DE1626130A1 - Gasturbinentriebwerksanlage - Google Patents

Gasturbinentriebwerksanlage

Info

Publication number
DE1626130A1
DE1626130A1 DE19681626130 DE1626130A DE1626130A1 DE 1626130 A1 DE1626130 A1 DE 1626130A1 DE 19681626130 DE19681626130 DE 19681626130 DE 1626130 A DE1626130 A DE 1626130A DE 1626130 A1 DE1626130 A1 DE 1626130A1
Authority
DE
Germany
Prior art keywords
stage
fan
fan rotor
turbine
rotor
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.)
Pending
Application number
DE19681626130
Other languages
German (de)
English (en)
Inventor
Wilde Geoffrey Light
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
Publication of DE1626130A1 publication Critical patent/DE1626130A1/de
Pending legal-status Critical Current

Links

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
    • F02K3/068—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
    • 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)
DE19681626130 1967-02-27 1968-02-26 Gasturbinentriebwerksanlage Pending DE1626130A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB9300/67A GB1113087A (en) 1967-02-27 1967-02-27 Gas turbine power plant

Publications (1)

Publication Number Publication Date
DE1626130A1 true DE1626130A1 (de) 1970-08-20

Family

ID=9869313

Family Applications (1)

Application Number Title Priority Date Filing Date
DE19681626130 Pending DE1626130A1 (de) 1967-02-27 1968-02-26 Gasturbinentriebwerksanlage

Country Status (4)

Country Link
US (1) US3505819A (enExample)
DE (1) DE1626130A1 (enExample)
FR (1) FR1554395A (enExample)
GB (1) GB1113087A (enExample)

Families Citing this family (55)

