EP2659112B1 - Gasturbinenmotor und schaufelsystem mit veränderbarer wölbung - Google Patents

Gasturbinenmotor und schaufelsystem mit veränderbarer wölbung Download PDF

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Publication number
EP2659112B1
EP2659112B1 EP11853198.7A EP11853198A EP2659112B1 EP 2659112 B1 EP2659112 B1 EP 2659112B1 EP 11853198 A EP11853198 A EP 11853198A EP 2659112 B1 EP2659112 B1 EP 2659112B1
Authority
EP
European Patent Office
Prior art keywords
airfoil portion
airfoil
crown
variable
groove
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.)
Active
Application number
EP11853198.7A
Other languages
English (en)
French (fr)
Other versions
EP2659112A4 (de
EP2659112A1 (de
Inventor
Robert A. Ress, Jr.
James Morton
Dan MOLNAR
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.)
Rolls Royce North American Technologies Inc
Original Assignee
Rolls Royce North American Technologies Inc
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 Rolls Royce North American Technologies Inc filed Critical Rolls Royce North American Technologies Inc
Publication of EP2659112A1 publication Critical patent/EP2659112A1/de
Publication of EP2659112A4 publication Critical patent/EP2659112A4/de
Application granted granted Critical
Publication of EP2659112B1 publication Critical patent/EP2659112B1/de
Active 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F04D29/08—Sealings
    • F04D29/083—Sealings especially adapted for elastic fluid pumps
    • 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
    • F04D29/544—Blade shapes
    • 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
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps

Definitions

  • the present invention relates to gas turbine engines, and more particularly, to gas turbine engines with variable camber vane systems.
  • Document EP 0 924 389 A2 describes an inlet guide vane having a gap, in which an inlet guide vane seal is located.
  • the seal has a longitudinally extending tubular portion and a dovetail portion, wherein a longitudinal axis extends the length of the tubular portion, and wherein the tubular portion and the dovetail portion are made of an elastomeric material, such as silicone rubber.
  • a trailing edge of the strut airfoil includes a retaining slot that tapers in a direction away from the leading edge of the strut airfoil, wherein the slot extends the length of the trailing edge, and dovetail portion must be slid into the slot from one of the ends of the strut airfoil.
  • the width of the slot is only slightly greater than the width of the retaining feature of the dovetail portion.
  • a gas turbine having a pre-vane and pre-guiding element wherein the pre-vane can be pivoted about an axis arranged radially, and wherein the pre-guiding element is formed fixedly.
  • a sealing device formed as a brush seal integrated in the pre-vane is provided.
  • Document US 3 990 810 A describes a vane assembly in which a variable vane is disposed immediately adjacent in nested relationship with a concave surface on a trailing edge of a stationary vane.
  • a seal pin is disposed in a radial groove provided in the concave face of the stationary vane to prevent leakage between the nested interface of the stationary vane and the variable vane.
  • an adjustable vane assembly in which a gas seal is inserted into slots of two vanes of an assembly during its assembly.
  • the present invention relates to a unique variable camber vane system for a gas turbine engine according to claim 1. Moreover, a unique gas turbine engine is disclosed.
  • gas turbine engine 10 is an aircraft propulsion power plant.
  • gas turbine engine 10 may be a land-based or marine engine.
  • gas turbine engine 10 is a multi-spool turbofan engine.
  • gas turbine engine 10 may be a single or multi-spool turbofan, turboshaft, turbojet, turboprop gas turbine or combined cycle engine.
  • Gas turbine engine 10 includes a fan system 12, a compressor system 14, a diffuser 16, a combustion system 18 and a turbine system 20.
  • Compressor system 14 is in fluid communication with fan system 12.
  • Diffuser 16 is in fluid communication with compressor system 14.
  • Combustion system 18 is fluidly disposed between compressor system 14 and turbine system 20.
  • Fan system 12 includes a fan rotor system 22.
  • fan rotor system 22 includes one or more rotors (not shown) that are powered by turbine system 20.
  • Compressor system 14 includes a compressor rotor system 24.
  • compressor rotor system 24 includes one or more rotors (not shown) that are powered by turbine system 20.
  • Turbine system 20 includes a turbine rotor system 26.
  • turbine rotor system 26 includes one or more rotors (not shown) operative to drive fan rotor system 22 and compressor rotor system 24.
  • Turbine rotor system 26 is driving coupled to compressor rotor system 24 and fan rotor system 22 via a shafting system 28.
  • shafting system 28 includes a plurality of shafts that may rotate at the same or different speeds and directions. In some embodiments, only a single shaft may be employed.
  • combustion system 18 includes a combustion liner (not shown) that contains a continuous combustion process.
  • combustion system 18 may take other forms, and may be, for example, a wave rotor combustion system, a rotary valve combustion system, or a slinger combustion system, and may employ deflagration and/or detonation combustion processes.
  • the hot gases exiting combustor 18 are directed into turbine system 20, which extracts energy in the form of mechanical shaft power to drive fan system 12 and compressor system 14 via shafting system 28.
  • the hot gases exiting turbine system 20 are directed into a nozzle (not shown), and provide a component of the thrust output by gas turbine engine 10.
  • Fan system 12 includes a variable guide vane system 40 having a variable inlet guide vane stage 42 and a variable outlet guide vane stage 44 disposed on either side of a rotating fan stage 46.
  • Variable inlet guide vane stage 42 is operative to guide air into rotating fan stage 46, and to selectively vary the incidence angle of the air flow entering rotating fan stage 46.
  • Variable outlet guide vane stage 44 is operative to guide air exiting rotating fan stage 46, and to selectively vary the incidence angle of the air flow exiting rotating fan stage 46.
  • variable inlet guide vane stage 42 and variable outlet guide vane stage 44 are actuated by an actuation system (not shown). Although described herein as with respect to fan system 12, it will be understood that variable guide vane system 40 may also or alternatively be employed as part of compressor system 14. In addition, although variable guide vane system 40 includes both variable inlet and outlet guide vane stages, other embodiments may include only a variable inlet guide vane stage or a variable outlet guide vane stage.
  • variable inlet guide vane stage 42 in accordance with an embodiment of the present invention is illustrated. It will be understood that some embodiments of variable outlet guide vane stage 44 may be similar to variable inlet guide vane stage 42, and hence, the following description of variable inlet guide vane stage 42 is also applicable to aspects of some embodiments of variable outlet guide vane stage 44.
  • Variable inlet guide vane stage 42 includes an outer band 50, an inner band 52 and plurality of vanes 54. Outer band 50 defines an outer flowpath wall of variable inlet guide vane stage 42.
  • Inner band 52 defines an inner flowpath wall of variable inlet guide vane stage 42.
  • Vanes 54 are airfoils that extend between outer band 50 and inner band 52, and are spaced apart circumferentially. In one form, vanes 54 extend in the radial direction between outer band 50 and inner band 52. In other embodiments, vanes 54 may extend between outer band 50 and inner band 52 at other angles.
