[go: up one dir, main page]

CA2822965C - Moteur a turbine a gaz et systeme d'ailettes a cambrure variable - Google Patents

Moteur a turbine a gaz et systeme d'ailettes a cambrure variable Download PDF

Info

Publication number
CA2822965C
CA2822965C CA2822965A CA2822965A CA2822965C CA 2822965 C CA2822965 C CA 2822965C CA 2822965 A CA2822965 A CA 2822965A CA 2822965 A CA2822965 A CA 2822965A CA 2822965 C CA2822965 C CA 2822965C
Authority
CA
Canada
Prior art keywords
airfoil portion
airfoil
crown
vane system
variable camber
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
CA2822965A
Other languages
English (en)
Other versions
CA2822965A1 (fr
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 CA2822965A1 publication Critical patent/CA2822965A1/fr
Application granted granted Critical
Publication of CA2822965C publication Critical patent/CA2822965C/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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

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)

Abstract

Selon un mode de réalisation, la présente invention concerne un système unique d'ailettes à cambrure variable pour un moteur à turbine à gaz. Selon un autre mode de réalisation, l'invention concerne un moteur à turbine à gaz unique. D'autres modes de réalisation comprennent des appareils, des systèmes, des dispositifs, du matériel, des procédés, et des combinaisons pour moteurs à turbine à gaz et des systèmes d'ailettes à cambrure variable. D'autres modes de réalisation, formes, caractéristiques, aspects, bénéfices, et avantages sont décrits dans la description et les dessins qui y sont associés.
CA2822965A 2010-12-27 2011-12-27 Moteur a turbine a gaz et systeme d'ailettes a cambrure variable Active CA2822965C (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US12/978,843 2010-12-27
US12/978,843 US20120163960A1 (en) 2010-12-27 2010-12-27 Gas turbine engine and variable camber vane system
PCT/US2011/067393 WO2012092277A1 (fr) 2010-12-27 2011-12-27 Moteur à turbine à gaz et système d'ailettes à cambrure variable

Publications (2)

Publication Number Publication Date
CA2822965A1 CA2822965A1 (fr) 2012-07-05
CA2822965C true CA2822965C (fr) 2020-02-11

Family

ID=46317012

Family Applications (1)

Application Number Title Priority Date Filing Date
CA2822965A Active CA2822965C (fr) 2010-12-27 2011-12-27 Moteur a turbine a gaz et systeme d'ailettes a cambrure variable

Country Status (4)

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

Cited By (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

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140064955A1 (en) * 2011-09-14 2014-03-06 General Electric Company Guide vane assembly for a gas turbine engine
EP2905425B1 (fr) 2014-02-06 2019-07-10 United Technologies Corporation Système d'étanchéité et aube variable
US9617864B2 (en) * 2014-07-21 2017-04-11 United Technologies Corporation Seal assembly for a guide vane assembly
CN106687666B (zh) * 2014-09-12 2019-07-09 通用电气公司 具有可变出口导向轮叶的轴流离心式压缩机
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
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
US10662782B2 (en) * 2016-11-17 2020-05-26 Raytheon Technologies Corporation Airfoil with airfoil piece having axial seal
US10794200B2 (en) 2018-09-14 2020-10-06 United Technologies Corporation Integral half vane, ringcase, and id shroud
US10781707B2 (en) 2018-09-14 2020-09-22 United Technologies Corporation Integral half vane, ringcase, and id shroud
CN111102012B (zh) * 2018-10-25 2024-07-09 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
US11802490B2 (en) 2021-08-25 2023-10-31 Rolls-Royce Corporation Controllable variable fan outlet guide vanes
US11788429B2 (en) 2021-08-25 2023-10-17 Rolls-Royce Corporation Variable tandem fan outlet guide vanes
US11879343B2 (en) 2021-08-25 2024-01-23 Rolls-Royce Corporation Systems for controlling variable outlet guide vanes
US11686211B2 (en) 2021-08-25 2023-06-27 Rolls-Royce Corporation Variable outlet 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
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
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
US12292056B2 (en) 2023-03-17 2025-05-06 Rolls-Royce North American Technologies Inc. Segmented variable fan outlet guide vane with gear assembly
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
US12398655B2 (en) 2023-03-17 2025-08-26 Rolls-Royce North American Technologies Inc. Segmented variable fan outlet guide vane with segment interface components
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

Family Cites Families (7)

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

Cited By (3)

* 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
US12392293B2 (en) 2021-03-17 2025-08-19 Pratt & Whitney Canada Corp. Lubrication system for aircraft engine reduction gearbox

Also Published As

Publication number Publication date
WO2012092277A1 (fr) 2012-07-05
CA2822965A1 (fr) 2012-07-05
US20120163960A1 (en) 2012-06-28
EP2659112B1 (fr) 2020-10-07
EP2659112A4 (fr) 2018-03-07
EP2659112A1 (fr) 2013-11-06

Similar Documents

Publication Publication Date Title
CA2822965C (fr) Moteur a turbine a gaz et systeme d'ailettes a cambrure variable
US11168574B2 (en) Segmented non-contact seal assembly for rotational equipment
CA2762810C (fr) Systeme de deflecteurs a geometrie variable pour moteurs a turbine a gaz
US10385715B2 (en) Floating, non-contact seal with angled beams
US9810238B2 (en) Turbocharger with turbine shroud
EP2776682B1 (fr) Joint d'étanchéité de turbomachine
US10550708B2 (en) Floating, non-contact seal with at least three beams
US10753370B2 (en) Variable diffuser with axially translating end wall for a centrifugal compressor
CN107435592B (zh) 用于燃气涡轮发动机的轴间密封系统及其组装方法
US11333041B2 (en) Turbine nozzle having an angled inner band flange
US20160097297A1 (en) Compressor and turbocharger
US12180840B1 (en) Seal assembly for a turbine engine
US12055153B1 (en) Variable pitch airfoil assembly for an open fan rotor of an engine having a damping element
US12305515B2 (en) Device for sealing and reinjecting a bypass flow for a turbine nozzle
US20110158792A1 (en) Engine and vane actuation system for turbine engine
US10787921B2 (en) High pressure turbine rear side plate
US12326089B2 (en) Seal assembly for a gas turbine engine
CA3208150A1 (fr) Assemblage d~aube directrice variable pour turbine a gaz

Legal Events

Date Code Title Description
EEER Examination request

Effective date: 20161114