US20120163960A1 - Gas turbine engine and variable camber vane system - Google Patents

Gas turbine engine and variable camber vane system Download PDF

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Publication number
US20120163960A1
US20120163960A1 US12/978,843 US97884310A US2012163960A1 US 20120163960 A1 US20120163960 A1 US 20120163960A1 US 97884310 A US97884310 A US 97884310A US 2012163960 A1 US2012163960 A1 US 2012163960A1
Authority
US
United States
Prior art keywords
airfoil
crown
gas turbine
turbine engine
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.)
Abandoned
Application number
US12/978,843
Other languages
English (en)
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
Priority to US12/978,843 priority Critical patent/US20120163960A1/en
Assigned to ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES, INC. reassignment ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES, INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: MOLNAR, Dan, MORTON, JAMES, RESS, ROBERT A., JR.
Priority to CA2822965A priority patent/CA2822965C/fr
Priority to EP11853198.7A priority patent/EP2659112B1/fr
Priority to PCT/US2011/067393 priority patent/WO2012092277A1/fr
Publication of US20120163960A1 publication Critical patent/US20120163960A1/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
    • 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
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
    • 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

  • FIG. 1 schematically depicts some aspects of a non-limiting example of a gas turbine engine in accordance with an embodiment of the present invention.
  • Airfoil portion 58 includes a crown 110 facing face 100 of airfoil portion 56 .
  • crown 110 is formed integrally with airfoil portion 58 .
  • 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 .
  • 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.
  • the crown is formed integrally with the second airfoil portion.
  • the seal strip is fitted in the groove with an interference fit.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US12/978,843 2010-12-27 2010-12-27 Gas turbine engine and variable camber vane system Abandoned US20120163960A1 (en)

Priority Applications (4)

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
CA2822965A CA2822965C (fr) 2010-12-27 2011-12-27 Moteur a turbine a gaz et systeme d'ailettes a cambrure variable
EP11853198.7A EP2659112B1 (fr) 2010-12-27 2011-12-27 Moteur à turbine à gaz et système d'ailettes à cambrure variable
PCT/US2011/067393 WO2012092277A1 (fr) 2010-12-27 2011-12-27 Moteur à turbine à gaz et système d'ailettes à cambrure variable

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
US20120163960A1 true US20120163960A1 (en) 2012-06-28

Family

ID=46317012

Family Applications (1)

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

Country Status (4)

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

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013081714A3 (fr) * 2011-09-14 2013-08-15 General Electric Company Ensemble aube directrice pour moteur à turbine à gaz
EP2905425A1 (fr) * 2014-02-06 2015-08-12 United Technologies Corporation Système d'étanchéité et aube variable
US20160017739A1 (en) * 2014-07-21 2016-01-21 United Technologies Corporation Seal assembly for a guide vane assembly
EP3093442A1 (fr) * 2015-05-15 2016-11-16 United Technologies Corporation Positionnement d'entretoise d'aube et systèmes de fixation
US20170248156A1 (en) * 2014-09-12 2017-08-31 General Electric Company Axi-centrifugal compressor with variable outlet guide vanes
US20180135428A1 (en) * 2016-11-17 2018-05-17 United Technologies Corporation Airfoil with airfoil piece having axial seal
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
US10259565B2 (en) 2016-08-11 2019-04-16 General Electric Company Inlet assembly for an aircraft aft fan
EP3623581A1 (fr) * 2018-09-14 2020-03-18 United Technologies Corporation Demi-aube, boîtier d'anneau et chemise id intégrés
CN111102012A (zh) * 2018-10-25 2020-05-05 中国科学院工程热物理研究所 采用自适应康达喷气的叶片及制作方法
US10704418B2 (en) 2016-08-11 2020-07-07 General Electric Company Inlet assembly for an aircraft aft fan
US10794200B2 (en) 2018-09-14 2020-10-06 United Technologies Corporation Integral half vane, ringcase, and id shroud
US11686211B2 (en) 2021-08-25 2023-06-27 Rolls-Royce Corporation Variable outlet guide vanes
US11788429B2 (en) 2021-08-25 2023-10-17 Rolls-Royce Corporation Variable tandem fan outlet guide vanes
US11802490B2 (en) 2021-08-25 2023-10-31 Rolls-Royce Corporation Controllable variable fan outlet guide vanes
US11879343B2 (en) 2021-08-25 2024-01-23 Rolls-Royce Corporation Systems for controlling variable outlet guide vanes
US12292056B2 (en) 2023-03-17 2025-05-06 Rolls-Royce North American Technologies Inc. Segmented variable fan outlet guide vane with gear assembly
US12320260B2 (en) 2023-03-17 2025-06-03 Rolls-Royce North American Technologies Inc. Segmented variable fan outlet guide vane with cam assembly and unique actuation mechanisms
US12352287B1 (en) * 2024-03-25 2025-07-08 Rtx Corporation Variable guide vane for aircraft propulsion system
US12398655B2 (en) 2023-03-17 2025-08-26 Rolls-Royce North American Technologies Inc. Segmented variable fan outlet guide vane with segment interface components
US12398648B2 (en) 2023-03-17 2025-08-26 Rolls-Royce North American Technologies Inc. Segmented variable fan outlet guide vane with cam assembly and pass through actuation mechanisms
US20250283421A1 (en) * 2024-03-06 2025-09-11 General Electric Company Gas turbine engine including stub-tandem variable inlet guide vanes
US12428974B2 (en) 2023-03-17 2025-09-30 Rolls-Royce North American Technologies Inc. Segmented variable fan outlet guide vane with unique actuation mechanisms
US12480422B2 (en) 2023-03-17 2025-11-25 Rolls-Royce North American Technologies Inc. Segmented variable fan outlet guide vane with pass through actuation mechanisms