  • Each vane 54 includes an airfoil portion 56 and an airfoil portion 58.
  • Airfoil portion 56 extends between a tip portion 60 and a root portion 62.
  • airfoil portion 56 includes the trailing edge 64 of vane 54.
  • airfoil portion 56 may be formed with a leading edge of vane 54 instead of trailing edge 64, e.g., for use in variable outlet guide vane 44.
  • Airfoil portion 58 extends between a tip portion 66 and a root portion 68.
  • airfoil portion 58 includes the leading edge 70 of vane 54.
  • airfoil portion 58 may be formed with a trailing edge instead of leading edge 70, e.g., for use in variable outlet guide vane 44.
  • airfoil portion 56 is fixed, i.e., stationary.
  • airfoil portion 56 may be movable, e.g., pivotable about an axis so as to be able to vary the angle of the trailing edge of vane 54.
  • airfoil portion 58 is variable, being configured to pivot about a pivot axis 72 with respect to airfoil portion 56, to provide a variable camber for vane 54.
  • airfoil portion 58 may be fixed.
  • airfoil portion 58 is coupled to an actuation system (not shown) that is operative to selectively position airfoil portion 58 at a desired incidence angle.
  • airfoil portion 56 may also or alternatively be coupled to an actuation system (not shown) that is operative to selectively position airfoil portion 56 at a desired incidence angle.
  • Outer band 50 includes a plurality of spaced apart openings 78.
  • Inner band 52 includes a plurality of spaced apart openings 80. Openings 78 and 80 are operative to receive pivot shafts 74 and 76, respectively, and retain airfoil portions 58 in the engine axial, circumferential and radial direction.
  • pivot shafts 74 and 76 retain airfoil portion 58 in outer band 50 and inner band 52 via anti-friction bushings 82 and 84.
  • Anti-friction bushings 82 and 84 are operative to provide bearing surfaces for pivot shafts 74 and 76. Other embodiments may not include anti-friction bushings 82 and 84.
  • Airfoil portion 58 is operative to rotate in rotation directions 86 about pivot axis 72.
  • Vane 54 has a pressure side 90 and a suction side 92, wherein the pressure on pressure side 90 exceeds that of suction side 92.
  • the pressure differential between pressure side 90 and suction side 92 may vary, e.g., depending upon vane 54 camber and engine operating conditions.
  • the pressure differential between pressure side 90 and suction side 92 provides an impetus to flow from pressure side 90 to suction side 92, e.g., between airfoil portion 56 and airfoil portion 58.
  • vanes 54 include a sealing arrangement 94 operative to seal between airfoil portion 56 and airfoil portion 58.
  • Sealing arrangement 94 includes a seal strip 96 arranged to seal against fluid flow between airfoil portion 56 and airfoil portion 58 during the operation of engine 10, and to accommodate movement of one or both of airfoil portions 56 and 58, e.g., rotation of airfoil portion 58 about pivot axis 72, while sealing against fluid flow.
  • seal strip 96 is a rigid structure that does not substantially deform in use or installation. In other embodiments, seal strip 96 may be a flexible structure. In one form, seal strip 96 is formed of a polymeric material, such as Vespel® (commercially available from DuPont Engineering Polymers, located in Newark, Delaware, U.S.A.) and/or Torlon® polyamide-imide (commercially available from Solvay Advanced Polymers, located in Alpharetta, Georgia, U.S.A.). In other embodiments, seal strip 96 may be formed of other materials. In one form, seal strip 96 is disposed in a groove 98.
  • groove 98 is disposed in a face 100 of airfoil portion 56 that faces airfoil portion 58.
  • seal strip 96, groove 98 and face 100 extend between tip portion 60 and root portion 62 of airfoil portion 56.
  • seal strip 96, groove 98 and/or face 100 may extend only partially between tip portion 60 and root portion 62.
  • Face 100 is formed with a radius 102 centered on pivot axis 72.
  • face 100 is formed integrally with airfoil portion 56. In other embodiments, face 100 may be formed separately and affixed to airfoil portion 56.
  • seal strip 96 is partially installed in groove 98, that is, leaving a portion 108 of seal strip 96 extending beyond face 100 of airfoil portion 56.
  • Seal strip 96 has a width 104 greater than a width 106 of groove 98, and is installed into groove 98 with an interference fit, e.g., 25.4-50.8 ⁇ m (0.001-0.002 inch). The amount of interference may vary with the needs of the application.
  • Airfoil portion 58 includes a crown 110 facing face 100 of airfoil portion 56.
  • crown 110 is formed integrally with airfoil portion 58. In other embodiments, crown 110 may be formed separately and affixed to airfoil portion 58.
  • Crown 110 is formed with a radius 112 centered on pivot axis 72.
  • crown 110 extends between tip portion 66 and root portion 68 of airfoil portion 58, and is positioned opposite groove 98. In other embodiments, crown 110 may extend only partially between tip portion 66 and root portion 68.
  • face 100 of airfoil portion 56 is concave, and is operative to receive therein crown 110 opposite groove 98 in a nested arrangement.
  • face 100 may be convex.
  • crown 110 of airfoil portion 58 is convex, and is operative to be received into face 100 in a nested arrangement.
  • crown 110 may be convex, e.g., an inverted crown.
  • Seal strip 96 includes a rubbing surface 114.
  • rubbing surface 114 is disposed opposite radius 112 of crown 110, and is operative to contact and seal against radius 112 of crown 110 of airfoil portion 58.
  • rubbing surface 114 may rub against crown 110, e.g., until wear of seal strip 96 resulting from rotation of airfoil portion 58 reduces or eliminates contact between seal strip 96 and crown 110.
  • rubbing surface 114 may be configured to be in close proximity to crown 110, but without any rubbing contact.
  • Rubbing surface 114 is preformed prior to installation into airfoil portion 56, e.g., machined.
  • rubbing surface 114 is configured as a radius 116 centered about pivot axis 72, e.g., the same radius as radius 112 of crown 110. According to the invention, the rubbing surface 114 is concave.

