FR2455179A1 - SYSTEM FOR HANDLING AN ELEMENT MOUNTED WITHIN A CRANKCASE - Google Patents

SYSTEM FOR HANDLING AN ELEMENT MOUNTED WITHIN A CRANKCASE

Info

Publication number
FR2455179A1
FR2455179A1 FR8009089A FR8009089A FR2455179A1 FR 2455179 A1 FR2455179 A1 FR 2455179A1 FR 8009089 A FR8009089 A FR 8009089A FR 8009089 A FR8009089 A FR 8009089A FR 2455179 A1 FR2455179 A1 FR 2455179A1
Authority
FR
France
Prior art keywords
swivel
organs
partial rotation
crankcase
annular
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.)
Granted
Application number
FR8009089A
Other languages
French (fr)
Other versions
FR2455179B1 (en
Inventor
Dudley Owen Nash
Thomas Simmons Clayton
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 FR2455179A1 publication Critical patent/FR2455179A1/en
Application granted granted Critical
Publication of FR2455179B1 publication Critical patent/FR2455179B1/fr
Granted legal-status Critical Current

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
    • F02K3/075—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 controlling flow ratio between flows
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Toys (AREA)

Abstract

SYSTEME DE POIDS ET DE COMPLEXITE REDUITS. IL COMPREND PLUSIEURS ORGANES PIVOTANTS 40 QUI TRAVERSENT CE CARTER ET TRANSMETTENT UN MOUVEMENT DE ROTATION; UN DISPOSITIF DE MANOEUVRE 50 QUI FAIT TOURNER UN OU PLUSIEURS DE CES ORGANES PIVOTANTS; UN AGENCEMENT QUI PROVOQUE LA ROTATION PARTIELLE SYNCHRONE DE CES ORGANES PIVOTANTS LORS DE LA ROTATION PARTIELLE DE L'UN D'ENTRE EUX, CET AGENCEMENT COMPRENANT: A)UN BRAS 64 PORTE PAR CHACUN DES ORGANES PIVOTANTS ET TOURNANT AVEC LUI; B)UN ELEMENT ANNULAIRE DE MANOEUVRE 60, MONTE CIRCULAIREMENT POUR AVOIR UNE ROTATION PARTIELLE AUTOUR D'AU MOINS UNE PARTIE DU CARTER; ET C)UNE BIELLETTE 62 CORRESPONDANT A CHACUN DES BRAS, CES BIELLETTES AYANT UNE EXTREMITE 68 FIXEE DE FACON PIVOTANTE A UN BRAS ET L'AUTRE L'EXTREMITE 66 FIXEE DE FACON PIVOTANTE A L'ELEMENT ANNULAIRE DE MANOEUVRE; ET UN MOYEN 44, 46, QUI RELIE CHACUN DES ORGANES PIVOTANTS A L'ELEMENT COULISSANT ET PROVOQUE LE COULISSEMENT DE CET ELEMENT LORS DE LA ROTATION DE CES ORGANES PIVOTANTS. APPLICATION AUX MOTEURS A TURBINE A GAZ.REDUCED WEIGHT AND COMPLEXITY SYSTEM. IT CONSISTS OF SEVERAL SWIVEL ORGANS 40 WHICH CROSS THIS CASE AND TRANSMIT A ROTATIONAL MOVEMENT; A MANEUVERING DEVICE 50 WHICH ROTATES ONE OR MORE OF THESE SWIVEL PARTS; AN ARRANGEMENT WHICH CAUSES THE SYNCHRONOUS PARTIAL ROTATION OF THESE SWIVEL ORGANS DURING THE PARTIAL ROTATION OF ONE OF THEM, THIS ARRANGEMENT CONSISTING OF: A) AN ARM 64 CARRIED BY EACH OF THE SWIVEL ORGANS AND TURNING WITH IT; B) AN ANNULAR MANEUVER 60 ELEMENT, MOUNTED CIRCULARLY TO HAVE A PARTIAL ROTATION AROUND AT LEAST PART OF THE CRANKCASE; AND C) A LINK 62 CORRESPONDING TO EACH OF THE ARMS, THESE LINKS HAVING AN END 68 FIXED IN A PIVOT WAY TO ONE ARM AND THE OTHER THE END 66 FIXED IN A PIVOTING WAY TO THE ANNULAR MANEUVER ELEMENT; AND A MEANS 44, 46, WHICH CONNECTS EACH OF THE SWIVEL ORGANS TO THE SLIDING ELEMENT AND CAUSES THE SLIDING OF THIS ELEMENT DURING THE ROTATION OF THESE SWIVEL PARTS. APPLICATION TO GAS TURBINE ENGINES.

