US20130052004A1 - Structural composite fan exit guide vane for a turbomachine - Google Patents

Structural composite fan exit guide vane for a turbomachine Download PDF

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Publication number
US20130052004A1
US20130052004A1 US13/217,372 US201113217372A US2013052004A1 US 20130052004 A1 US20130052004 A1 US 20130052004A1 US 201113217372 A US201113217372 A US 201113217372A US 2013052004 A1 US2013052004 A1 US 2013052004A1
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United States
Prior art keywords
exit guide
fan exit
guide vane
diameter shroud
fan
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.)
Abandoned
Application number
US13/217,372
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English (en)
Inventor
Nicholas D. Stilin
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RTX Corp
Original Assignee
Individual
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Filing date
Publication date
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=46750230&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=US20130052004(A1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Individual filed Critical Individual
Priority to US13/217,372 priority Critical patent/US20130052004A1/en
Assigned to UNITED TECHNOLOGIES CORPORATION reassignment UNITED TECHNOLOGIES CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Stilin, Nicholas D.
Priority to EP12181806.6A priority patent/EP2562361B2/fr
Publication of US20130052004A1 publication Critical patent/US20130052004A1/en
Abandoned 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced

Definitions

  • the present disclosure is directed toward turbomachine assemblies and more particularly, toward a structural fan exit guide vane for use in a gas turbine engine.
  • Turbomachines such as gas turbine engines, draw air or other gases into the machine using a fan component.
  • the rotation of the fan blades drawing the air in causes the incoming air to swirl in the direction of the fan's rotation.
  • the air In order to operate the turbomachine properly, however, the air must pass axially through the turbomachine.
  • turbomachines include fan exit guide vanes that straighten the air flow behind the fan blades.
  • Fan exit guide vanes assemblies include multiple vanes, each of which has an airfoil shaped profile that is aerodynamically designed to force the airflow passing through the fan exit guide vane into an axial flow path. Also included within turbomachine assemblies is a separate fan frame that supports the engine core, the fan, and the fan case. The fan frame also maintains the concentricness of the fan case, and the fan blades, and the engine core, thus providing for proper fan tip clearance between the engine shroud and the fan blades.
  • a structural composite fan exit guide vane segment includes a single monolithic component having an inner diameter shroud, an outer diameter shroud, and a plurality of fan exit guide vanes connecting the inner diameter shroud and the outer diameter shroud.
  • a gas turbine engine has a fan frame composed of a plurality of fan exit guide vane segments.
  • Each of the fan exit guide vane segments has a single monolithic component with an inner diameter shroud, an outer diameter shroud, and a plurality of fan exit guide vanes connecting the inner diameter shroud and the outer diameter shroud.
  • a method for creating a fan exit guide vane segment that includes the steps of creating a semi-continuous fiber preform by looping fibers in a desired profile, and infusing the fiber preform with a resin during a molding process thereby creating a single monolithic fan exit guide vane segment.
  • FIG. 1A illustrates a partial side view of an air intake for the gas turbine engine of FIG. 1A .
  • FIG. 1B illustrates a front view of the air intake for a gas turbine engine.
  • FIG. 2 is a contextual drawing of a structural fan exit guide vane assembly.
  • FIG. 3A illustrates a first isometric view of a structural fan exit guide vane segment.
  • FIG. 3B illustrates a second isometric view of the structural fan exit guide vane segment of FIG. 3A .
  • FIG. 4 illustrates a partial isometric view of a fan exit guide vane assembly outer diameter shroud.
