SG11201402972XA - Gas turbine engine with variable overall pressure ratio - Google Patents

Gas turbine engine with variable overall pressure ratio

Info

Publication number
SG11201402972XA
SG11201402972XA SG11201402972XA SG11201402972XA SG11201402972XA SG 11201402972X A SG11201402972X A SG 11201402972XA SG 11201402972X A SG11201402972X A SG 11201402972XA SG 11201402972X A SG11201402972X A SG 11201402972XA SG 11201402972X A SG11201402972X A SG 11201402972XA
Authority
SG
Singapore
Prior art keywords
gas turbine
turbine engine
pressure ratio
overall pressure
variable overall
Prior art date
Application number
SG11201402972XA
Other languages
English (en)
Inventor
James W Norris
Daniel B Kupratis
Gary M Stetson
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of SG11201402972XA publication Critical patent/SG11201402972XA/en

Links

Classifications

    • 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
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F02C3/145—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chamber being in the reverse flow-type
    • 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
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • 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
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/105—Heating the by-pass flow
    • 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
    • F05D2220/00—Application
    • F05D2220/70—Application in combination with
    • F05D2220/76—Application in combination with an electrical generator
    • 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
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/402—Transmission of power through friction drives
    • F05D2260/4023—Transmission of power through friction drives through a friction clutch
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

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)
  • Control Of Positive-Displacement Air Blowers (AREA)
SG11201402972XA 2011-12-09 2012-10-31 Gas turbine engine with variable overall pressure ratio SG11201402972XA (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/316,058 US8935912B2 (en) 2011-12-09 2011-12-09 Gas turbine engine with variable overall pressure ratio
PCT/US2012/062659 WO2013085641A1 (en) 2011-12-09 2012-10-31 Gas turbine engine with variable overall pressure ratio

Publications (1)

Publication Number Publication Date
SG11201402972XA true SG11201402972XA (en) 2014-07-30

Family

ID=47192143

Family Applications (1)

Application Number Title Priority Date Filing Date
SG11201402972XA SG11201402972XA (en) 2011-12-09 2012-10-31 Gas turbine engine with variable overall pressure ratio

Country Status (5)

Country Link
US (1) US8935912B2 (zh)
EP (1) EP2788603B1 (zh)
CN (1) CN103906910B (zh)
SG (1) SG11201402972XA (zh)
WO (1) WO2013085641A1 (zh)

