GB1197711A - Improvements in Turbofan Type Engine. - Google Patents

Improvements in Turbofan Type Engine.

Info

Publication number
GB1197711A
GB1197711A GB48228/65A GB4822865A GB1197711A GB 1197711 A GB1197711 A GB 1197711A GB 48228/65 A GB48228/65 A GB 48228/65A GB 4822865 A GB4822865 A GB 4822865A GB 1197711 A GB1197711 A GB 1197711A
Authority
GB
United Kingdom
Prior art keywords
compressor
wheel
rotor
blades
hub
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
GB48228/65A
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of GB1197711A publication Critical patent/GB1197711A/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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/022—Blade-carrying members, e.g. rotors with concentric rows of axial 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
    • 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
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • 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
    • 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

Abstract

1,197,711. Gas turbine ducted fan engines. GENERAL ELECTRIC CO. Nov. 12, 1965 [Dec. 2, 1964 (2)], No.48228/65. Heading F1J. A front fan jet engine has an air inlet, an axial-flow compressor, a combustion chamber or chambers, a turbine driven by gases from the combustion chamber(s) for driving the compressor and an exhaust nozzle, the air inlet being divided into inner and outer concentric annular passages by a flow splitter and the compressor comprising a first wheel secured to a shaft and having a plurality of compressor blades rotatable in the inner passage and a second wheel secured to the shaft downstream of the first and having a plurality of compressor blades rotatable in the inner and outer passages. The compressor 10 shown in Fig. 2 comprises a first wheel 64 from the hub 65 of which project a plurality of radially extending rotor blades 66. A hub fairing 67 provides a smooth entry into the wheel 64 and the peripheral surface 68 of the hub 65 between the blades 66 forms a smooth continuation of the fairing 67. The wheel 64 is connected by a cylindrical spacer 69 to a second wheel 70 having a hub 72 from which project a plurality of rotor blades 74, the peripheral surface 73 of the hub 72 between the blades 74 continuing the smooth inner flow path boundary wall of the compressor. A casing surrounds the wheels 64, 70 to define an annular flow passage 14 and includes a first plurality of stator vanes 78 intermediate the wheels 64, 70 and a second plurality of stator vanes 80 downstream of the wheel 70. Shrouds 84, 85 are provided at the inner ends of the stator vanes 78, 80, respectively, and are shaped to form a continuation of the peripheral surfaces 68, 73, respectively. Each blade 74 comprises an inner portion 74a and an outer portion 74b separated by a shroud member 88 which forms part of a contoured flowsplitter 90 dividing the annular flow passage 14 into an inner annulus 14a and an outer annulus 14b. In addition to the shroud member 88, the flow-splitter 90 comprises a forwardly-extending portion 92, having a first section 92a affixed to the stator vanes 78 and second section 92b affixed to the rotor blades 66 extending forwardly of the first, and a rearwardlyextending member 94 affixed to the stator vanes 80. The outer annulus 14b is designed to pass approximately the same mass flow in a single rotor stage comprising rotor blade means 74b as the inner annulus 14a , wherein the inner portion of a second rotor stage comprising rotor blade means 74a is supercharged by a first rotor stage comprising rotor blade means 66. The outer wall 94a of the member 94 and the rear portion of the outer surface 88a of the member 88 are sloped to provide, in combination with a sloping portion 18b of the inner surface 18 of the casing, a convergent flow passage such that the slope of the blade tips 74c of the outer portions 74b of the rotor blades 74 is minimized.
GB48228/65A 1964-12-02 1965-11-12 Improvements in Turbofan Type Engine. Expired GB1197711A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US41668164A 1964-12-02 1964-12-02
US41668064A 1964-12-02 1964-12-02

Publications (1)

Publication Number Publication Date
GB1197711A true GB1197711A (en) 1970-07-08

Family

ID=27023449

Family Applications (1)

Application Number Title Priority Date Filing Date
GB48228/65A Expired GB1197711A (en) 1964-12-02 1965-11-12 Improvements in Turbofan Type Engine.

