • US 3,992,127 A1 discloses a guide vane assembly in a gas turbine.
  • the vanes are arranged between an inner case and an outer case.
  • the engaging surfaces of the vanes are provided with adjacent end caps forming engaging pivot and seat surfaces.
  • a vane assembly for a turbo-machine comprising a multitude of vanes arranged between a first case and a second case, wherein each vane comprises a vane body between a first and a second end portion.
  • At least one of the first and second end portions of the at least one vane comprises an elliptical head portion which is fixedly connected to the respective case dedicated to the at least one of the first and second end portions.
  • the elliptically shaped head portion allows for favourable conditions during connecting the vane end portion to its dedicated case.
  • the elliptical shape provides relatively large radii which result in a smaller risk during e.g. welding the vane end portion to the dedicated case.
  • a preferred vane can comprises a vane body arranged between the first end portion and the second end portion being provided for connection to inner and/or outer cases. At least one of the end portions can comprise an elliptically shaped head portion, wherein the elliptically shaped head portion comprises a base elliptical head area of a generally elliptical cross section arranged crosswise to the vane body which elliptical area is provided for "" O ""
  • the elliptical head area of the elliptically shaped head portion can comprise a collar portion arranged crosswise to the main surface of the head area provided for connection to the vane body.
  • the at least one vane can be connected with its elliptically shaped head portion to the outer case of the two cases.
  • the outer case is preferably an annular ring. The outer case can be easily accessed during welding.
  • At least one vane can be connected with its elliptically shaped head portion to the inner case of the two cases.
  • the inner case can preferably be embodied as an annular ring. It is also possible to provide both second end portions of the vane with an elliptically shaped head portion and connect the elliptically shaped head portions to their dedicated inner or outer cases.
  • the at least one vane can welded with its elliptically shaped head portion to the at least one case.
  • the elliptic shape yields large radii which allow for a better distribution of stresses occurring during welding. This results in a favourable prolongation of the lifetime of the vane assembly.
  • the at least one elliptically shaped head portion can be welded to the vane body.
  • the vane with its end portions can also be formed in one piece.
  • the ellipse principal axis of the elliptical head portion can be oriented parallel to an axial direction of the cases. This yields in a favourable distribution of stress during welding.
  • the ellipse head area of the at least one elliptical head portion can be oriented parallel to a main surface of the at least one case to which it is connected.
  • the vane body can abut with its front face to the case surface.
  • a turbo-machine comprising at least one stage with a vane assembly with anyone of the features described above.
  • the preferred vane assembly improves the conditions for robot welding thus providing a reproducibly high quality fabrication method for a turbo- machine. This is particularly useful in applications where large numbers of turbo- machines have to be produced, e.g. for series production of vehicles, particularly work machines, in which such turbo-machines are employed.
  • the at least one stage can comprise a vane assembly with at least one vane comprising one or two elliptical head portions welded to an outer case.
  • robot welding can be used.
  • the at least one stage can comprise a vane assembly with at least one vane comprising one or two elliptical head portions welded to an inner case.
  • a method for fabricating a vane assembly comprising the steps of forming first or a second end portion of a vane by welding an elliptically shaped head portion to a vane body of the vane; providing an annular case with at least one elliptical slot; positioning the vane with its elliptically shaped head portion into the slot of the dedicated case for connecting the vane to the dedicated case; welding the elliptically shaped head portion with its elliptical head area to the slot dedicated case.
  • the welding step can be performed by an automated welding process, favourably by robot welding.
  • Fig. 1a, 1b a front view (Fig. 1a) and a perspective interior view (Fig. 1b) of a preferred embodiment of a vane assembly according to the invention; - -
  • Fig. 2a, 2b an egdewise perspective view (Fig. 2a) and a prespective view on the broad side (Fig. 2b) of a preferred vane of a vane assembly according to the invention.
  • FIG. 3a-3c several details of a preferred vane of a vane assembly according to the invention.
  • Fig. 4a, 4b a top view (Fig. 4a) and a bottom view (Fig. 4b) of a preferred elliptical head portion according to the invention.
  • Fig. 1a and 1b illustrate different views of a preferred vane assembly 100 for a turbo-machine (not shown) comprising a multitude of vanes 20 arranged in a ring between a first case 10 and a second case 40.
  • the front view in Fig. 1a shows a ring arrangement of a multitude of vanes 20, e.g. thirteen vanes 20 in this example embodiment, which vanes 20 extend in a radial direction between an inner first case 10, embodied as an annular sheet and an outer second case 40 embodied as an annular sheet.
  • a central opening 12 provides space for a shaft of the turbo- machine (not shown).
  • a fluid e.g.
