SE8703304L - MOTRO-TURNING TURBO FLASH ENGINE WITH HIGH PREPARATION - Google Patents

MOTRO-TURNING TURBO FLASH ENGINE WITH HIGH PREPARATION

Info

Publication number
SE8703304L
SE8703304L SE8703304A SE8703304A SE8703304L SE 8703304 L SE8703304 L SE 8703304L SE 8703304 A SE8703304 A SE 8703304A SE 8703304 A SE8703304 A SE 8703304A SE 8703304 L SE8703304 L SE 8703304L
Authority
SE
Sweden
Prior art keywords
drive shaft
compressor
motro
turning
blade row
Prior art date
Application number
SE8703304A
Other languages
Unknown language ( )
Swedish (sv)
Other versions
SE8703304D0 (en
Inventor
A R Stuart
Original Assignee
Gen Electric
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 Gen Electric filed Critical Gen Electric
Publication of SE8703304D0 publication Critical patent/SE8703304D0/en
Publication of SE8703304L publication Critical patent/SE8703304L/en

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
    • F02K3/072—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 counter-rotating, e.g. fan rotors
    • 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
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors

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)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

A gas turbine engine comprises a core gas generator engine 16, a power turbine, 30 a fan section 52, and a booster compressor 66. The power turbine 16 includes first and second counterrotatiable turbine blade rows effective for rotating first and second drive shafts, 44, 48 respectively. The fan section includes a first fan blade row 58 connected to the first drive shaft 44 and a second fan blade row 62 connected to the second drive shaft 48. The booster compressor includes a first compressor blade row 70 connected to the first drive shaft 44 and a second compressor blade row 74 connected to the second drive shaft 48. An alternative configuration of compressor blade rows is disclosed (Fig. 2). The power turbine blade rows rotate at substantially the same speed. <IMAGE>
SE8703304A 1986-08-29 1987-08-26 MOTRO-TURNING TURBO FLASH ENGINE WITH HIGH PREPARATION SE8703304L (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US90225986A 1986-08-29 1986-08-29

Publications (2)

Publication Number Publication Date
SE8703304D0 SE8703304D0 (en) 1987-08-26
SE8703304L true SE8703304L (en) 1988-03-01

Family

ID=25415571

Family Applications (1)

Application Number Title Priority Date Filing Date
SE8703304A SE8703304L (en) 1986-08-29 1987-08-26 MOTRO-TURNING TURBO FLASH ENGINE WITH HIGH PREPARATION

Country Status (6)

Country Link
JP (1) JPS63106335A (en)
DE (1) DE3728436A1 (en)
FR (1) FR2603344A1 (en)
GB (1) GB2194292A (en)
IT (1) IT1222557B (en)
SE (1) SE8703304L (en)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3812027A1 (en) * 1988-04-11 1989-10-26 Mtu Muenchen Gmbh PROPFAN TURBO ENGINE
US5010729A (en) * 1989-01-03 1991-04-30 General Electric Company Geared counterrotating turbine/fan propulsion system
US4969325A (en) * 1989-01-03 1990-11-13 General Electric Company Turbofan engine having a counterrotating partially geared fan drive turbine
US4916894A (en) * 1989-01-03 1990-04-17 General Electric Company High bypass turbofan engine having a partially geared fan drive turbine
DE4122008A1 (en) * 1991-07-03 1993-01-14 Mtu Muenchen Gmbh GAUGE ENGINE WITH COUNTER-PRESSURE LOW-PRESSURE COMPRESSOR (BOOSTER)
US6666017B2 (en) * 2002-05-24 2003-12-23 General Electric Company Counterrotatable booster compressor assembly for a gas turbine engine
US7246484B2 (en) * 2003-08-25 2007-07-24 General Electric Company FLADE gas turbine engine with counter-rotatable fans
FR2866073B1 (en) * 2004-02-11 2006-07-28 Snecma Moteurs TURBOREACTOR HAVING TWO SOLIDARITY CONTRAROTATIVE BLOWERS OF A CONTRAROTATIVE LOW-PRESSURE COMPRESSOR
FR2866387B1 (en) * 2004-02-12 2008-03-14 Snecma Moteurs AERODYNAMIC ADAPTATION OF THE BACK BLOW OF A DOUBLE BLOWER TURBOREACTOR
US7603844B2 (en) * 2005-10-19 2009-10-20 General Electric Company Gas turbine engine assembly and methods of assembling same
US7966806B2 (en) * 2006-10-31 2011-06-28 General Electric Company Turbofan engine assembly and method of assembling same
FR2918120B1 (en) * 2007-06-28 2009-10-02 Snecma Sa DOUBLE BLOWER TURBOMACHINE

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2430399A (en) * 1942-11-05 1947-11-04 Armstrong Siddeley Motors Ltd Jet augmenter for combustion turbine propulsion plants
US3861139A (en) * 1973-02-12 1975-01-21 Gen Electric Turbofan engine having counterrotating compressor and turbine elements and unique fan disposition
NL8303401A (en) * 1982-11-01 1984-06-01 Gen Electric DRIVE TURBINE FOR OPPOSITE ROTATING PROPELLERS.
FR2560642A1 (en) * 1984-03-02 1985-09-06 Gen Electric TURBOSOUFFLANTE MOTOR WITH COUNTER-ROTATION

Also Published As

Publication number Publication date
GB2194292A (en) 1988-03-02
IT1222557B (en) 1990-09-05
FR2603344A1 (en) 1988-03-04
SE8703304D0 (en) 1987-08-26
JPS63106335A (en) 1988-05-11
GB8713929D0 (en) 1987-07-22
IT8721741A0 (en) 1987-08-28
DE3728436A1 (en) 1988-03-03

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Legal Events

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NAV Patent application has lapsed

Ref document number: 8703304-9

Effective date: 19900504