Country Status (3)

Country Link
DE (1) DE1526815A1 (en)
GB (1) GB1197711A (en)
SE (1) SE333275B (en)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0203881A1 (en) * 1985-05-29 1986-12-03 United Technologies Corporation Ducted prop engine
EP1147291A2 (en) * 1998-02-26 2001-10-24 Allison Advanced Development Company Compressor endwall bleed system
EP1632672A3 (en) * 2004-09-03 2011-11-16 MTU Aero Engines AG Fan for an aircraft engine
EP2441674A1 (en) * 2010-10-15 2012-04-18 Airbus Opérations SAS Aircraft nacelle including a rear frame tilted towards the rear
US20170058677A1 (en) * 2015-08-27 2017-03-02 Rolls Royce North American Technologies Inc. Methods of Creating Fluidic Barriers In Turbine Engines
CN110005544A (en) * 2019-05-12 2019-07-12 西北工业大学 From driving by-pass air duct annular flabellum compression set
CN111322158A (en) * 2018-12-14 2020-06-23 劳斯莱斯有限公司 Ice crystal protection for gas turbine engines
US11247780B2 (en) 2018-08-22 2022-02-15 Rolls-Royce Plc Turbomachine having inner and outer fans with hub-tip ratios
US11306682B2 (en) 2018-08-22 2022-04-19 Rolls-Royce Plc Concentric turbomachine with trailing edge
US11313327B2 (en) 2018-08-22 2022-04-26 Rolls-Royce Plc Concentric turbomachine with electric machine
US11371350B2 (en) 2018-08-22 2022-06-28 Rolls-Royce Plc Concentric turbomachine with electric machine
US11371467B2 (en) 2018-08-22 2022-06-28 Rolls-Royce Plc Concentric turbomachine with electric machine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008013542A1 (en) 2008-03-11 2009-09-17 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with multi-rotor arrangement

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0203881A1 (en) * 1985-05-29 1986-12-03 United Technologies Corporation Ducted prop engine
US4704862A (en) * 1985-05-29 1987-11-10 United Technologies Corporation Ducted prop engine
EP1147291A2 (en) * 1998-02-26 2001-10-24 Allison Advanced Development Company Compressor endwall bleed system
EP1147291A4 (en) * 1998-02-26 2003-03-26 Allison Advanced Dev Co Compressor endwall bleed system
EP1632672A3 (en) * 2004-09-03 2011-11-16 MTU Aero Engines AG Fan for an aircraft engine
EP2441674A1 (en) * 2010-10-15 2012-04-18 Airbus Opérations SAS Aircraft nacelle including a rear frame tilted towards the rear
FR2966126A1 (en) * 2010-10-15 2012-04-20 Airbus Operations Sas AIRCRAFT NACELLE INCORPORATING A REAR FRAME INCLINE TOWARDS THE REAR
US9284060B2 (en) 2010-10-15 2016-03-15 Airbus Operations (S.A.S) Aircraft nacelle including a rear frame inclined to the rear
US20170058677A1 (en) * 2015-08-27 2017-03-02 Rolls Royce North American Technologies Inc. Methods of Creating Fluidic Barriers In Turbine Engines
US10267160B2 (en) * 2015-08-27 2019-04-23 Rolls-Royce North American Technologies Inc. Methods of creating fluidic barriers in turbine engines
US11247780B2 (en) 2018-08-22 2022-02-15 Rolls-Royce Plc Turbomachine having inner and outer fans with hub-tip ratios
US11306682B2 (en) 2018-08-22 2022-04-19 Rolls-Royce Plc Concentric turbomachine with trailing edge
US11313327B2 (en) 2018-08-22 2022-04-26 Rolls-Royce Plc Concentric turbomachine with electric machine
US11371350B2 (en) 2018-08-22 2022-06-28 Rolls-Royce Plc Concentric turbomachine with electric machine
US11371467B2 (en) 2018-08-22 2022-06-28 Rolls-Royce Plc Concentric turbomachine with electric machine
CN111322158A (en) * 2018-12-14 2020-06-23 劳斯莱斯有限公司 Ice crystal protection for gas turbine engines
CN110005544A (en) * 2019-05-12 2019-07-12 西北工业大学 From driving by-pass air duct annular flabellum compression set

Also Published As

Publication number Publication date
DE1526815A1 (en) 1971-01-28
SE333275B (en) 1971-03-08

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Legal Events

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