  • FIG. 1 b The perspective view of Fig. 1 b on the vane assembly 100 shows case segments 44 of the outer second case 40 and illustrates a preferred embodiment of the vane assembly 100 according to the invention.
  • a multitude of the vanes 20 are attached with a foot portion 28 to the inner case 10 and with an elliptically shaped head portion 30 of their second end portions 26 to the second case 40.
  • shaped head portion 30 is oriented parallel to a main surface 46 of the case 40 and is received in a slot 42 of appropriate shape. This can be seen by the elliptical features in a general axial extension with their large principal axis on the outer main surface 46 of the outer second case 40.
  • vanes 20 can also be connected to the first inner case 10 in a similar way with their foot portions 28 which can be elliptically shaped (not shown).
  • Fig. 2a and 2b show a vane 20 with an elliptically shaped head portion 30 and which is attached with its foot portion to an inner case 10 in different views.
  • Fig. 2a shows a view on the edge of the vane 20.
  • Fig. 2b shows a view on the broad side of the vane 20.
  • the vane 20 has a vane body 22 which extends between a first end portion 24 abutting to the inner first case 10 and a second end portion 26 provided for connection to the second case 40 (Fig. 1b).
  • the second end portion 26 comprises an elliptically shaped head portion 30 which is formed as an elliptically shaped hat.
  • the elliptically shaped head portion 30 comprises a collar portion 32 with which it is connected to the vane body 22 and a head area 34 of generally elliptical cross section with a rim 36.
  • the elliptically shaped head portion 30 is an integral part of the vane 20 an preferably welded to the vane body 22.
  • the vane 20 is connected with the rim 36 to the elliptically formed slot 42 in the second case 40 (Fig. 1 b).
  • the vane 20 is welded to the first and second case 10, 40 with its foot portion 28 and its elliptically shaped head portion 30.
  • Fig. 3a shows a case segment 44 of the outer second case 40 into which an elliptical slot 42 has been made, e.g. by milling.
  • the elliptically shaped head portion 30 of a vane 20 is received in this slot 42 and welded with its rim 36 to the circumference area of the slot 42.
  • Fig. 3b shows the end portion 26 of the vane 20.
  • the second end portion 26 comprises an elliptically shaped head portion 30.
  • the elliptically shaped head portion 30 is composed of an elliptically head area 34 and a collar portion 32 which is the interface between the vane body 22 and the end portion 26.
  • the elliptic head area 34 has an elliptic rim 36 around the end portion 26 of the vane 20.
  • the elliptically shaped head portion 30 is welded to the vane body 22 before the vane 20 is welded to the outer second case 40.
  • the first end portion 24 of the vane has been connected, preferably welded, to the first inner case 10, which is indicated in Fig. 3c.
  • the welding is done in an automated robot welding process.
  • a foot portion 28 can be provided at the first case 10 and the vane body 22 can be attached, preferably welded, to the foot portion 28 before the elliptically shaped head portion 30 is welded to the vane body. It is possible to form the foot portion 28 also as an elliptically shaped head portion equivalent to the elliptically shaped head portion 30.
  • Fig. 4a and 4b show a detailed illustration of the elliptical head portion 30 as a top view in Fig. 4a and a bottom view in Fig. 4b.
  • the elliptical head portion 30 has an elliptical head area 34 formed as a hat which covers the vane body 22, which can be hollow.
  • the elliptical head area 34 is not necessarily plane but can be uneven and preferably provides the same curvature as the respective case 10 or 40 to which is has to fit in the respective slot 42 (Fig. 3b) in order to provide a smooth surface (Fig. 1b).
  • the ellipse principal axis 48 of the elliptical head portion 30 can be oriented parallel to an axial direction of the cases 10, 40 (Fig. 1b).
  • the bottom view in Fig. 3b shows a collar portion 32 of the head portion 30 which is oriented crosswise to the elliptic head area 34.
  • the collar portion 32 is arranged inside the elliptic head area 34 so that the rim 36 of the elliptic head area 34 — ⁇ —
  • the collar portion 32 forms an interface to the vane body 22 (Fig. 2a, 2b) to which it can be attached, preferably by welding.
  • the invention provides an improved geometry of a vane 20 and a vane assembly 100 which is particularly convenient for robot welding, thus providing a reproducible and cost effective production process for vane assemblies 100 and turbo-machines.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L’invention concerne un ensemble aube (100) pour une turbomachine, comprenant une multitude d’aubes (20) agencées entre une première enveloppe (10) et une seconde enveloppe (40), chaque aube (20) comprenant un corps d’aube (22) entre une première et une seconde partie d’extrémité (24, 26). La première partie et/ou la seconde partie d’extrémité (24, 26) de l’aube ou des aubes (20) comprennent une partie de tête elliptique (30) qui est reliée fixement à l’enveloppe respective (10, 40), dédiée à la première partie et/ou à la seconde partie d’extrémité (24, 26). L’invention concerne également une turbomachine équipée d’un ensemble aube et un procédé de fabrication d’un ensemble aube.
PCT/SE2008/000413 2008-06-26 2008-06-26 Ensemble aube, procédé de fabrication associé, et turbomachine équipée de cet ensemble aube WO2009157817A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/SE2008/000413 WO2009157817A1 (fr) 2008-06-26 2008-06-26 Ensemble aube, procédé de fabrication associé, et turbomachine équipée de cet ensemble aube

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/SE2008/000413 WO2009157817A1 (fr) 2008-06-26 2008-06-26 Ensemble aube, procédé de fabrication associé, et turbomachine équipée de cet ensemble aube

Publications (1)

Publication Number Publication Date
WO2009157817A1 true WO2009157817A1 (fr) 2009-12-30

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Cited By (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2395214A1 (fr) * 2010-06-10 2011-12-14 Alstom Technology Ltd Collecteur de gaz d'échappement pour turbomachine et procédé de production dudit collecteur
WO2011157962A1 (fr) * 2010-06-18 2011-12-22 Aircelle Structure de redressement de flux d'air pour nacelle de moteur d'aéronef
ITCO20120054A1 (it) * 2012-10-31 2014-05-01 Nuovo Pignone Srl Metodi per produrre pale di turbomacchine mediante wire electric discharge machining, pale e turbomacchine
EP3159485A1 (fr) * 2015-10-20 2017-04-26 General Electric Company Connexion fabriquée de manière additive pour un diaphragme de turbine
US9828867B2 (en) 2012-12-29 2017-11-28 United Technologies Corporation Bumper for seals in a turbine exhaust case
US9845695B2 (en) 2012-12-29 2017-12-19 United Technologies Corporation Gas turbine seal assembly and seal support
US9850774B2 (en) 2012-12-29 2017-12-26 United Technologies Corporation Flow diverter element and assembly
US9884393B2 (en) 2015-10-20 2018-02-06 General Electric Company Repair methods utilizing additively manufacturing for rotor blades and components
US9890663B2 (en) 2012-12-31 2018-02-13 United Technologies Corporation Turbine exhaust case multi-piece frame
US9903216B2 (en) 2012-12-29 2018-02-27 United Technologies Corporation Gas turbine seal assembly and seal support
US9903224B2 (en) 2012-12-29 2018-02-27 United Technologies Corporation Scupper channelling in gas turbine modules
US9914172B2 (en) 2015-10-20 2018-03-13 General Electric Company Interlocking material transition zone with integrated film cooling
US9982561B2 (en) 2012-12-29 2018-05-29 United Technologies Corporation Heat shield for cooling a strut
US9982564B2 (en) 2012-12-29 2018-05-29 United Technologies Corporation Turbine frame assembly and method of designing turbine frame assembly
US10006306B2 (en) 2012-12-29 2018-06-26 United Technologies Corporation Turbine exhaust case architecture
US10053998B2 (en) 2012-12-29 2018-08-21 United Technologies Corporation Multi-purpose gas turbine seal support and assembly
US10054009B2 (en) 2012-12-31 2018-08-21 United Technologies Corporation Turbine exhaust case multi-piece frame
US10060279B2 (en) 2012-12-29 2018-08-28 United Technologies Corporation Seal support disk and assembly
US10087843B2 (en) 2012-12-29 2018-10-02 United Technologies Corporation Mount with deflectable tabs
EP3399146A1 (fr) * 2017-05-04 2018-11-07 Rolls-Royce plc Ensemble d'aube pour moteur de turbine à gaz
US10138742B2 (en) 2012-12-29 2018-11-27 United Technologies Corporation Multi-ply finger seal
US10180072B2 (en) 2015-10-20 2019-01-15 General Electric Company Additively manufactured bladed disk
US10240532B2 (en) 2012-12-29 2019-03-26 United Technologies Corporation Frame junction cooling holes
US10240481B2 (en) 2012-12-29 2019-03-26 United Technologies Corporation Angled cut to direct radiative heat load
US10294819B2 (en) 2012-12-29 2019-05-21 United Technologies Corporation Multi-piece heat shield
US10329956B2 (en) 2012-12-29 2019-06-25 United Technologies Corporation Multi-function boss for a turbine exhaust case
US10329957B2 (en) 2012-12-31 2019-06-25 United Technologies Corporation Turbine exhaust case multi-piece framed
US10330011B2 (en) 2013-03-11 2019-06-25 United Technologies Corporation Bench aft sub-assembly for turbine exhaust case fairing
US10370975B2 (en) 2015-10-20 2019-08-06 General Electric Company Additively manufactured rotor blades and components
US10472987B2 (en) 2012-12-29 2019-11-12 United Technologies Corporation Heat shield for a casing
EP3771804A1 (fr) * 2019-07-29 2021-02-03 Pratt & Whitney Canada Corp. Carter d'échappement de moteur à turbine à gaz