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11174916B2 (en) 2019-03-21 2021-11-16 Pratt & Whitney Canada Corp. Aircraft engine reduction gearbox
US11268453B1 (en) 2021-03-17 2022-03-08 Pratt & Whitney Canada Corp. Lubrication system for aircraft engine reduction gearbox

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8632302B2 (en) * 2009-12-07 2014-01-21 Dresser-Rand Company Compressor performance adjustment system

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US3887297A (en) * 1974-06-25 1975-06-03 United Aircraft Corp Variable leading edge stator vane assembly
CA1038298A (fr) * 1975-10-14 1978-09-12 Westinghouse Canada Limited Rotor a pales orientables pour turbine a gaz
US3990810A (en) * 1975-12-23 1976-11-09 Westinghouse Electric Corporation Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaped gas turbine
US6045325A (en) * 1997-12-18 2000-04-04 United Technologies Corporation Apparatus for minimizing inlet airflow turbulence in a gas turbine engine
DE10352789B4 (de) * 2003-11-12 2006-04-13 Mtu Aero Engines Gmbh Gasturbine
US7730714B2 (en) * 2005-11-29 2010-06-08 General Electric Company Turbofan gas turbine engine with variable fan outlet guide vanes

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8632302B2 (en) * 2009-12-07 2014-01-21 Dresser-Rand Company Compressor performance adjustment system

