GB0912166D0 - A turbofan gas turbine engine - Google Patents

A turbofan gas turbine engine

Info

Publication number
GB0912166D0
GB0912166D0 GB0912166A GB0912166A GB0912166D0 GB 0912166 D0 GB0912166 D0 GB 0912166D0 GB 0912166 A GB0912166 A GB 0912166A GB 0912166 A GB0912166 A GB 0912166A GB 0912166 D0 GB0912166 D0 GB 0912166D0
Authority
GB
United Kingdom
Prior art keywords
gas turbine
turbine engine
turbofan gas
turbofan
engine
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Withdrawn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
GB0912166A
Other versions
GB2471845A (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 GB0912166A priority Critical patent/GB2471845A/en
Publication of GB0912166D0 publication Critical patent/GB0912166D0/en
Publication of GB2471845A publication Critical patent/GB2471845A/en
Withdrawn legal-status Critical Current

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
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • 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
    • F02K3/06—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 with front fan
GB0912166A 2009-07-14 2009-07-14 Fan outlet guide vane arrangement in a turbofan gas turbine engine Withdrawn GB2471845A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB0912166A GB2471845A (en) 2009-07-14 2009-07-14 Fan outlet guide vane arrangement in a turbofan gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB0912166A GB2471845A (en) 2009-07-14 2009-07-14 Fan outlet guide vane arrangement in a turbofan gas turbine engine

Publications (2)

Publication Number Publication Date
GB0912166D0 true GB0912166D0 (en) 2009-08-26
GB2471845A GB2471845A (en) 2011-01-19

Family

ID=41057887

Family Applications (1)

Application Number Title Priority Date Filing Date
GB0912166A Withdrawn GB2471845A (en) 2009-07-14 2009-07-14 Fan outlet guide vane arrangement in a turbofan gas turbine engine

Country Status (1)

Country Link
GB (1) GB2471845A (en)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10107191B2 (en) 2012-02-29 2018-10-23 United Technologies Corporation Geared gas turbine engine with reduced fan noise
US20130219922A1 (en) * 2012-02-29 2013-08-29 Jonathan Gilson Geared gas turbine engine with reduced fan noise
EP3799030A1 (en) * 2019-09-26 2021-03-31 Rolls-Royce Deutschland Ltd & Co KG Acoustic liner and gas turbine engine with such acoustic liner
US11566564B2 (en) 2020-07-08 2023-01-31 Raytheon Technologies Corporation Acoustically treated panels
US11230928B1 (en) 2020-07-22 2022-01-25 Raytheon Technologies Corporation Guide vane with truss structure and honeycomb
US11512608B2 (en) 2020-08-14 2022-11-29 Raytheon Technologies Corporation Passive transpirational flow acoustically lined guide vane
US11408349B2 (en) * 2020-08-14 2022-08-09 Raytheon Technologies Corporation Active flow control transpirational flow acoustically lined guide vane
US11804206B2 (en) 2021-05-12 2023-10-31 Goodrich Corporation Acoustic panel for noise attenuation
US11830467B2 (en) 2021-10-16 2023-11-28 Rtx Coroporation Unit cell resonator networks for turbomachinery bypass flow structures
US11781485B2 (en) 2021-11-24 2023-10-10 Rtx Corporation Unit cell resonator networks for gas turbine combustor tone damping

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3883264A (en) * 1971-04-08 1975-05-13 Gadicherla V R Rao Quiet fan with non-radial elements
US3820628A (en) * 1972-10-02 1974-06-28 United Aircraft Corp Sound suppression means for rotating machinery
US5169288A (en) * 1991-09-06 1992-12-08 General Electric Company Low noise fan assembly
FR2681644B1 (en) * 1991-09-20 1995-02-24 Onera (Off Nat Aerospatiale) IMPROVEMENT FOR BLOWERS, PARTICULARLY FOR TURBOREACTORS WITH AT LEAST TWO FLOWS.
DE102006060694B4 (en) * 2006-12-18 2020-07-09 Rolls-Royce Deutschland Ltd & Co Kg Rotor and stator blade arrangement for a gas turbine engine

Also Published As

Publication number Publication date
GB2471845A (en) 2011-01-19

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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)