GB1125251A - Improved gas turbine engine - Google Patents

Improved gas turbine engine

Info

Publication number
GB1125251A
GB1125251A GB39156/66A GB3915666A GB1125251A GB 1125251 A GB1125251 A GB 1125251A GB 39156/66 A GB39156/66 A GB 39156/66A GB 3915666 A GB3915666 A GB 3915666A GB 1125251 A GB1125251 A GB 1125251A
Authority
GB
United Kingdom
Prior art keywords
compressor
turbine
gas turbine
air
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.)
Expired
Application number
GB39156/66A
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.)
Williams International Corp
Original Assignee
Williams International 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 Williams International Corp filed Critical Williams International Corp
Publication of GB1125251A publication Critical patent/GB1125251A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • F04D19/026—Multi-stage pumps with a plurality of shafts rotating at different speeds
    • 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
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/02—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps having non-centrifugal stages, e.g. centripetal
    • F04D17/025—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps having non-centrifugal stages, e.g. centripetal comprising axial flow and radial flow stages

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1,125,251. Gas turbine engines; gas turbine jet engines. WILLIAMS RESEARCH CORP. Sept. 1, 1966 [Sept. 22, 1965], No. 39156/66. Headings F1G and F1J. A gas turbine engine comprises compressor means which comprises a low-pressure axial-flow compressor and a high-pressure centrifugal compressor, the L.P. compressor being driven by an L.P. turbine, and the H.P. compressor being driven by an H.P. turbine, the turbines and the associated compressors comprising independently rotatable spools. The engine shown in Fig. 1 is a gas turbine by-pass type jet engine and comprises an axial-flow L.P. compressor 16 and a centrifugal H.P. compressor 18, annular combustion equipment 22, an H.P. turbine 24 connected to drive the H.P. compressor through shaft 56, and an L.P. turbine 26, 28 connected to drive the L.P. compressor through shaft 33. The L.P. compressor comprises four stages 34, 35, 36, 37 some of the air delivered by the first two stages 34, 35 passing on to the second two stages 36, 37, the remainder passing through the by-pass duct 14 to the outlet 31. The air delivered from the axial-flow stages 36, 37 passes through duct 17 to the centrifugal compressor 18. Air delivered by the compressor 18 passes through diffuser 19, in which are disposed vanes 61, to the combustion equipment. The L.P. turbine comprises two stages 26, 28. In Fig. 2 (not shown), the invention is applied to a gas turbine jet engine of the non-by-pass type. In the engine shown in Fig. 3 air is tapped off from the air chamber 215 of the combustion equipment and supplied to an external point of use. The air is tapped off from the chamber through passages 214 which extend through the vanes 213 in the diffuser 212. The air passes into the chamber 219 and thence through duct 217. In the embodiment of Fig. 4 (not shown) the invention is applied to a gas turbine engine of the kind having a separate power turbine from which useful shaft power is taken.
GB39156/66A 1965-09-22 1966-09-01 Improved gas turbine engine Expired GB1125251A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US489149A US3357176A (en) 1965-09-22 1965-09-22 Twin spool gas turbine engine with axial and centrifugal compressors

Publications (1)

Publication Number Publication Date
GB1125251A true GB1125251A (en) 1968-08-28

Family

ID=23942615

Family Applications (1)

Application Number Title Priority Date Filing Date
GB39156/66A Expired GB1125251A (en) 1965-09-22 1966-09-01 Improved gas turbine engine

Country Status (2)

Country Link
US (1) US3357176A (en)
GB (1) GB1125251A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2062652A5 (en) * 1969-09-25 1971-06-25 Garrett Corp
US8414249B2 (en) 2007-09-27 2013-04-09 Cummins Turbo Technologies Limited Multistage compressor with improved map width performance

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2005226584A (en) * 2004-02-13 2005-08-25 Honda Motor Co Ltd Compressor and gas turbine engine
FR2921973B1 (en) * 2007-10-04 2011-04-29 Snecma INTERMEDIATE CASING OF TURBOJET AND TURBOREACTOR
FR2932227B1 (en) * 2008-06-09 2011-07-01 Snecma TURBOJET DOUBLE FLOW
US20100326085A1 (en) * 2009-06-25 2010-12-30 Veilleux Leo J Lightweight start system for a gas turbine engine
CN102182696A (en) * 2011-04-15 2011-09-14 林钧浩 Centripetal pressurizing heat-generating ventilation compressor
US20130186058A1 (en) * 2012-01-24 2013-07-25 William G. Sheridan Geared turbomachine fan and compressor rotation
US8459038B1 (en) 2012-02-09 2013-06-11 Williams International Co., L.L.C. Two-spool turboshaft engine control system and method
US10329943B2 (en) 2014-11-18 2019-06-25 Rolls-Royce North American Technologies Inc. Split axial-centrifugal compressor
US9982676B2 (en) 2014-11-18 2018-05-29 Rolls-Royce North American Technologies Inc. Split axial-centrifugal compressor
US10480519B2 (en) * 2015-03-31 2019-11-19 Rolls-Royce North American Technologies Inc. Hybrid compressor
US10590854B2 (en) 2016-01-26 2020-03-17 United Technologies Corporation Geared gas turbine engine
US10830144B2 (en) * 2016-09-08 2020-11-10 Rolls-Royce North American Technologies Inc. Gas turbine engine compressor impeller cooling air sinks
US11156092B2 (en) * 2019-02-07 2021-10-26 Honeywell International Inc. Multistage axial-centrifugal compressor systems and methods for manufacture

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB594139A (en) * 1944-12-11 1947-11-04 Lindsay Grahame Dawson Improvements in or relating to compressors
GB697285A (en) * 1950-03-20 1953-09-16 Havilland Engine Co Ltd Improvements in or relating to centrifugal compressors
US2746246A (en) * 1952-09-05 1956-05-22 Valota Alessandro Axial flow gas turbine
US2969644A (en) * 1955-10-24 1961-01-31 Williams Res Corp Drive means for a regenerator in a reexpansion gas turbine engine
US2952973A (en) * 1958-06-02 1960-09-20 Gen Motors Corp Turbofan-ramjet engine
US3093969A (en) * 1959-05-20 1963-06-18 Avco Corp Fuel control temperature unit
US3232053A (en) * 1963-09-13 1966-02-01 Bendix Corp Fuel feed and power control apparatus for combustion engines

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2062652A5 (en) * 1969-09-25 1971-06-25 Garrett Corp
US8414249B2 (en) 2007-09-27 2013-04-09 Cummins Turbo Technologies Limited Multistage compressor with improved map width performance
US8690522B2 (en) 2007-09-27 2014-04-08 Cummins Turbo Technologies Limited Multistage compressor with improved map width performance
US8845268B2 (en) 2007-09-27 2014-09-30 Cummins Turbo Technologies Limited Multistage compressor with improved map width performance

Also Published As

Publication number Publication date
US3357176A (en) 1967-12-12

Similar Documents

Publication Publication Date Title
GB1125251A (en) Improved gas turbine engine
GB1493049A (en) Turbofan engine
GB1137087A (en) Improvements in or relating to driving radial-flow compressors
GB1113542A (en) Gas turbine engine
GB1305302A (en)
GB626044A (en) Improvements in or relating to gas turbine power plants
GB1171966A (en) Improvements in or relating to Multiple Flow Gas Turbine Jet Engines
GB987625A (en) Improvements in or relating to axial flow compressors, for example for aircraft gas turbine engines
GB1043168A (en) Improvements in or relating to turbo-compressors
US3620020A (en) Gas turbine engine
GB1321657A (en) Ducted fan gas turbine jet propulsion engine
GB891278A (en) A gas turbine power unit
GB1221344A (en) Improvements in turbines, turbo-charging compressors and processes of gas impingement upon blades of a rotor
GB586554A (en) Improvements in or relating to turbines
GB795651A (en) Improvements in or relating to aircraft power plant installations incorporating gas-turbine engines
GB981857A (en) Gas turbine engine
GB1348127A (en) Gas turbine engine
GB1173566A (en) Gas Turbine Improvements.
GB701557A (en) Improvements relating to gas turbine power plant
GB1020145A (en) Power plant e.g. for jet propulsion of aircraft
GB749598A (en) Improvements in or relating to temperature-sensitive arrangements for gas-turbine engines
GB694414A (en) Improvements in or relating to internal combustion gas turbine engines
GB1280361A (en) Improvements in or relating to gas turbine engines
GB593403A (en) Power plant for the propulsion of aircraft
GB805003A (en) Improvements in and relating to inlet duct arrangements for gas turbines and compressors