  • FIG. 1A illustrates a partial side view of an air intake for a gas turbine engine 10 .
  • FIG. 1B illustrates a front view of the gas turbine engine 10 with a cutout view 60 illustrating the fan exit guide vanes 50 behind the fan blades 30 .
  • the gas turbine engine 10 has an air intake fan 40 that rotates fan blades 30 radially about an axis A.
  • the rotation of the fan blades 30 draws air into the gas turbine engine 10 along a flow path 32 .
  • the fan 40 is encased in a fan case 20 , such as a turbine engine shroud. As the air passes through the fan blades 30 , the air begins swirling radially relative to axis A due to the rotation of the fan blades 30 .
  • each of the structural fan exit guide vane segments 50 includes multiple foil shaped guide vanes 52 .
  • Each guide vane 52 is connected to an inner diameter shroud 58 and an outer diameter shroud 56 .
  • Each of the outer diameter shrouds 56 are connected to the fan case 20 .
  • Each of the inner diameter shrouds 58 are connected to an engine core 42 .
  • the structural fan exit guide vanes 50 provide structural support to the engine core 42 and the fan case 20 , thereby ensuring that proper clearance is maintained between the tips of the fan blades 30 and the fan case 20 . Additionally, the structural support of the structural fan exit guide vane segments 50 maintains the concentricness of the engine core 42 , the fan blades 30 , and the fan case 20 .
  • FIG. 1B illustrates a front view of the gas turbine engine 10 , with a cutout segment 60 illustrating the structural fan exit guide vane segments 50 positioned axially behind the fan blades 30 .
  • Each of the structural fan exit guide vanes segments 50 includes a first exit guide vane 52 and a second exit guide vane 54 .
  • the outer diameter shroud 56 of each structural fan exit guide vane segment 50 abuts the outer diameter shrouds of each adjacent structural fan exit guide vane segment 50 resulting in a circular structural fan exit guide vane segment assembly behind the fan blades 30 .
  • the structural fan exit guide vane assembly structurally supports the engine core 42 , the fan blades 30 , and the fan case 20 and axially straightens the flow path 32 .
  • each of the inner diameter shrouds 58 abuts the inner diameter shrouds 58 of each adjacent structural fan exit guide vane segment 50 .
  • each structural fan exit guide vane segment 50 abutting two adjacent fan exit guide vane segments 50 creates a circular structural fan exit guide vane assembly that provides the structural support described above, and the airflow straightening described above, while at the same time not requiring a separate structural frame assembly to support the fan 40 , the fan case 20 , and the engine core 42 .
  • FIG. 2 illustrates a more detailed contextual side drawing of a single structural fan exit guide vane 100 .
  • the outer diameter shroud 156 and the inner diameter shroud 158 of the structural fan exit guide vane 100 are connected by guide vanes 152 , 154 .
  • Each of the shrouds 156 , 158 is fastened to the fan case 20 and the engine case 42 via a plurality of fasteners 170 , such as bolts.
  • the fasteners 170 protrude through the shrouds 156 , 158 and into the fan case 20 and the engine core 42 .
  • Each of the inner diameter shroud 158 and the outer diameter shroud 156 also includes a fiber bulge 160 , resulting from the molding process, that physically contacts the fan case 20 (in the case of the outer diameter shroud 156 ) and the engine core 42 (in the case of the inner diameter shroud 158 ).
  • FIG. 3A illustrates an isometric view of a structural fan exit guide vane segment 200 that can be used as the structural fan exit guide vane segment 50 of FIGS. 1A and 1B .
  • the structural fan exit guide vane segment 200 includes an arced outer diameter shroud 256 and an arced inner diameter shroud 258 with each of the arcs being coaxial.
  • the shrouds 256 , 258 are connected via a two fan exit guide vanes 252 , 254 .
  • Each of the shrouds 256 , 258 also includes multiple counter sunk holes 272 for fastening the shrouds 256 , 258 to the fan case 20 and the engine core 42 .
  • the arcing of the shrouds is concentric.
  • the countersinking of the fastener bolts 272 allows the fastener heads to be flush with the exposed surface of the shrouds 256 , 258 , thereby minimizing the effect of the fasteners on the airflow along the flow path 32 through the gas turbine engine 10 .
  • integral flow path spacer 280 Also attached to both the inner and the outer diameter shrouds 256 , 258 is an integral flow path spacer 280 .
  • the integral flow path spacer 280 on the outer diameter shroud 256 is visible in FIG. 3A , while the integral flow path spacer 280 on the inner diameter shroud 258 is hidden due to the view angle.
  • the integral flow path spacer 280 provides an airflow seal between each structural guide vane 200 and the adjacent structural guide vanes 200 .
  • the integral flow path spacer 280 is only placed on a single shroud edge of each of the inner and outer diameter shrouds 256 , 258 .
  • each shroud edge with a spacer abuts an edge of an adjacent shroud 256 , 258 without a spacer resulting in each abutment being sealed by a single integral flow path spacer 280 .
  • Each of the guide vanes 252 , 254 has an airfoil shaped profile that allows the vanes 252 , 254 to force air passing through the structural fan exit guide vane assembly into an axial flow path.
  • the particular foil profile of the vanes 252 , 254 can be designed according to known techniques to fit the requirements of a particular gas turbine engine implementation.
  • FIG. 3B illustrates an alternate viewpoint of the structural guide vane assembly of FIG. 3A , with like numerals indicating like elements.
  • the view shown in FIG. 3B shows the integral flow path spacer 280 on each of the inner and outer diameter shrouds 256 , 258 . Also illustrated is the fiber bulge 260 on the inner diameter shroud 256 .
  • the isometric view of FIG. 3B further illustrates the foil profile of the guide vanes 252 , 254 .
  • FIG. 4 provides a zoomed isometric view of the outer diameter shroud 256 and the integral flow path spacer 280 of FIGS. 3A and 3B .
  • the integral flow path spacer 280 is a solid piece of flexible material, such as rubber, and includes a seal portion 282 and a connection portion 284 .
  • the seal portion 282 overhangs the edge of the outer diameter shroud 258 .
  • the seal portion 282 deforms to provide an airtight seal between the two outer diameter shrouds 256 .
  • the seal portion 282 also provides vibrational damping between the structural guide vane segments 200 .
  • connection portion 284 of the integral flow path spacer 280 is affixed to the shroud segment, attaching the integral flow path spacer 282 to the shroud.
  • a similar integral flow path spacer 282 design is used with the inner diameter shroud 258 .
  • the structural fan exit guide vane segments described above and illustrated in the figures use a single monolithic carbon/epoxy structure to construct the guide vane segment as a single piece.
  • the two vanes are shaped into a preform having the desired airfoil profile using a continuous or semi-continuous fiber.
  • the fiber preform is then infused with a carbon/epoxy resin during a molding process.
  • This type of resin molding generates an end component that is a single piece and is constructed of a fiber reinforced polymer matrix composite.
  • the molding process also creates the inner and outer diameter shrouds using standard carbon/epoxy laminate molding processes.
  • the counter sunk holes can either be created as part of the molding process or drilled after the molding process is finished.
  • three or more guide vanes can be constructed in the same manner, and could be used in each monolithic vane segment and still fall within the above disclosure.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US13/217,372 2011-08-25 2011-08-25 Structural composite fan exit guide vane for a turbomachine Abandoned US20130052004A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US13/217,372 US20130052004A1 (en) 2011-08-25 2011-08-25 Structural composite fan exit guide vane for a turbomachine
EP12181806.6A EP2562361B2 (fr) 2011-08-25 2012-08-24 Aube directrice de sortie de fan composite structurelle pour turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/217,372 US20130052004A1 (en) 2011-08-25 2011-08-25 Structural composite fan exit guide vane for a turbomachine