* Cited by examiner, † Cited by third party
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US3747343A (en) * 1972-02-10 1973-07-24 United Aircraft Corp Low noise prop-fan
US3847368A (en) * 1973-01-04 1974-11-12 J Sakal Lift cell
DE602004028528D1 (de) * 2004-12-01 2010-09-16 United Technologies Corp Tip-Turbinentriebwerk mit mehreren Gebläse- und Turbinenstufen
WO2006112807A2 (en) 2004-12-01 2006-10-26 United Technologies Corporation Turbine engine and method for starting a turbine engine
US8087885B2 (en) * 2004-12-01 2012-01-03 United Technologies Corporation Stacked annular components for turbine engines
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
WO2006110124A2 (en) * 2004-12-01 2006-10-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
EP1831530B1 (en) * 2004-12-01 2009-02-25 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US7631480B2 (en) * 2004-12-01 2009-12-15 United Technologies Corporation Modular tip turbine engine
WO2006059997A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Annular turbine ring rotor
US8083030B2 (en) * 2004-12-01 2011-12-27 United Technologies Corporation Gearbox lubrication supply system for a tip engine
DE602004031470D1 (de) * 2004-12-01 2011-03-31 United Technologies Corp Übergangskanal mit mitteln zur strömungsvektorbeeinflussung bei einer gasturbine
US8033092B2 (en) * 2004-12-01 2011-10-11 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
US9845727B2 (en) * 2004-12-01 2017-12-19 United Technologies Corporation Tip turbine engine composite tailcone
EP1825117B1 (en) * 2004-12-01 2012-06-13 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
WO2006059994A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Seal assembly for a fan-turbine rotor of a tip turbine engine
DE602004016065D1 (de) 2004-12-01 2008-10-02 United Technologies Corp Variable gebläseeinlassleitschaufelanordnung, turbinenmotor mit solch einer anordnung und entsprechendes steuerverfahren
US8807936B2 (en) * 2004-12-01 2014-08-19 United Technologies Corporation Balanced turbine rotor fan blade for a tip turbine engine
EP1825112B1 (en) * 2004-12-01 2013-10-23 United Technologies Corporation Cantilevered tip turbine engine
WO2006059975A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Peripheral combustor for tip turbine engine
WO2006059987A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Particle separator for tip turbine engine
US8365511B2 (en) * 2004-12-01 2013-02-05 United Technologies Corporation Tip turbine engine integral case, vane, mount and mixer
EP1825113B1 (en) * 2004-12-01 2012-10-24 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
WO2006060010A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Compressor inlet guide vane for tip turbine engine and corresponding control method
DE602004016059D1 (de) * 2004-12-01 2008-10-02 United Technologies Corp Tip-turbinentriebwerk mit wärmetauscher
EP1828567B1 (en) 2004-12-01 2011-10-12 United Technologies Corporation Diffuser aspiration for a tip turbine engine
WO2006060005A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Fan-turbine rotor assembly with integral inducer section for a tip turbine engine
EP1841960B1 (en) * 2004-12-01 2011-05-25 United Technologies Corporation Starter generator system for a tip turbine engine
WO2006059990A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Regenerative turbine blade and vane cooling for a tip turbine engine
WO2006060009A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Turbine blade engine comprising turbine clusters and radial attachment lock arrangement therefor
EP1828574B1 (en) * 2004-12-01 2010-11-03 United Technologies Corporation Close coupled gearbox assembly for a tip turbine engine
WO2006059969A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Counter-rotating compressor case and assembly method for tip turbine engine
US7887296B2 (en) * 2004-12-01 2011-02-15 United Technologies Corporation Fan blade with integral diffuser section and tip turbine blade section for a tip turbine engine
US7959532B2 (en) * 2004-12-01 2011-06-14 United Technologies Corporation Hydraulic seal for a gearbox of a tip turbine engine
US7921636B2 (en) * 2004-12-01 2011-04-12 United Technologies Corporation Tip turbine engine and corresponding operating method
WO2006059986A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
WO2006060013A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Seal assembly for a fan rotor of a tip turbine engine
WO2006060012A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine comprising turbine blade clusters and method of assembly
US20080219833A1 (en) * 2004-12-01 2008-09-11 United Technologies Corporation Inducer for a Fan Blade of a Tip Turbine Engine
US7927075B2 (en) * 2004-12-01 2011-04-19 United Technologies Corporation Fan-turbine rotor assembly for a tip turbine engine
WO2006110122A2 (en) 2004-12-01 2006-10-19 United Technologies Corporation Inflatable bleed valve for a turbine engine and a method of operating therefore
WO2006059999A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
WO2006059989A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine support structure
WO2006060011A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
WO2006062497A1 (en) * 2004-12-04 2006-06-15 United Technologies Corporation Tip turbine engine mount
US8192141B1 (en) * 2007-04-05 2012-06-05 The United States Of America As Represented By The Secretary Of The Air Force Dual compression rotor
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine
US10385868B2 (en) * 2016-07-05 2019-08-20 General Electric Company Strut assembly for an aircraft engine
US10677264B2 (en) 2016-10-14 2020-06-09 General Electric Company Supersonic single-stage turbofan engine
US12012898B2 (en) 2022-11-03 2024-06-18 General Electric Company Gas turbine engine with acoustic spacing of the fan blades and outlet guide vanes
US12428962B1 (en) 2024-06-14 2025-09-30 General Electric Company Gas turbine engine with acoustic spacing of the fan blades and outlet guide vanes
US12292017B1 (en) * 2024-06-14 2025-05-06 General Electric Company Gas turbine engine with acoustic spacing of the fan blades and outlet guide vanes
US12421854B1 (en) * 2024-06-14 2025-09-23 General Electric Company Gas turbine engine with acoustic spacing of the fan blades and outlet guide vanes
US12429067B1 (en) 2024-06-14 2025-09-30 General Electric Company Gas turbine engine with acoustic spacing of the fan blades and outlet guide vanes

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB180299A (en) * 1921-05-14 1922-10-26 Bbc Brown Boveri & Cie Improvements in rotors for centrifugal compressors
US2526409A (en) * 1945-01-09 1950-10-17 Lockheed Aircraft Corp Turbo-propeller type power plant having radial flow exhaust turbine means
US2689681A (en) * 1949-09-17 1954-09-21 United Aircraft Corp Reversely rotating screw type multiple impeller compressor
US3075743A (en) * 1958-10-20 1963-01-29 Gen Dynamics Corp Turbo-machine with slotted blades
US2998700A (en) * 1959-04-29 1961-09-05 Jr Harvey R Chaplin Jet diffuser for shrouded propellers
US3197124A (en) * 1962-04-03 1965-07-27 Sallou Jean Centrifugal pump impellers
US3194487A (en) * 1963-06-04 1965-07-13 United Aircraft Corp Noise abatement method and apparatus
US3330475A (en) * 1965-04-12 1967-07-11 United Aircraft Corp Vane construction in turbofan engine
US3363419A (en) * 1965-04-27 1968-01-16 Rolls Royce Gas turbine ducted fan engine

Also Published As

Publication number Publication date
GB1113087A (en) 1968-05-08
US3505819A (en) 1970-04-14
FR1554395A (enExample) 1969-01-17

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