GB1280113A - Compressors for gas turbine engines - Google Patents

Compressors for gas turbine engines

Info

Publication number
GB1280113A
GB1280113A GB31621/70A GB3162170A GB1280113A GB 1280113 A GB1280113 A GB 1280113A GB 31621/70 A GB31621/70 A GB 31621/70A GB 3162170 A GB3162170 A GB 3162170A GB 1280113 A GB1280113 A GB 1280113A
Authority
GB
United Kingdom
Prior art keywords
flow
flow section
mixed
gas turbine
air
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
GB31621/70A
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.)
Avco Corp
Original Assignee
Avco 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 Avco Corp filed Critical Avco Corp
Publication of GB1280113A publication Critical patent/GB1280113A/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
    • F04D21/00—Pump involving supersonic speed of pumped fluids
    • 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
    • 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
    • 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
    • F04D19/024—Multi-stage pumps with contrarotating parts

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

1280113 Centrifugal and axial-flow compressors; gas turbine engines AVCO CORP 30 June 1970 [4 Aug 1969] 31621/70 Headings F1C and F1G A compressor in or for a gas turbine engine comprises an axial-flow section 32, 46, Fig. 1, and a downstream, contra-rotating mixed-flow section 62. The axial-flow section discharges air at subsonic absolute velocity. The mixed-flow section has an inlet portion which is of substantially constant flow area and receives the air at supersonic relative velocity to thereby produce shock waves and reduce supersonic flow to subsonic, whereafter the air is radially accelerated and diffused in the outlet portion of the mixed-flow section. The impeller blades of the latter may be divided into an inlet row and and outlet row separated by a row of stator blades, Fig. 3 (not shown). Stator vanes (150), Fig. 8 (not shown), may be located immediately upstream of the mixed-flow section to equalize the relative velocity of the entering air over the radial extent of the annular flow duct. In the gas turbine engine shown, the compressed air is discharged through a diffuser 84 into combustion apparatus 18 comprising an annular series of cylindrical combustion units 90 which deliver hot gases into a duct 92. The latter discharges the gases through a full-admission inlet nozzle to drive turbine wheels 98, 114, which drive the respective compressor sections, and to either drive a further turbine wheel having an output shaft 30 or exhaust through a nozzle to produce propulsive thrust. Alternatively, the two compressor sections may be driven by a single turbine wheel via gearing. Sump housings 54, 72, 120 for the shaft bearings are each sealed at both ends by friction or labyrinth seal assemblies 60, 74, 106, 122.
GB31621/70A 1969-08-04 1970-06-30 Compressors for gas turbine engines Expired GB1280113A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US85726469A 1969-08-04 1969-08-04

Publications (1)

Publication Number Publication Date
GB1280113A true GB1280113A (en) 1972-07-05

Family

ID=25325589

Family Applications (1)

Application Number Title Priority Date Filing Date
GB31621/70A Expired GB1280113A (en) 1969-08-04 1970-06-30 Compressors for gas turbine engines

Country Status (5)

Country Link
US (1) US3546880A (en)
JP (1) JPS5030854B1 (en)
DE (1) DE2032562A1 (en)
GB (1) GB1280113A (en)
SE (1) SE356792B (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2226854A (en) * 1988-12-16 1990-07-11 Gen Electric A bypass turbofan jet engine subassembly
GB2503495A (en) * 2012-06-29 2014-01-01 Rolls Royce Plc Spool for turbo machinery