Publications (1)

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US20130052004A1 true US20130052004A1 (en) 2013-02-28

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US13/217,372 Abandoned US20130052004A1 (en) 2011-08-25 2011-08-25 Structural composite fan exit guide vane for a turbomachine

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US (1) US20130052004A1 (fr)
EP (1) EP2562361B2 (fr)

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130149127A1 (en) * 2011-12-09 2013-06-13 General Electric Company Structural Platforms for Fan Double Outlet Guide Vane
US20140133975A1 (en) * 2011-12-09 2014-05-15 General Electric Company Double Fan Outlet Guide Vane with Structural Platforms
US20140140832A1 (en) * 2011-12-09 2014-05-22 General Electric Company Quick Engine Change Assembly for Outlet Guide Vanes
US20140294574A1 (en) * 2012-11-21 2014-10-02 Techspace Aero S.A. Stator Blades of an Axial Turbocompressor and Manufacturing Process
WO2015006009A1 (fr) * 2013-07-08 2015-01-15 United Technologies Corporation Bloc réacteur incliné
US20150345315A1 (en) * 2014-06-02 2015-12-03 Snecma Turbine engine guide vane attachment orifice closer
US20170167502A1 (en) * 2015-12-14 2017-06-15 General Electric Company Rotor assembly for use in a turbofan engine and method of assembling
US20170370326A1 (en) * 2016-06-28 2017-12-28 United Technologies Corporation Particle extraction system for a gas turbine engine
US20180030995A1 (en) * 2016-08-01 2018-02-01 United Technologies Corporation Fan blade with composite cover
US20180080332A1 (en) * 2016-09-19 2018-03-22 Safran Aircraft Engines Intermediate casing guide vane wheel
US10385868B2 (en) * 2016-07-05 2019-08-20 General Electric Company Strut assembly for an aircraft engine
US10443625B2 (en) * 2016-09-21 2019-10-15 General Electric Company Airfoil singlets
US10483659B1 (en) * 2018-11-19 2019-11-19 United Technologies Corporation Grounding clip for bonded vanes
US10589475B2 (en) 2014-09-23 2020-03-17 General Electric Company Braided blades and vanes having dovetail roots
US10724390B2 (en) 2018-03-16 2020-07-28 General Electric Company Collar support assembly for airfoils
US11208198B2 (en) * 2019-01-15 2021-12-28 Safran Aircraft Engines Composite propeller vane or blade for aircraft integrating a conformation part
US20250369365A1 (en) * 2022-04-15 2025-12-04 Safran Aircraft Engines Turbine engine motor having an unducted fan
FR3166179A1 (fr) * 2024-09-12 2026-03-13 Safran Aircraft Engines Section de soufflante avec joint deformable

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3003668B1 (fr) 2013-03-25 2020-10-30 Snecma Procede de conception d'une preforme commune pour la realisation de preformes d'aubes directrices de sortie de turbomachine en materiau composite a profils geometriques differents
GB201513232D0 (en) 2015-07-28 2015-09-09 Rolls Royce Plc A nozzle guide vane passage

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US8105039B1 (en) * 2011-04-01 2012-01-31 United Technologies Corp. Airfoil tip shroud damper

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US5226789A (en) * 1991-05-13 1993-07-13 General Electric Company Composite fan stator assembly
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FR2852884B1 (fr) * 2003-03-26 2005-05-06 Hurel Hispano Procede de fabrication de pieces en composite a matrice polyimide
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US2942843A (en) * 1956-06-15 1960-06-28 Westinghouse Electric Corp Blade vibration damping structure
US3632460A (en) * 1967-06-24 1972-01-04 Rolls Royce Epicyclic weaving of fiber discs
US4786347A (en) * 1984-07-07 1988-11-22 Rolls-Royce Plc Method of manufacturing an annular bladed member having an integral shroud
US5482433A (en) * 1993-11-19 1996-01-09 United Technologies Corporation Integral inner and outer shrouds and vanes
US5722813A (en) * 1996-10-28 1998-03-03 Alliedsignal Inc. Segmented composite compressor deswirl
US20030185673A1 (en) * 2002-01-21 2003-10-02 Honda Giken Kogyo Kabushiki Kaisha Flow-rectifying member and its unit and method for producing flow-rectifying member
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US8105039B1 (en) * 2011-04-01 2012-01-31 United Technologies Corp. Airfoil tip shroud damper