Cited By (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013081714A3 (fr) * 2011-09-14 2013-08-15 General Electric Company Ensemble aube directrice pour moteur à turbine à gaz
EP2905425A1 (fr) * 2014-02-06 2015-08-12 United Technologies Corporation Système d'étanchéité et aube variable
US9803559B2 (en) 2014-02-06 2017-10-31 United Technologies Corporation Variable vane and seal arrangement
US20160017739A1 (en) * 2014-07-21 2016-01-21 United Technologies Corporation Seal assembly for a guide vane assembly
US9617864B2 (en) * 2014-07-21 2017-04-11 United Technologies Corporation Seal assembly for a guide vane assembly
US20170248156A1 (en) * 2014-09-12 2017-08-31 General Electric Company Axi-centrifugal compressor with variable outlet guide vanes
US11448235B2 (en) * 2014-09-12 2022-09-20 General Electric Company Axi-centrifugal compressor with variable outlet guide vanes
US10704563B2 (en) * 2014-09-12 2020-07-07 General Electric Company Axi-centrifugal compressor with variable outlet guide vanes
EP3093442A1 (fr) * 2015-05-15 2016-11-16 United Technologies Corporation Positionnement d'entretoise d'aube et systèmes de fixation
US20160333726A1 (en) * 2015-05-15 2016-11-17 United Technologies Corporation Vane strut positioning and securing systems
US9879560B2 (en) * 2015-05-15 2018-01-30 United Technologies Corporation Vane strut positioning and securing systems
US10704418B2 (en) 2016-08-11 2020-07-07 General Electric Company Inlet assembly for an aircraft aft fan
US10259565B2 (en) 2016-08-11 2019-04-16 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
US10252790B2 (en) 2016-08-11 2019-04-09 General Electric Company Inlet assembly for an aircraft aft fan
US10662782B2 (en) * 2016-11-17 2020-05-26 Raytheon Technologies Corporation Airfoil with airfoil piece having axial seal
US20180135428A1 (en) * 2016-11-17 2018-05-17 United Technologies Corporation Airfoil with airfoil piece having axial seal
EP3623581A1 (fr) * 2018-09-14 2020-03-18 United Technologies Corporation Demi-aube, boîtier d'anneau et chemise id intégrés
US10781707B2 (en) 2018-09-14 2020-09-22 United Technologies Corporation Integral half vane, ringcase, and id shroud
US10794200B2 (en) 2018-09-14 2020-10-06 United Technologies Corporation Integral half vane, ringcase, and id shroud
CN111102012A (zh) * 2018-10-25 2020-05-05 中国科学院工程热物理研究所 采用自适应康达喷气的叶片及制作方法
US11788429B2 (en) 2021-08-25 2023-10-17 Rolls-Royce Corporation Variable tandem fan outlet guide vanes
US11686211B2 (en) 2021-08-25 2023-06-27 Rolls-Royce Corporation Variable outlet guide vanes
US11802490B2 (en) 2021-08-25 2023-10-31 Rolls-Royce Corporation Controllable variable fan outlet guide vanes
US11879343B2 (en) 2021-08-25 2024-01-23 Rolls-Royce Corporation Systems for controlling variable outlet guide vanes
US12292056B2 (en) 2023-03-17 2025-05-06 Rolls-Royce North American Technologies Inc. Segmented variable fan outlet guide vane with gear assembly
US12320260B2 (en) 2023-03-17 2025-06-03 Rolls-Royce North American Technologies Inc. Segmented variable fan outlet guide vane with cam assembly and unique actuation mechanisms
US12398655B2 (en) 2023-03-17 2025-08-26 Rolls-Royce North American Technologies Inc. Segmented variable fan outlet guide vane with segment interface components
US12398648B2 (en) 2023-03-17 2025-08-26 Rolls-Royce North American Technologies Inc. Segmented variable fan outlet guide vane with cam assembly and pass through actuation mechanisms
US12428974B2 (en) 2023-03-17 2025-09-30 Rolls-Royce North American Technologies Inc. Segmented variable fan outlet guide vane with unique actuation mechanisms
US12480422B2 (en) 2023-03-17 2025-11-25 Rolls-Royce North American Technologies Inc. Segmented variable fan outlet guide vane with pass through actuation mechanisms
US20250283421A1 (en) * 2024-03-06 2025-09-11 General Electric Company Gas turbine engine including stub-tandem variable inlet guide vanes
US12352287B1 (en) * 2024-03-25 2025-07-08 Rtx Corporation Variable guide vane for aircraft propulsion system

Also Published As

Publication number Publication date
WO2012092277A1 (fr) 2012-07-05
CA2822965A1 (fr) 2012-07-05
EP2659112A4 (fr) 2018-03-07
CA2822965C (fr) 2020-02-11
EP2659112B1 (fr) 2020-10-07
EP2659112A1 (fr) 2013-11-06

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Legal Events

Date Code Title Description
AS Assignment

Owner name: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES, INC., IND

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:RESS, ROBERT A., JR.;MOLNAR, DAN;MORTON, JAMES;SIGNING DATES FROM 20110105 TO 20110121;REEL/FRAME:026108/0605

STCB Information on status: application discontinuation

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