Families Citing this family (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3902314A (en) * 1973-11-29 1975-09-02 Avco Corp Gas turbine engine frame structure
US3918828A (en) * 1974-09-05 1975-11-11 Emerson L Kumm Flow control for compressors and pumps
FR2365702A1 (en) * 1976-09-22 1978-04-21 Mtu Muenchen Gmbh GAS TURBINE ENGINE, ESPECIALLY SMALL GAS TURBINE ENGINE
US4592204A (en) * 1978-10-26 1986-06-03 Rice Ivan G Compression intercooled high cycle pressure ratio gas generator for combined cycles
JPS55138666U (en) * 1980-04-01 1980-10-02
US4685286A (en) * 1984-05-02 1987-08-11 United Technologies Corporation Method of disassembly for a gas turbine engine
US4611464A (en) * 1984-05-02 1986-09-16 United Technologies Corporation Rotor assembly for a gas turbine engine and method of disassembly
FR2644844B1 (en) * 1989-03-23 1994-05-06 Snecma SUSPENSION OF THE LOW PRESSURE TURBINE ROTOR OF A DOUBLE BODY TURBOMACHINE
DE59010207D1 (en) * 1989-06-10 1996-04-25 Mtu Muenchen Gmbh Gas turbine engine with diagonal compressor
US8137054B2 (en) * 2008-12-23 2012-03-20 General Electric Company Supersonic compressor
US9097258B2 (en) * 2009-06-25 2015-08-04 General Electric Company Supersonic compressor comprising radial flow path
US8845277B2 (en) * 2010-05-24 2014-09-30 United Technologies Corporation Geared turbofan engine with integral gear and bearing supports
US9476355B2 (en) * 2012-02-29 2016-10-25 Siemens Energy, Inc. Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section
US10012098B2 (en) * 2012-02-29 2018-07-03 Siemens Energy, Inc. Mid-section of a can-annular gas turbine engine to introduce a radial velocity component into an air flow discharged from a compressor of the mid-section
US20140060001A1 (en) * 2012-09-04 2014-03-06 Alexander R. Beeck Gas turbine engine with shortened mid section
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
US10393381B2 (en) * 2017-01-27 2019-08-27 General Electric Company Unitary flow path structure
US10378373B2 (en) * 2017-02-23 2019-08-13 General Electric Company Flow path assembly with airfoils inserted through flow path boundary
US10247019B2 (en) 2017-02-23 2019-04-02 General Electric Company Methods and features for positioning a flow path inner boundary within a flow path assembly
US10508546B2 (en) 2017-09-20 2019-12-17 General Electric Company Turbomachine with alternatingly spaced turbine rotor blades
US10823001B2 (en) 2017-09-20 2020-11-03 General Electric Company Turbomachine with alternatingly spaced turbine rotor blades
US10738617B2 (en) 2017-09-20 2020-08-11 General Electric Company Turbomachine with alternatingly spaced turbine rotor blades
US10823000B2 (en) 2017-09-20 2020-11-03 General Electric Company Turbomachine with alternatingly spaced turbine rotor blades
US10914194B2 (en) 2017-09-20 2021-02-09 General Electric Company Turbomachine with alternatingly spaced turbine rotor blades
US11098592B2 (en) 2017-09-20 2021-08-24 General Electric Company Turbomachine with alternatingly spaced turbine rotor blades
US10781717B2 (en) 2017-09-20 2020-09-22 General Electric Company Turbomachine with alternatingly spaced turbine rotor blades
US11112119B2 (en) * 2018-10-25 2021-09-07 General Electric Company Combustor assembly for a turbo machine
US11118535B2 (en) 2019-03-05 2021-09-14 General Electric Company Reversing gear assembly for a turbo machine
BE1028108B1 (en) * 2020-02-28 2021-09-28 Safran Aero Boosters TURBOMACHINE TRANSSONIC COMPRESSOR
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly
CN114973902B (en) * 2022-04-14 2023-06-23 西北工业大学 Aeroengine low-pressure turbine model for teaching and assembly method

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2689681A (en) * 1949-09-17 1954-09-21 United Aircraft Corp Reversely rotating screw type multiple impeller compressor
USRE24810E (en) * 1952-04-30 1960-04-19 Alfred Buchi Turbine driven multi-stage blower or pump
US3037349A (en) * 1956-09-28 1962-06-05 Daimler Benz Ag Gas turbine installation, particularly for motor vehicles

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2226854A (en) * 1988-12-16 1990-07-11 Gen Electric A bypass turbofan jet engine subassembly
GB2226854B (en) * 1988-12-16 1992-04-29 Gen Electric Jet engine fan and compressor bearing support
GB2503495A (en) * 2012-06-29 2014-01-01 Rolls Royce Plc Spool for turbo machinery
GB2503495B (en) * 2012-06-29 2014-12-03 Rolls Royce Plc Spool for turbo machinery
US9366260B2 (en) 2012-06-29 2016-06-14 Rolls-Royce Plc Spool for turbo machinery
EP2679783A3 (en) * 2012-06-29 2018-03-07 Rolls-Royce plc Spool for turbo machinery

Also Published As

Publication number Publication date
DE2032562A1 (en) 1971-02-18
SE356792B (en) 1973-06-04
US3546880A (en) 1970-12-15
JPS5030854B1 (en) 1975-10-04

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLNP Patent lapsed through nonpayment of renewal fees