GB1345835A - Air intake devices for fans or compressors - Google Patents

Air intake devices for fans or compressors

Info

Publication number
GB1345835A
GB1345835A GB2567172A GB2567172A GB1345835A GB 1345835 A GB1345835 A GB 1345835A GB 2567172 A GB2567172 A GB 2567172A GB 2567172 A GB2567172 A GB 2567172A GB 1345835 A GB1345835 A GB 1345835A
Authority
GB
United Kingdom
Prior art keywords
blades
trailing edge
leading
membrane
compressors
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.)
Expired
Application number
GB2567172A
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of GB1345835A publication Critical patent/GB1345835A/en
Expired 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
    • 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
    • F01D5/148—Blades with variable camber, e.g. by ejection of fluid
    • 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
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1345835 Axial flow fans and compressors; gas turbine plant SOC NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION 1 June 1972 [3 June 1971] 25671/72 Headings F1C F1G and FIT [Also in Division F2] A fan or compressor intake comprises a series of blades whose flanks are constituted by elastic walls deformable under the action of an inflatable body so as to create between adjacent blades a sonic throat acting to attenuate noise propagating upstream. The blades may constitute fixed inlet guides (7) to the compressor or fan (1) of a gas turbine aircraft engine Figs.1, 9 (not shown). Each blade 8 may comprise, Fig.6, an elastic membrane 13 which is maintained in contact with metal leading and trailing edge portions 9, 10a by bars 11, 12 respectively which support a nose cone (3) at their inner ends. When silencing is required a valve (17) is opened to supply compressed air to inflate internal bladder 14, thus causing the flanks of membrane 13 to deform to the dotted profile 18a, 19a defining a sonic throat between adjacent blades 8. Each trailing edge portion 10a may include a passage 23 supplying a stream of air 25 through slot 24 to reduce wake noise. In a modification, Fig.7, leading and trailing edge portions 9b, 10b are connected by a rigid web 26 and membrane 13 is replaced by two membranes 28, 29 each provided with two beads 30 retained in grooves 27 by bars 31, 32. Three pairs 33, 34, 35 of bladders are provided each of which can be independently supplied with compressed air to permit differential inflation. In a further modification, Fig.8 (not shown) only one pair of bladders is provided but the membranes (28a, 29a) have a thickness which varies from the leading to the trailing edge. A relief valve (37) controls bladder inflation pressure. The blades 8 may or may not have a diffusing function The intake may include boundary layer suction devices.
GB2567172A 1971-06-03 1972-06-01 Air intake devices for fans or compressors Expired GB1345835A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7120104A FR2139741B1 (en) 1971-06-03 1971-06-03

Publications (1)

Publication Number Publication Date
GB1345835A true GB1345835A (en) 1974-02-06

Family

ID=9078043

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2567172A Expired GB1345835A (en) 1971-06-03 1972-06-01 Air intake devices for fans or compressors

Country Status (2)

Country Link
FR (1) FR2139741B1 (en)
GB (1) GB1345835A (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2235733A (en) * 1989-09-07 1991-03-13 Gen Electric Damper assembly for a jet engine strut
GB2397855A (en) * 2003-01-30 2004-08-04 Rolls Royce Plc Damping vibrations in turbomachine aerofoils
WO2005056984A1 (en) * 2003-12-06 2005-06-23 Eads Deutschland Gmbh Method for reducing the noise of turbo generators by modifying the surface circulation of a stator
EP1574668A2 (en) * 2004-03-10 2005-09-14 General Electric Company Bifurcated outlet guide vanes
DE102007002518B3 (en) * 2007-01-17 2008-07-31 Air Fertigung-Technologie Gmbh & Co.Kg Vane for e.g. water turbine, of ship machine, has blowing medium formed between cover and carrying structure, where measures are met to enable transfer of blowing medium from side of vane blade to other side of blade
EP1898055A3 (en) * 2006-09-01 2011-06-15 United Technologies Corporation Variable geometry guide vane for a gas turbine engine
EP2383442A3 (en) * 2010-04-30 2014-04-02 Rolls-Royce plc Gas turbine engine
CN113518704A (en) * 2019-02-27 2021-10-19 赛峰飞机发动机公司 Assembly of outlet guide blades for aircraft turbines using inflatable bladders
CN113863991A (en) * 2021-10-20 2021-12-31 中国航发沈阳黎明航空发动机有限责任公司 Active control flexible surface blade with high pneumatic efficiency

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4820117A (en) * 1987-07-09 1989-04-11 United Technologies Corporation Crossed I-beam structural strut
FR2696210B1 (en) * 1992-09-25 1994-10-28 Turbomeca System for adjusting the air supply conditions of a turbomachine, centrifugal compressor comprising an adjustment system and auxiliary power unit comprising such a compressor.
US10280759B2 (en) * 2016-05-25 2019-05-07 United Technologies Corporation Mechanically retained fan blade cover
US11379629B2 (en) 2020-02-21 2022-07-05 Raytheon Technologies Corporation System and process for designing internal components for a gas turbine engine

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5056738A (en) * 1989-09-07 1991-10-15 General Electric Company Damper assembly for a strut in a jet propulsion engine
GB2235733A (en) * 1989-09-07 1991-03-13 Gen Electric Damper assembly for a jet engine strut
GB2397855A (en) * 2003-01-30 2004-08-04 Rolls Royce Plc Damping vibrations in turbomachine aerofoils
GB2397855B (en) * 2003-01-30 2006-04-05 Rolls Royce Plc A turbomachine aerofoil
US7025568B2 (en) 2003-01-30 2006-04-11 Rolls-Royce Plc Turbomachine aerofoil
US7758296B2 (en) 2003-12-06 2010-07-20 Eads Deutschland Gmbh Method for reducing the noise of turbo engines
WO2005056984A1 (en) * 2003-12-06 2005-06-23 Eads Deutschland Gmbh Method for reducing the noise of turbo generators by modifying the surface circulation of a stator
EP1574668A2 (en) * 2004-03-10 2005-09-14 General Electric Company Bifurcated outlet guide vanes
EP1574668A3 (en) * 2004-03-10 2012-12-12 General Electric Company Bifurcated outlet guide vanes
EP1898055A3 (en) * 2006-09-01 2011-06-15 United Technologies Corporation Variable geometry guide vane for a gas turbine engine
DE102007002518B3 (en) * 2007-01-17 2008-07-31 Air Fertigung-Technologie Gmbh & Co.Kg Vane for e.g. water turbine, of ship machine, has blowing medium formed between cover and carrying structure, where measures are met to enable transfer of blowing medium from side of vane blade to other side of blade
EP2383442A3 (en) * 2010-04-30 2014-04-02 Rolls-Royce plc Gas turbine engine
US8870530B2 (en) 2010-04-30 2014-10-28 Rolls-Royce Plc Gas turbine engine
CN113518704A (en) * 2019-02-27 2021-10-19 赛峰飞机发动机公司 Assembly of outlet guide blades for aircraft turbines using inflatable bladders
CN113518704B (en) * 2019-02-27 2023-11-24 赛峰飞机发动机公司 Assembly of outlet guide vanes for an aircraft turbine using an inflatable bladder
CN113863991A (en) * 2021-10-20 2021-12-31 中国航发沈阳黎明航空发动机有限责任公司 Active control flexible surface blade with high pneumatic efficiency

Also Published As

Publication number Publication date
FR2139741B1 (en) 1975-01-17
FR2139741A1 (en) 1973-01-12

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee