GB670309A - Improvements in or relating to a starter device for high speed internal combustion engines - Google Patents

Improvements in or relating to a starter device for high speed internal combustion engines

Info

Publication number
GB670309A
GB670309A GB30246/49A GB3024649A GB670309A GB 670309 A GB670309 A GB 670309A GB 30246/49 A GB30246/49 A GB 30246/49A GB 3024649 A GB3024649 A GB 3024649A GB 670309 A GB670309 A GB 670309A
Authority
GB
United Kingdom
Prior art keywords
gear
engine
turbine
shaft
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
GB30246/49A
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.)
Garrett Corp
Original Assignee
Garrett 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 Garrett Corp filed Critical Garrett Corp
Publication of GB670309A publication Critical patent/GB670309A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00Features, 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
    • F02C7/26Starting; Ignition
    • F02C7/268Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
    • F02C7/275Mechanical drives
    • F02C7/277Mechanical drives the starter being a separate turbine
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/60Efficient 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)
  • Supercharger (AREA)

Abstract

670,309. Turning-gear. GARRETT CORPORATION. Nov. 25, 1949 [June 25, 1949] No. 30246/49. Class 7(v) In a starter device for high-speed internal combustion engines having a shaft 121, Fig. 1, and comprising a housing 22 adapted to be detachably connected to the engine 15, a drive shaft 100 rotatably supported in the housing 22 and adapted to be operatively connected to the engine shaft 121, a turbine in the housing 22 having an air driven wheel 55, and transmission means, such as sun and planetary gearing 53, 79 and 81, friction rings 88 and 97, driving element 40 and pawl and ratchet coupling 112, interconnecting the wheel 55 and the drive shaft 100, the transmission is adapted to partially or completely interrupt the transmission of power to the.drive shaft 100 in response to the occurence of an overload condition. Compressed air enters a scroll 68 and flows through tangential nozzles having nozzle openings 66 formed by inclined blades or partitions 67 to impinge upon the blades of the turbine wheel 55, the air then discharging axially through a passage 70 in which .is a screen 71. Rotation of turbine shaft 52 which has the sun gear 53 secured thereto is transmitted to the compound planetary gear 79 and 81, the part 81 meshing with gear 53 and part 79 meshing with a ring gear 85 that is engaged on opposite side faces by the friction rings 88 and 97, the former being secured to the casing and the latter to a ring 91 which is joined. by pins 94 to another ring 92, a spring 98 surrounding each pin and serving to load the friction rings. The ring gear 85 is held stationary so that the planetary gears 79, .81 travel round the gear 85 to rotate the driving element 40 at a speed slower than that of the turbine. Upon a predetermined load being exceeded the gear 85 overcomes the frictional resistance of the rings 88 and 97 and revolves whilst the planetary gears merely rotate on their own axes. The driving element 40 is coupled by a cross pin 45 to a driving member 46 which is in turn connected by the pawl and ratchet coupling 112 to the splined driving shaft 100 that engages the engine to be started. When the engine reaches operating speed sufficient torque and centrifugal force are imposed upon the spring-loaded coupling pawls 111 to cause them to pivot out of engagement with the ratchet and disconnect the drive to the engine, whereupon the starter is stopped. The starter may be permanently fixed to the engine or removed therefrom as soon as the engine has started. The compressed air is supplied by an auxiliary unit 20, Fig. 8, comprising a compressor 126, part of the output from which is led through pipes 135 past valves 140, 141, which control the air flow to either one or both of the starters 17 and 18, attached to engines 15 and 16, respectively. Part of the air may be diverted for other services whilst the remainder is directed through auxiliary combustion chambers 128 to enter the scroll of turbine 125 which drives the compressor.
GB30246/49A 1949-06-25 1949-11-25 Improvements in or relating to a starter device for high speed internal combustion engines Expired GB670309A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US670309XA 1949-06-25 1949-06-25

Publications (1)

Publication Number Publication Date
GB670309A true GB670309A (en) 1952-04-16

Family

ID=22073276

Family Applications (1)

Application Number Title Priority Date Filing Date
GB30246/49A Expired GB670309A (en) 1949-06-25 1949-11-25 Improvements in or relating to a starter device for high speed internal combustion engines

Country Status (1)

Country Link
GB (1) GB670309A (en)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1076998B (en) * 1952-07-05 1960-03-03 United Aircraft Corp Turning coupling on turning devices for internal combustion engines
US2968923A (en) * 1955-05-06 1961-01-24 North American Aviation Inc Mobile starter for jet aircraft engines
DE1101862B (en) * 1955-10-24 1961-03-09 Bendix Corp Coupling for turning devices of internal combustion engines
US2994194A (en) * 1958-12-05 1961-08-01 Bendix Corp Starting system having a gas generator
US3046741A (en) * 1958-12-08 1962-07-31 Bendix Corp Starting system having a gas generator
EP0189875A1 (en) * 1985-01-26 1986-08-06 Klöckner-Humboldt-Deutz Aktiengesellschaft Auxiliary power system for a gas turbine engine
GB2178797A (en) * 1985-08-03 1987-02-18 Malcolm David Allcard Cold starting of diesel engines
EP0343412A1 (en) * 1988-05-24 1989-11-29 AlliedSignal Inc. Turbine starter device
WO2005042948A2 (en) * 2003-09-12 2005-05-12 Honeywell International Inc. Air turbine starter with unitary inlet and stator
US6991425B2 (en) 2003-09-12 2006-01-31 Honeywell International, Inc. Air turbine starter with unitary inlet and stator

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1076998B (en) * 1952-07-05 1960-03-03 United Aircraft Corp Turning coupling on turning devices for internal combustion engines
US2968923A (en) * 1955-05-06 1961-01-24 North American Aviation Inc Mobile starter for jet aircraft engines
DE1101862B (en) * 1955-10-24 1961-03-09 Bendix Corp Coupling for turning devices of internal combustion engines
US2994194A (en) * 1958-12-05 1961-08-01 Bendix Corp Starting system having a gas generator
US3046741A (en) * 1958-12-08 1962-07-31 Bendix Corp Starting system having a gas generator
EP0189875A1 (en) * 1985-01-26 1986-08-06 Klöckner-Humboldt-Deutz Aktiengesellschaft Auxiliary power system for a gas turbine engine
GB2178797A (en) * 1985-08-03 1987-02-18 Malcolm David Allcard Cold starting of diesel engines
EP0343412A1 (en) * 1988-05-24 1989-11-29 AlliedSignal Inc. Turbine starter device
WO2005042948A2 (en) * 2003-09-12 2005-05-12 Honeywell International Inc. Air turbine starter with unitary inlet and stator
WO2005042948A3 (en) * 2003-09-12 2005-06-23 Honeywell Int Inc Air turbine starter with unitary inlet and stator
US6991425B2 (en) 2003-09-12 2006-01-31 Honeywell International, Inc. Air turbine starter with unitary inlet and stator

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