FR8009089A 1979-04-23 1980-04-23 SYSTEM FOR HANDLING AN ELEMENT MOUNTED WITHIN A CRANKCASE Granted FR2455179A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US3233079A 1979-04-23 1979-04-23

Publications (2)

Publication Number Publication Date
FR2455179A1 true FR2455179A1 (en) 1980-11-21
FR2455179B1 FR2455179B1 (en) 1984-07-20

Family

ID=21864363

Family Applications (1)

Application Number Title Priority Date Filing Date
FR8009089A Granted FR2455179A1 (en) 1979-04-23 1980-04-23 SYSTEM FOR HANDLING AN ELEMENT MOUNTED WITHIN A CRANKCASE

Country Status (6)

Country Link
JP (1) JPS55142937A (en)
DE (1) DE3015119A1 (en)
FR (1) FR2455179A1 (en)
GB (1) GB2047815B (en)
IL (1) IL59497A (en)
IT (1) IT1131033B (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2527688A1 (en) * 1982-06-01 1983-12-02 Gen Electric Actuator for gas turbine engine - has external actuator rotating crank with yoke linked to annular slide in engine
FR2926328A1 (en) * 2008-01-14 2009-07-17 Snecma Sa Ducted-fan turbine engine i.e. aircraft turbofan, has slat located in downstream side of discharge passage with respect to flow direction of gas stream, where slat is movable to outlet position in which slat projects inside primary channel

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS58200038A (en) * 1982-05-18 1983-11-21 ゼネラル・エレクトリツク・カンパニイ Actuator for gas turbine engine
US5417055A (en) * 1988-06-28 1995-05-23 Rolls-Royce Plc Valve for diverting fluid flows in turbomachines
GB8815292D0 (en) * 1988-06-28 1994-10-26 Rolls Royce Plc Valve for diverting fluid flows in turbomachines
DE3911715A1 (en) * 1989-04-10 1990-10-11 Mtu Muenchen Gmbh SHUT-OFF DEVICE FOR BLOWED, IN PARTICULAR BLOWED, RADIANT JET ENGINES
DE4004416C2 (en) * 1990-02-13 1993-10-14 Mtu Muenchen Gmbh Turbo ramjet with shut-off device for variable switching operation
US5123240A (en) * 1990-03-19 1992-06-23 General Electric Co. Method and apparatus for ejecting foreign matter from the primary flow path of a gas turbine engine
FR2664018B1 (en) * 1990-06-29 1993-08-13 Gen Electric BYPASS VALVE SYSTEM.
GB2259328B (en) * 1991-09-03 1995-07-19 Gen Electric Gas turbine engine variable bleed pivotal flow splitter
US5287697A (en) * 1992-01-02 1994-02-22 General Electric Company Variable area bypass injector seal
US6742324B2 (en) * 2002-09-13 2004-06-01 General Electric Company Methods and apparatus for supporting variable bypass valve systems
US6901739B2 (en) * 2003-10-07 2005-06-07 General Electric Company Gas turbine engine with variable pressure ratio fan system
US20120070271A1 (en) 2010-09-21 2012-03-22 Urban Justin R Gas turbine engine with bleed duct for minimum reduction of bleed flow and minimum rejection of hail during hail ingestion events
US8935926B2 (en) 2010-10-28 2015-01-20 United Technologies Corporation Centrifugal compressor with bleed flow splitter for a gas turbine engine
DE102011101331A1 (en) * 2011-05-12 2012-11-15 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine engine with bleed air extraction device
CN109162829B (en) * 2018-09-04 2019-08-23 中国航发沈阳发动机研究所 The compressibility of variable cycle engine
CN111636978B (en) * 2020-06-16 2021-06-18 南京航空航天大学 Flow regulating mechanism suitable for turbine-based circulating combined engine

