GB2049053B - Curved centreline air intake for a gas turbine engine - Google Patents

Curved centreline air intake for a gas turbine engine

Info

Publication number
GB2049053B
GB2049053B GB8012276A GB8012276A GB2049053B GB 2049053 B GB2049053 B GB 2049053B GB 8012276 A GB8012276 A GB 8012276A GB 8012276 A GB8012276 A GB 8012276A GB 2049053 B GB2049053 B GB 2049053B
Authority
GB
United Kingdom
Prior art keywords
gas turbine
air intake
turbine engine
centreline
curved
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
GB8012276A
Other languages
English (en)
Other versions
GB2049053A (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.)
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 GB2049053A publication Critical patent/GB2049053A/en
Application granted granted Critical
Publication of GB2049053B publication Critical patent/GB2049053B/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0266—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
    • B64D2033/0286—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/0536—Highspeed fluid intake means [e.g., jet engine intake]

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
GB8012276A 1979-05-14 1980-04-14 Curved centreline air intake for a gas turbine engine Expired GB2049053B (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US06/038,980 US4220171A (en) 1979-05-14 1979-05-14 Curved centerline air intake for a gas turbine engine

Publications (2)

Publication Number Publication Date
GB2049053A GB2049053A (en) 1980-12-17
GB2049053B true GB2049053B (en) 1983-01-12

Family

ID=21903005

Family Applications (1)

Application Number Title Priority Date Filing Date
GB8012276A Expired GB2049053B (en) 1979-05-14 1980-04-14 Curved centreline air intake for a gas turbine engine

Country Status (7)

Country Link
US (1) US4220171A (enExample)
JP (1) JPS566024A (enExample)
CA (1) CA1140349A (enExample)
DE (1) DE3018263A1 (enExample)
FR (1) FR2456845B1 (enExample)
GB (1) GB2049053B (enExample)
IT (1) IT1131162B (enExample)