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

Claims (6)

  1. Schaufelsystem mit veränderbarer Wölbung für einen Gasturbinenmotor (10), umfassend:
    einen ersten Flügelabschnitt (56) mit einem ersten Spitzenbereich (60), einem ersten Wurzelbereich (62), einer sich zumindest teilweise zwischen dem ersten Spitzenbereich (60) und dem ersten Wurzelbereich (62) erstreckenden Fläche (100) und einer Nut (98) in der Fläche (100), die zumindest teilweise zwischen dem ersten Spitzenbereich (60) und dem ersten Wurzelbereich (62) verläuft, wobei die Nut (98) eine Nutbreite (106) hat,
    einen zweiten Flügelabschnitt (58), der dazu angeordnet ist, sich bezüglich des ersten Flügelabschnitts (56) um eine Schwenkachse (72) zu drehen, wobei der zweite Flügelabschnitt (58) einen zweiten Spitzenbereich (66), einen zweiten Wurzelbereich (68) und eine Krone (110) aufweist, die sich zumindest teilweise zwischen dem zweiten Spitzenbereich (66) und dem zweiten Wurzelbereich (68) erstreckt, wobei die Krone (110) einen um die Schwenkachse (72) zentrierten und gegenüber der Nut (98) angeordneten Kronenradius (112) umfasst, und
    ein Dichtungsband (96) mit einer Dichtungsbreite (104) größer als die Breite der Nut (98) und einer konkaven Reibungsfläche (114), wobei die Reibungsfläche (114) vor einem Einbau in den ersten Flügelabschnitt (56) dazu vorgeformt ist, einen zum Kronenradius (112) komplementären und entgegengesetzten Radius (116) zu haben,
    wobei das Dichtungsband (96) wenigstens teilweise mit einer Presspassung in der Nut (98) angeordnet ist, und wobei das Dichtungsband (96) dazu angeordnet ist, gegen eine Fluidströmung zwischen dem ersten Flügelabschnitt (56) und dem zweiten Flügelabschnitt (58) abzudichten.
  2. Schaufelsystem mit veränderbarer Wölbung nach Anspruch 1,
    wobei die Reibungsfläche (114) einen mit dem Kronenradius (112) übereinstimmenden Reibungsflächenradius (116) hat.
  3. Schaufelsystem mit veränderbarer Wölbung nach Anspruch 1,
    wobei die Krone (110) integral mit dem zweiten Flügelabschnitt (58) ausgebildet ist,
    oder wobei die Fläche (100) integral mit dem ersten Flügelabschnitt (56) ausgebildet ist,
    oder wobei die Fläche (100) konkav und dazu funktionsfähig ist, die Krone (110) in sich aufzunehmen.
  4. Schaufelsystem mit veränderbarer Wölbung nach Anspruch 1,
    wobei der erste Flügelabschnitt (56) stationär ist.
  5. Schaufelsystem mit veränderbarer Wölbung nach Anspruch 4, wobei der erste Flügelabschnitt (56) und der zweite Flügelabschnitt (58) zumindest einen Teil einer Einlassleitschaufel (42) mit einer starren Vorderkante und einer verstellbaren Hinterkante bilden, wobei der erste Flügelabschnitt (56) die Vorderkante enthält und wobei der zweite Flügelabschnitt (58) die Hinterkante enthält.
  6. Schaufelsystem mit veränderbarer Wölbung nach Anspruch 1, wobei der erste Flügelabschnitt (56) und der zweite Flügelabschnitt (58) zumindest einen Teil einer Auslassleitschaufel (44) mit einer verstellbaren Vorderkante und einer starren Hinterkante bilden, wobei der erste Flügelabschnitt (56) die Vorderkante enthält und wobei der zweite Flügelabschnitt (58) die Hinterkante enthält.
EP11853198.7A 2010-12-27 2011-12-27 Gasturbinenmotor und schaufelsystem mit veränderbarer wölbung Active EP2659112B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US12/978,843 US20120163960A1 (en) 2010-12-27 2010-12-27 Gas turbine engine and variable camber vane system
PCT/US2011/067393 WO2012092277A1 (en) 2010-12-27 2011-12-27 Gas turbine engine and variable camber vane system

Publications (3)

Publication Number Publication Date
EP2659112A1 EP2659112A1 (de) 2013-11-06
EP2659112A4 EP2659112A4 (de) 2018-03-07
EP2659112B1 true EP2659112B1 (de) 2020-10-07

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ID=46317012

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11853198.7A Active EP2659112B1 (de) 2010-12-27 2011-12-27 Gasturbinenmotor und schaufelsystem mit veränderbarer wölbung

Country Status (4)

Country Link
US (1) US20120163960A1 (de)
EP (1) EP2659112B1 (de)
CA (1) CA2822965C (de)
WO (1) WO2012092277A1 (de)

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US9617864B2 (en) * 2014-07-21 2017-04-11 United Technologies Corporation Seal assembly for a guide vane assembly
EP3191715A1 (de) * 2014-09-12 2017-07-19 General Electric Company Axi-zentrifugalverdichter mit verstellbaren auslassleitschaufeln
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US10704418B2 (en) 2016-08-11 2020-07-07 General Electric Company Inlet assembly for an aircraft aft fan
US10252790B2 (en) 2016-08-11 2019-04-09 General Electric Company Inlet assembly for an aircraft aft fan
US10253779B2 (en) 2016-08-11 2019-04-09 General Electric Company Inlet guide vane assembly for reducing airflow swirl distortion of an aircraft aft fan
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Also Published As

Publication number Publication date
EP2659112A4 (de) 2018-03-07
WO2012092277A1 (en) 2012-07-05
CA2822965A1 (en) 2012-07-05
CA2822965C (en) 2020-02-11
EP2659112A1 (de) 2013-11-06
US20120163960A1 (en) 2012-06-28

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