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EP1801357A1 (fr) * 2005-12-22 2007-06-27 Techspace aero Aubage statorique de turbomachine, turbomachine comportant l'aubage et aube de turbomachine

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Cited By (41)

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EP2395214A1 (fr) * 2010-06-10 2011-12-14 Alstom Technology Ltd Collecteur de gaz d'échappement pour turbomachine et procédé de production dudit collecteur
CH703309A1 (de) * 2010-06-10 2011-12-15 Alstom Technology Ltd Abgasgehäuse für eine gasturbine sowie verfahren zum herstellen eines solchen abgasgehäuses.
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WO2011157962A1 (fr) * 2010-06-18 2011-12-22 Aircelle Structure de redressement de flux d'air pour nacelle de moteur d'aéronef
FR2961555A1 (fr) * 2010-06-18 2011-12-23 Aircelle Sa Structure de redressement de flux d'air pour nacelle de moteur d'aeronef
CN102971217A (zh) * 2010-06-18 2013-03-13 埃尔塞乐公司 用于飞行器发动机机舱的气流矫直结构
ITCO20120054A1 (it) * 2012-10-31 2014-05-01 Nuovo Pignone Srl Metodi per produrre pale di turbomacchine mediante wire electric discharge machining, pale e turbomacchine
WO2014067868A1 (fr) * 2012-10-31 2014-05-08 Nuovo Pignone Srl Procédés de fabrication d'aubes de turbomachines par usinage par étincelage, aubes et turbomachines
CN104822901A (zh) * 2012-10-31 2015-08-05 诺沃皮尼奥内股份有限公司 通过金属线放电加工制造涡轮机叶片的方法、叶片和涡轮机
JP2015533398A (ja) * 2012-10-31 2015-11-24 ヌオーヴォ ピニォーネ ソチエタ レスポンサビリタ リミタータＮｕｏｖｏ Ｐｉｇｎｏｎｅ Ｓ．Ｒ．Ｌ． ワイヤ放電加工によるターボ機械の翼の製造方法、翼およびターボ機械
US10240532B2 (en) 2012-12-29 2019-03-26 United Technologies Corporation Frame junction cooling holes
US10294819B2 (en) 2012-12-29 2019-05-21 United Technologies Corporation Multi-piece heat shield
US9845695B2 (en) 2012-12-29 2017-12-19 United Technologies Corporation Gas turbine seal assembly and seal support
US9850774B2 (en) 2012-12-29 2017-12-26 United Technologies Corporation Flow diverter element and assembly
US10941674B2 (en) 2012-12-29 2021-03-09 Raytheon Technologies Corporation Multi-piece heat shield
US10472987B2 (en) 2012-12-29 2019-11-12 United Technologies Corporation Heat shield for a casing
US9903216B2 (en) 2012-12-29 2018-02-27 United Technologies Corporation Gas turbine seal assembly and seal support
US9903224B2 (en) 2012-12-29 2018-02-27 United Technologies Corporation Scupper channelling in gas turbine modules
US10329956B2 (en) 2012-12-29 2019-06-25 United Technologies Corporation Multi-function boss for a turbine exhaust case
US9982561B2 (en) 2012-12-29 2018-05-29 United Technologies Corporation Heat shield for cooling a strut
US9982564B2 (en) 2012-12-29 2018-05-29 United Technologies Corporation Turbine frame assembly and method of designing turbine frame assembly
US10006306B2 (en) 2012-12-29 2018-06-26 United Technologies Corporation Turbine exhaust case architecture
US10053998B2 (en) 2012-12-29 2018-08-21 United Technologies Corporation Multi-purpose gas turbine seal support and assembly
US9828867B2 (en) 2012-12-29 2017-11-28 United Technologies Corporation Bumper for seals in a turbine exhaust case
US10060279B2 (en) 2012-12-29 2018-08-28 United Technologies Corporation Seal support disk and assembly
US10087843B2 (en) 2012-12-29 2018-10-02 United Technologies Corporation Mount with deflectable tabs
US10240481B2 (en) 2012-12-29 2019-03-26 United Technologies Corporation Angled cut to direct radiative heat load
US10138742B2 (en) 2012-12-29 2018-11-27 United Technologies Corporation Multi-ply finger seal
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