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US9239012B2 (en) 2011-06-08 2016-01-19 United Technologies Corporation Flexible support structure for a geared architecture gas turbine engine
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US10724431B2 (en) 2012-01-31 2020-07-28 Raytheon Technologies Corporation Buffer system that communicates buffer supply air to one or more portions of a gas turbine engine
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US20130192198A1 (en) 2012-01-31 2013-08-01 Lisa I. Brilliant Compressor flowpath
US9169781B2 (en) 2012-01-31 2015-10-27 United Technologies Corporation Turbine engine gearbox
US20160130949A1 (en) 2012-01-31 2016-05-12 United Technologies Corporation Low noise turbine for geared turbofan engine
US10400629B2 (en) 2012-01-31 2019-09-03 United Technologies Corporation Gas turbine engine shaft bearing configuration
US8869508B2 (en) 2012-01-31 2014-10-28 United Technologies Corporation Gas turbine engine variable area fan nozzle control
US20130192251A1 (en) 2012-01-31 2013-08-01 Peter M. Munsell Buffer system that communicates buffer supply air to one or more portions of a gas turbine engine
US10107191B2 (en) 2012-02-29 2018-10-23 United Technologies Corporation Geared gas turbine engine with reduced fan noise
US9555871B2 (en) * 2012-03-05 2017-01-31 The Boeing Company Two-surface sandwich structure for accommodating in-plane expansion of one of the surfaces relative to the opposing surface
US10125693B2 (en) 2012-04-02 2018-11-13 United Technologies Corporation Geared turbofan engine with power density range
US10138809B2 (en) 2012-04-02 2018-11-27 United Technologies Corporation Geared turbofan engine with a high ratio of thrust to turbine volume
US8572943B1 (en) 2012-05-31 2013-11-05 United Technologies Corporation Fundamental gear system architecture
WO2014099087A2 (en) 2012-09-28 2014-06-26 United Technologies Corporation Method of assembly for gas turbine fan drive gear system
BR112015007733B1 (pt) 2012-10-08 2022-05-03 United Technologies Corporation Motores de turbina a gás, e, método para distribuir peso entre um conjunto de propulsor e um conjunto de gerador de gás de um motor de turbina a gás
WO2014058710A1 (en) 2012-10-09 2014-04-17 United Technologies Corporation Improved operability geared turbofan engine including compressor section variable guide vanes
US9920653B2 (en) 2012-12-20 2018-03-20 United Technologies Corporation Low pressure ratio fan engine having a dimensional relationship between inlet and fan size
US9932933B2 (en) 2012-12-20 2018-04-03 United Technologies Corporation Low pressure ratio fan engine having a dimensional relationship between inlet and fan size
US9863326B2 (en) 2013-03-12 2018-01-09 United Technologies Corporation Flexible coupling for geared turbine engine
US10605172B2 (en) 2013-03-14 2020-03-31 United Technologies Corporation Low noise turbine for geared gas turbine engine
US11719161B2 (en) 2013-03-14 2023-08-08 Raytheon Technologies Corporation Low noise turbine for geared gas turbine engine
WO2014151785A1 (en) 2013-03-15 2014-09-25 United Technologies Corporation Turbofan engine bearing and gearbox arrangement
US10724479B2 (en) 2013-03-15 2020-07-28 United Technologies Corporation Thrust efficient turbofan engine
US10316758B2 (en) 2013-05-09 2019-06-11 United Technologies Corporation Turbofan engine front section
WO2015012923A2 (en) 2013-05-09 2015-01-29 United Technologies Corporation Turbofan engine front section
EP3058202A4 (en) 2013-10-16 2017-06-28 United Technologies Corporation Geared turbofan engine with targeted modular efficiency
US10156206B2 (en) * 2013-10-24 2018-12-18 United Technologies Corporation Pivoting blocker door
US10502163B2 (en) 2013-11-01 2019-12-10 United Technologies Corporation Geared turbofan arrangement with core split power ratio
EP3063385A4 (en) 2013-11-01 2017-07-12 United Technologies Corporation Geared turbofan arrangement with core split power ratio
US8869504B1 (en) 2013-11-22 2014-10-28 United Technologies Corporation Geared turbofan engine gearbox arrangement
WO2015175056A2 (en) 2014-02-19 2015-11-19 United Technologies Corporation Gas turbine engine airfoil
WO2015126774A1 (en) 2014-02-19 2015-08-27 United Technologies Corporation Gas turbine engine airfoil
WO2015175043A2 (en) 2014-02-19 2015-11-19 United Technologies Corporation Gas turbine engine airfoil
WO2015175052A2 (en) 2014-02-19 2015-11-19 United Technologies Corporation Gas turbine engine airfoil
EP3108107B1 (en) 2014-02-19 2023-10-11 Raytheon Technologies Corporation Turbofan engine with geared architecture and lpc airfoils
EP3108115B8 (en) 2014-02-19 2023-11-08 RTX Corporation Turbofan engine with geared architecture and lpc blades
EP3108121B1 (en) 2014-02-19 2023-09-06 Raytheon Technologies Corporation Turbofan engine with geared architecture and lpc airfoils
WO2015175045A2 (en) 2014-02-19 2015-11-19 United Technologies Corporation Gas turbine engine airfoil
US10280843B2 (en) 2014-03-07 2019-05-07 United Technologies Corporation Geared turbofan with integral front support and carrier
US9976490B2 (en) 2014-07-01 2018-05-22 United Technologies Corporation Geared gas turbine engine with oil deaerator
US10060289B2 (en) 2014-07-29 2018-08-28 United Technologies Corporation Geared gas turbine engine with oil deaerator and air removal
GB201418322D0 (en) * 2014-10-16 2014-12-03 Rolls Royce Plc Gas turbine engine nacelle
US9915225B2 (en) 2015-02-06 2018-03-13 United Technologies Corporation Propulsion system arrangement for turbofan gas turbine engine
US9470093B2 (en) 2015-03-18 2016-10-18 United Technologies Corporation Turbofan arrangement with blade channel variations
US10371168B2 (en) 2015-04-07 2019-08-06 United Technologies Corporation Modal noise reduction for gas turbine engine
US10458270B2 (en) 2015-06-23 2019-10-29 United Technologies Corporation Roller bearings for high ratio geared turbofan engine
US10830136B2 (en) 2015-11-19 2020-11-10 General Electric Company Fan case for use in a turbofan engine, and method of assembling a turbofan engine
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US10669948B2 (en) 2017-01-03 2020-06-02 Raytheon Technologies Corporation Geared turbofan with non-epicyclic gear reduction system
US10738646B2 (en) 2017-06-12 2020-08-11 Raytheon Technologies Corporation Geared turbine engine with gear driving low pressure compressor and fan at common speed, and failsafe overspeed protection and shear section
US10724445B2 (en) 2018-01-03 2020-07-28 Raytheon Technologies Corporation Method of assembly for fan drive gear system with rotating carrier
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Also Published As

Publication number Publication date
IT1131162B (it) 1986-06-18
IT8021936A0 (it) 1980-05-09
JPS566024A (en) 1981-01-22
FR2456845B1 (fr) 1985-09-20
FR2456845A1 (fr) 1980-12-12
CA1140349A (en) 1983-02-01
US4220171A (en) 1980-09-02
JPS6240530B2 (enExample) 1987-08-28
GB2049053A (en) 1980-12-17
DE3018263A1 (de) 1980-11-27

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Legal Events

Date Code Title Description
PE20 Patent expired after termination of 20 years

Effective date: 20000413