GB0319757D0 - A gas turbine engine or lift fan with variable inlet guide vanes - Google Patents

A gas turbine engine or lift fan with variable inlet guide vanes

Info

Publication number
GB0319757D0
GB0319757D0 GBGB0319757.1A GB0319757A GB0319757D0 GB 0319757 D0 GB0319757 D0 GB 0319757D0 GB 0319757 A GB0319757 A GB 0319757A GB 0319757 D0 GB0319757 D0 GB 0319757D0
Authority
GB
United Kingdom
Prior art keywords
gas turbine
turbine engine
guide vanes
inlet guide
variable inlet
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.)
Withdrawn
Application number
GBGB0319757.1A
Other versions
GB2405184A (en
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 PLC
Original Assignee
Rolls Royce PLC
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 PLC filed Critical Rolls Royce PLC
Priority to GB0319757A priority Critical patent/GB2405184A/en
Publication of GB0319757D0 publication Critical patent/GB0319757D0/en
Publication of GB2405184A publication Critical patent/GB2405184A/en
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/001—Shrouded propellers
    • 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
    • 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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/068—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type being characterised by a short axial length relative to the diameter
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B64C2027/8254—Shrouded tail rotors, e.g. "Fenestron" fans
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
GB0319757A 2003-08-22 2003-08-22 A gas turbine engine lift fan with tandem inlet guide vanes Withdrawn GB2405184A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB0319757A GB2405184A (en) 2003-08-22 2003-08-22 A gas turbine engine lift fan with tandem inlet guide vanes

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB0319757A GB2405184A (en) 2003-08-22 2003-08-22 A gas turbine engine lift fan with tandem inlet guide vanes

Publications (2)

Publication Number Publication Date
GB0319757D0 true GB0319757D0 (en) 2003-09-24
GB2405184A GB2405184A (en) 2005-02-23

Family

ID=28460129

Family Applications (1)

Application Number Title Priority Date Filing Date
GB0319757A Withdrawn GB2405184A (en) 2003-08-22 2003-08-22 A gas turbine engine lift fan with tandem inlet guide vanes

Country Status (1)

Country Link
GB (1) GB2405184A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114981521A (en) * 2019-12-18 2022-08-30 赛峰航空助推器股份有限公司 Module for a turbomachine

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2961565B1 (en) 2010-06-18 2012-09-07 Snecma AERODYNAMIC COUPLING BETWEEN TWO ANNULAR ROWS OF AUBES FIXED IN A TURBOMACHINE
GB201114380D0 (en) 2011-08-22 2011-10-05 Rolls Royce Plc An aircraft propulsion system and a method of controlling the same
FR2998012B1 (en) 2012-11-09 2018-07-13 Safran Helicopter Engines COMPRESSION ASSEMBLY FOR TURBOMACHINE
DE102014204346A1 (en) 2014-03-10 2015-09-10 Rolls-Royce Deutschland Ltd & Co Kg Method for producing a double-row paddle wheel for a turbomachine and double-row paddle wheel
EP3009604B1 (en) * 2014-09-19 2018-08-08 United Technologies Corporation Radially fastened fixed-variable vane system
US10378554B2 (en) 2014-09-23 2019-08-13 Pratt & Whitney Canada Corp. Gas turbine engine with partial inlet vane
US10145301B2 (en) 2014-09-23 2018-12-04 Pratt & Whitney Canada Corp. Gas turbine engine inlet
US9938848B2 (en) 2015-04-23 2018-04-10 Pratt & Whitney Canada Corp. Rotor assembly with wear member
US9957807B2 (en) 2015-04-23 2018-05-01 Pratt & Whitney Canada Corp. Rotor assembly with scoop
FR3039219B1 (en) * 2015-07-22 2020-02-07 Safran Aircraft Engines AIRCRAFT COMPRISING TWO CONTRAROTATIVE BLOWERS AT THE BACK OF A FUSELAGE WITH SETTING THE BLADES OF THE DOWNSTREAM BLOWER
US11391298B2 (en) 2015-10-07 2022-07-19 General Electric Company Engine having variable pitch outlet guide vanes
US20180017019A1 (en) * 2016-07-15 2018-01-18 General Electric Company Turbofan engine wth a splittered rotor fan
DE102016113568A1 (en) 2016-07-22 2018-01-25 Rolls-Royce Deutschland Ltd & Co Kg Method for producing a tandem vane segment
US10724540B2 (en) 2016-12-06 2020-07-28 Pratt & Whitney Canada Corp. Stator for a gas turbine engine fan
US10690146B2 (en) 2017-01-05 2020-06-23 Pratt & Whitney Canada Corp. Turbofan nacelle assembly with flow disruptor
US11396888B1 (en) 2017-11-09 2022-07-26 Williams International Co., L.L.C. System and method for guiding compressible gas flowing through a duct
US11952943B2 (en) 2019-12-06 2024-04-09 Pratt & Whitney Canada Corp. Assembly for a compressor section of a gas turbine engine
US20210172373A1 (en) * 2019-12-06 2021-06-10 Pratt & Whitney Canada Corp. Assembly for a compressor section of a gas turbine engine
US11149552B2 (en) 2019-12-13 2021-10-19 General Electric Company Shroud for splitter and rotor airfoils of a fan for a gas turbine engine
FR3105315B1 (en) * 2019-12-18 2022-02-18 Safran Aircraft Engines COMPRESSOR MODULE FOR TURBOMACHINE
CN113682462A (en) * 2021-09-18 2021-11-23 上海交通大学 Propulsion unit and electric drive ducted fan propulsion system with adjustable inlet pre-rotation guide vanes

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB936504A (en) * 1961-02-22 1963-09-11 Rolls Royce Improvements in compressor intakes for gas turbine engines
GB1085390A (en) * 1965-09-18 1967-09-27 Turbowerke Meia En Veb A rotor or stator for axial flow machines, particularly for extractors and blowers
DE3025753A1 (en) * 1980-07-08 1982-01-28 Mannesmann AG, 4000 Düsseldorf DEVICE FOR CONTROLLING AXIAL COMPRESSORS
FR2595117B1 (en) * 1986-02-28 1991-05-17 Mtu Muenchen Gmbh VARIABLE GEOMETRIC TURBOCHARGER

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114981521A (en) * 2019-12-18 2022-08-30 赛峰航空助推器股份有限公司 Module for a turbomachine

Also Published As

Publication number Publication date
GB2405184A (en) 2005-02-23

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Legal Events

Date Code Title Description
WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)