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2934895A (en) * 1958-09-15 1960-05-03 Curtiss Wright Corp Dual cycle engine distributor construction
US3060680A (en) * 1957-12-30 1962-10-30 Rolls Royce By-pass gas-turbine engine and control therefor
US3153904A (en) * 1961-12-29 1964-10-27 Stanley H Ellis Turbo-ramjet configuration
GB1124169A (en) * 1967-04-07 1968-08-21 Rolls Royce Mechanism e.g. for use in a jet nozzle
FR2088303A1 (en) * 1970-05-04 1972-01-07 Gen Electric
GB1300405A (en) * 1969-06-25 1972-12-20 Secr Defence Improvements in nozzles for gas turbine jet propulsion engines
GB1301615A (en) * 1970-04-23 1973-01-04
FR2399547A1 (en) * 1977-08-02 1979-03-02 Gen Electric MULTI-BYPASS VARIABLE CYCLE TURBO-BLOWER MOTOR

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB864519A (en) * 1958-08-05 1961-04-06 Rolls Royce Improved annular fluid control valve device
DE2247400C2 (en) * 1972-09-27 1975-01-16 Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Device for blowing off compressed air from a compressor of a gas turbine jet engine
DE2740904A1 (en) * 1977-09-10 1979-03-22 Motoren Turbinen Union DEVICE FOR OPERATING SHUT-OFF ELEMENTS IN GAS TURBINE ENGINES, IN PARTICULAR GAS TURBINE JET

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3060680A (en) * 1957-12-30 1962-10-30 Rolls Royce By-pass gas-turbine engine and control therefor
US2934895A (en) * 1958-09-15 1960-05-03 Curtiss Wright Corp Dual cycle engine distributor construction
US3153904A (en) * 1961-12-29 1964-10-27 Stanley H Ellis Turbo-ramjet configuration
GB1124169A (en) * 1967-04-07 1968-08-21 Rolls Royce Mechanism e.g. for use in a jet nozzle
GB1300405A (en) * 1969-06-25 1972-12-20 Secr Defence Improvements in nozzles for gas turbine jet propulsion engines
GB1301615A (en) * 1970-04-23 1973-01-04
FR2088303A1 (en) * 1970-05-04 1972-01-07 Gen Electric
FR2399547A1 (en) * 1977-08-02 1979-03-02 Gen Electric MULTI-BYPASS VARIABLE CYCLE TURBO-BLOWER MOTOR

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2527688A1 (en) * 1982-06-01 1983-12-02 Gen Electric Actuator for gas turbine engine - has external actuator rotating crank with yoke linked to annular slide in engine
FR2926328A1 (en) * 2008-01-14 2009-07-17 Snecma Sa Ducted-fan turbine engine i.e. aircraft turbofan, has slat located in downstream side of discharge passage with respect to flow direction of gas stream, where slat is movable to outlet position in which slat projects inside primary channel

Also Published As

Publication number Publication date
GB2047815A (en) 1980-12-03
IT8020837A0 (en) 1980-03-21
JPS642774B2 (en) 1989-01-18
IL59497A0 (en) 1980-05-30
FR2455179B1 (en) 1984-07-20
GB2047815B (en) 1983-03-30
DE3015119A1 (en) 1980-11-06
IL59497A (en) 1984-08-31
JPS55142937A (en) 1980-11-07
IT1131033B (en) 1986-06-18

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Legal Events

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ST Notification of lapse