Cited By (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130149130A1 (en) * 2011-12-09 2013-06-13 General Electric Company Fan Hub Frame for Double Outlet Guide Vane
US20140133975A1 (en) * 2011-12-09 2014-05-15 General Electric Company Double Fan Outlet Guide Vane with Structural Platforms
US20140140832A1 (en) * 2011-12-09 2014-05-22 General Electric Company Quick Engine Change Assembly for Outlet Guide Vanes
US9303531B2 (en) * 2011-12-09 2016-04-05 General Electric Company Quick engine change assembly for outlet guide vanes
US9303520B2 (en) * 2011-12-09 2016-04-05 General Electric Company Double fan outlet guide vane with structural platforms
US20130149127A1 (en) * 2011-12-09 2013-06-13 General Electric Company Structural Platforms for Fan Double Outlet Guide Vane
US20140294574A1 (en) * 2012-11-21 2014-10-02 Techspace Aero S.A. Stator Blades of an Axial Turbocompressor and Manufacturing Process
WO2015006009A1 (fr) * 2013-07-08 2015-01-15 United Technologies Corporation Bloc réacteur incliné
US20160146104A1 (en) * 2013-07-08 2016-05-26 United Technologies Corporation Angled Core Engine
US9797266B2 (en) * 2014-06-02 2017-10-24 Snecma Turbine engine guide vane attachment orifice closer
US20150345315A1 (en) * 2014-06-02 2015-12-03 Snecma Turbine engine guide vane attachment orifice closer
US10589475B2 (en) 2014-09-23 2020-03-17 General Electric Company Braided blades and vanes having dovetail roots
US20170167502A1 (en) * 2015-12-14 2017-06-15 General Electric Company Rotor assembly for use in a turbofan engine and method of assembling
US10047763B2 (en) * 2015-12-14 2018-08-14 General Electric Company Rotor assembly for use in a turbofan engine and method of assembling
US20170370326A1 (en) * 2016-06-28 2017-12-28 United Technologies Corporation Particle extraction system for a gas turbine engine
US10774788B2 (en) * 2016-06-28 2020-09-15 Raytheon Technologies Corporation Particle extraction system for a gas turbine engine
US10385868B2 (en) * 2016-07-05 2019-08-20 General Electric Company Strut assembly for an aircraft engine
US10570917B2 (en) * 2016-08-01 2020-02-25 United Technologies Corporation Fan blade with composite cover
US20180030995A1 (en) * 2016-08-01 2018-02-01 United Technologies Corporation Fan blade with composite cover
US11396884B2 (en) 2016-08-01 2022-07-26 Raytheon Technologies Corporation Fan blade with composite cover
US10458261B2 (en) * 2016-09-19 2019-10-29 Safran Aircraft Engines Intermediate casing guide vane wheel
US20180080332A1 (en) * 2016-09-19 2018-03-22 Safran Aircraft Engines Intermediate casing guide vane wheel
US10443625B2 (en) * 2016-09-21 2019-10-15 General Electric Company Airfoil singlets
US10724390B2 (en) 2018-03-16 2020-07-28 General Electric Company Collar support assembly for airfoils
US10483659B1 (en) * 2018-11-19 2019-11-19 United Technologies Corporation Grounding clip for bonded vanes
US11208198B2 (en) * 2019-01-15 2021-12-28 Safran Aircraft Engines Composite propeller vane or blade for aircraft integrating a conformation part
US20250369365A1 (en) * 2022-04-15 2025-12-04 Safran Aircraft Engines Turbine engine motor having an unducted fan
FR3166179A1 (fr) * 2024-09-12 2026-03-13 Safran Aircraft Engines Section de soufflante avec joint deformable
WO2026057951A1 (fr) * 2024-09-12 2026-03-19 Safran Aircraft Engines Section de soufflante avec joint deformable

Also Published As

Publication number Publication date
EP2562361B1 (fr) 2015-12-09
EP2562361B2 (fr) 2019-04-10
EP2562361A1 (fr) 2013-02-27

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AS Assignment

Owner name: UNITED TECHNOLOGIES CORPORATION, CONNECTICUT

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:STILIN, NICHOLAS D.;REEL/FRAME:026804/0775

Effective date: 20110823

STCB Information on status: application discontinuation

Free format text: ABANDONED -- AFTER EXAMINER'S ANSWER OR BOARD OF APPEALS DECISION