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* Cited by examiner, † Cited by third party
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US9222409B2 (en) * 2012-03-15 2015-12-29 United Technologies Corporation Aerospace engine with augmenting turbojet
US9140212B2 (en) * 2012-06-25 2015-09-22 United Technologies Corporation Gas turbine engine with reverse-flow core having a bypass flow splitter
US9523329B2 (en) * 2013-03-15 2016-12-20 United Technologies Corporation Gas turbine engine with stream diverter
US9810145B1 (en) * 2013-06-11 2017-11-07 Philip C. Bannon Ducted impeller
WO2015088606A2 (en) * 2013-12-13 2015-06-18 United Technologies Corporation Architecture for an axially compact, high performance propulsion system
US10100675B2 (en) 2014-12-09 2018-10-16 United Technologies Corporation Outer diffuser case for a gas turbine engine
US20160169102A1 (en) * 2014-12-12 2016-06-16 United Technologies Corporation Reverse core flow gas turbine engine
DE102015205516A1 (de) * 2014-12-22 2016-06-23 Dürr Systems GmbH Vorrichtung und Verfahren zur thermischen Abgasreinigung
US11225913B2 (en) 2015-02-19 2022-01-18 Raytheon Technologies Corporation Method of providing turbine engines with different thrust ratings
US10794273B2 (en) 2015-07-01 2020-10-06 Raytheon Technologies Corporation Advanced distributed engine architecture-design alternative
US10883424B2 (en) 2016-07-19 2021-01-05 Pratt & Whitney Canada Corp. Multi-spool gas turbine engine architecture
US11415063B2 (en) 2016-09-15 2022-08-16 Pratt & Whitney Canada Corp. Reverse-flow gas turbine engine
US10393067B2 (en) * 2016-08-25 2019-08-27 United Technologies Corporation Gas turbine engine with cold turbine and multiple core flowpaths
US10465611B2 (en) 2016-09-15 2019-11-05 Pratt & Whitney Canada Corp. Reverse flow multi-spool gas turbine engine with aft-end accessory gearbox drivingly connected to both high pressure spool and low pressure spool
US11035293B2 (en) 2016-09-15 2021-06-15 Pratt & Whitney Canada Corp. Reverse flow gas turbine engine with offset RGB
US10385774B2 (en) * 2016-09-19 2019-08-20 United Technologies Corporation Split compressor turbine engine
US10815899B2 (en) 2016-11-15 2020-10-27 Pratt & Whitney Canada Corp. Gas turbine engine accessories arrangement
US10533559B2 (en) * 2016-12-20 2020-01-14 Pratt & Whitney Canada Corp. Reverse flow engine architecture
US20180216525A1 (en) * 2017-01-30 2018-08-02 Pratt & Whitney Canada Corp. Gas turbine engine architecture with split compressor system
US10808624B2 (en) 2017-02-09 2020-10-20 Pratt & Whitney Canada Corp. Turbine rotor with low over-speed requirements
US11149578B2 (en) * 2017-02-10 2021-10-19 General Electric Company Propulsion system for an aircraft
US10746188B2 (en) 2017-03-14 2020-08-18 Pratt & Whitney Canada Corp. Inter-shaft bearing connected to a compressor boost system
US10473028B2 (en) 2017-07-17 2019-11-12 United Technologies Corporation Clutched compressor section for gas turbine engine
US11231043B2 (en) * 2018-02-21 2022-01-25 General Electric Company Gas turbine engine with ultra high pressure compressor
US11536153B2 (en) 2018-08-08 2022-12-27 Pratt & Whitney Canada Corp. Turboshaft gas turbine engine
US10482299B1 (en) 2018-11-05 2019-11-19 Sammy Kayara Parent and dependent recycling product codes for finished products
US11781506B2 (en) 2020-06-03 2023-10-10 Rtx Corporation Splitter and guide vane arrangement for gas turbine engines
FR3123375B1 (fr) * 2021-05-27 2023-05-12 Safran Aircraft Engines Turbomachine comprenant une machine électrique intégrée à l’arrière
US20240280053A1 (en) * 2023-02-17 2024-08-22 General Electric Company Reverse flow gas turbine engine having electric machine

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US2504181A (en) * 1950-04-18 Double compound independent rotor
GB390448A (en) 1931-10-24 1933-04-06 Milo Ab Improvements in or relating to gas turbine plants particularly for propulsion of ships
US4007892A (en) 1971-07-15 1977-02-15 Tabor Alga M Aircraft flight method and apparatus for boosting an aircraft to a very high altitude and thereafter boosting the aircraft to a high rate of forward speed
US4222235A (en) 1977-07-25 1980-09-16 General Electric Company Variable cycle engine
EP0103370A1 (en) * 1982-08-11 1984-03-21 Rolls-Royce Plc Improvements in or relating to gas turbine engines
FR2646473B1 (fr) * 1989-04-26 1991-07-05 Snecma Moteur a soufflantes contrarotatives tractrices
US6134880A (en) * 1997-12-31 2000-10-24 Concepts Eti, Inc. Turbine engine with intercooler in bypass air passage
FR2858999B1 (fr) * 2003-08-18 2005-11-11 Snecma Moteurs Turbomachine pour aeronef a emissions de bruit reduites
US20060137355A1 (en) * 2004-12-27 2006-06-29 Pratt & Whitney Canada Corp. Fan driven emergency generator
US8887485B2 (en) 2008-10-20 2014-11-18 Rolls-Royce North American Technologies, Inc. Three spool gas turbine engine having a clutch and compressor bypass
EP3135920B1 (en) * 2008-12-31 2018-12-19 Rolls-Royce North American Technologies, Inc. Variable pressure ratio compressor
US8176725B2 (en) 2009-09-09 2012-05-15 United Technologies Corporation Reversed-flow core for a turbofan with a fan drive gear system

Also Published As

Publication number Publication date
US20130145769A1 (en) 2013-06-13
WO2013085641A1 (en) 2013-06-13
EP2788603B1 (en) 2016-04-27
EP2788603A1 (en) 2014-10-15
CN103906910A (zh) 2014-07-02
CN103906910B (zh) 2016-06-29
US8935912B2 (en) 2015-01-20

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