GB1084184A - - Google Patents

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Publication number
GB1084184A
GB1084184A GB1084184DA GB1084184A GB 1084184 A GB1084184 A GB 1084184A GB 1084184D A GB1084184D A GB 1084184DA GB 1084184 A GB1084184 A GB 1084184A
Authority
GB
United Kingdom
Prior art keywords
turbine
ducted fan
blades
struts
stages
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
Publication of GB1084184A publication Critical patent/GB1084184A/en
Active legal-status Critical Current

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Classifications

    • 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
    • F02K3/072—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 counter-rotating, e.g. fan rotors
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1,084,184. Gas turbine ducted fan engines. ROLLS-ROYCE Ltd. April 18, 1966 [April 27, 1965], No.17760/65. Headings F1J and F1T. [Also in Division F2] A gas turbine ducted fan engine comprises compressor means, combustion equipment and turbine means, and an exhaust duct through which the exhaust gases from the turbine means pass, further turbine means being disposed in the exhaust duct, the further turbine means having at least two contra-rotating stages, there being ducted fan means having at least two contra-rotating stages which are drivingly connected to respective contra-rotating stages of the further turbine means. Means are provided for supplying air to or withdrawing air from the hollow interiors of the ducted fan blades so as to reduce wake turbulence downstream of the blades. The ducted fan engine shown comprises low-pressure compressor 42, high-pressure compressor 45, combustion equipment, high-pressure turbine 46, and low-pressure turbine 43. The exhaust gases from the turbines 46, 43 discharge through annular duct 11 in which are disposed further turbine means comprising contra-rotating turbine stages 13', 14'. The turbine stages 13' are carried by rotor discs 13 which are mounted on shaft 15 which rotates on bearings 16, 17 carried by stator structure. The turbine stages 14' are interconnected by shrouding 18 and the rotor-assembly 14 is mounted on bearings 20, 21 carried by the shaft 15. The rotor assembly 13 is connected by shroud ring 27 to fan rotor 28 on which are mounted ducted fan blades 30. The rotor assembly 14 is connected at the shroud ring 18 to fan rotor 31 on which are mounted ducted fan blades 32. The ducted fan blade assemblies 30, 32 are disposed within annular fan duct 24 defined between inner stator structure 22 and outer stator structure 23, radially-extending support struts 33 extending between the structures 22, 23 upstream of the fan blades 30, 32. The ducted fan assemblies 30, 32 rotate in opposite directions. The ducted fan blades 30, 32 also the struts 33 are hollow and air under pressure taken from the low pressure compressor 42 passes through ducts 47, 38 and 40 to the hollow interiors of the blades and struts and discharges therefrom through slits in the trailing edges, whereby wake turbulence downstream of the blades and struts is reduced. Alternatively the hollow interiors of the blades and struts may be connected to a source of low pressure for the purpose of boundary layer suction.
GB1084184D Active GB1084184A (en)

Publications (1)

Publication Number Publication Date
GB1084184A true GB1084184A (en)

Family

ID=1758823

Family Applications (1)

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GB1084184D Active GB1084184A (en)

Country Status (1)

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GB (1) GB1084184A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2535394A1 (en) * 1982-11-01 1984-05-04 Gen Electric COUNTER-ROTATION WORKING TURBINE
FR2606081A1 (en) * 1986-10-29 1988-05-06 Snecma PROPULSION ENGINE WITH CONTRAROTATING WORKING TURBINES
GB2462921A (en) * 2008-08-27 2010-03-03 Snecma Method for reducing the vibration levels of a propfan of contrarotating bladed disks of a turbine engine
WO2014158283A1 (en) * 2013-03-14 2014-10-02 Bronwyn Power A subsonic shock strut

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2535394A1 (en) * 1982-11-01 1984-05-04 Gen Electric COUNTER-ROTATION WORKING TURBINE
FR2606081A1 (en) * 1986-10-29 1988-05-06 Snecma PROPULSION ENGINE WITH CONTRAROTATING WORKING TURBINES
EP0270403A1 (en) * 1986-10-29 1988-06-08 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Propulsion engine with contrarotating power turbines
US4765135A (en) * 1986-10-29 1988-08-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Gas turbine engine
GB2462921A (en) * 2008-08-27 2010-03-03 Snecma Method for reducing the vibration levels of a propfan of contrarotating bladed disks of a turbine engine
FR2935427A1 (en) * 2008-08-27 2010-03-05 Snecma METHOD FOR REDUCING THE VIBRATION LEVELS OF A DOUBLET AND CONTRAROTATIVE TURBOMACHINE AIRBORNE WHEELS.
GB2462921B (en) * 2008-08-27 2012-09-05 Snecma Method for reducing the vibration levels of a propfan of contrarotating bladed discs of a turbine engine
US8375698B2 (en) 2008-08-27 2013-02-19 Snecma Method for reducing the vibration levels of a propfan of contrarotating bladed disks of a turbine engine
WO2014158283A1 (en) * 2013-03-14 2014-10-02 Bronwyn Power A subsonic shock strut
US10309236B2 (en) 2013-03-14 2019-06-04 Rolls-Royce Corporation Subsonic shock strut

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