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GB971690A - Gas turbine engine - Google Patents

Gas turbine engine

Info

Publication number
GB971690A
GB971690A GB3238763A GB3238763A GB971690A GB 971690 A GB971690 A GB 971690A GB 3238763 A GB3238763 A GB 3238763A GB 3238763 A GB3238763 A GB 3238763A GB 971690 A GB971690 A GB 971690A
Authority
GB
United Kingdom
Prior art keywords
shafting
gears
engine
low
pressure compressor
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
GB3238763A
Inventor
William John Davies
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB3238763A priority Critical patent/GB971690A/en
Publication of GB971690A publication Critical patent/GB971690A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • F02C7/00—Features, 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
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • 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
    • F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gear Transmission (AREA)

Abstract

971,690. Toothed gearing. ROLLS-ROYCE Ltd. Aug. 15, 1963, No. 32387/63. Heading F2Q. [Also in Division F1] The invention relates to a gas turbine engine of the type comprising a low-pressure compressor 11, a high-pressure compressor 12, combustion equipment 13, a high-pressure turbine 14 and a low-pressure turbine 15, the high-pressure turbine being connected to the high-pressure compressor by first shafting 16, the low-pressure turbine being connected to the low-pressure compressor by second shafting 17, the second shafting being disposed concentrically within the first shafting. A third shafting 22 is mounted within the second shafting and is adapted to be drivingly connected to engine auxiliary equipment, there being a drive transmission for transmitting drive from the first shafting to the third shafting or vice versa, the drive transmission passing through the second shafting. The drive transmission 24 shown in Figs. 1 and 2 is an epicyclic gearing comprising compound planet gears 25, 26 rotatably carried by a flange portion 23 of the second shafting 17 which constitutes a planet carrier, the gears 26 engaging with an internal ring gear 31 formed in the first shafting 16, and the gears 25 engaging with an internal ring gear 27 formed in the flange 30 of the third shafting 22. The shafting 22 in Fig. 1 is connected to drive rotary parts of a fuel supply control system 21 disposed within the fairing cone 20. In Fig. 1A, the shafting 22 is also connected by means of gearing 34, 35, 36 and a clutch 33 to an engine starter 32. In a further embodiment, Fig. 3, simple planet gears 34 are utilized, the gears being carried by a planet carrier portion 35 of the shafting 17 and engaging with an internal ring gear 31 formed in the shafting 16 and with a sun gear 36 formed on the shaft 22. The engine shown is a vertical lift engine having a thrust to weight ratio of at least 8: 1 and preferably 16: 1.
GB3238763A 1963-08-15 1963-08-15 Gas turbine engine Expired GB971690A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB3238763A GB971690A (en) 1963-08-15 1963-08-15 Gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3238763A GB971690A (en) 1963-08-15 1963-08-15 Gas turbine engine

Publications (1)

Publication Number Publication Date
GB971690A true GB971690A (en) 1964-09-30

Family

ID=10337822

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3238763A Expired GB971690A (en) 1963-08-15 1963-08-15 Gas turbine engine

Country Status (1)

Country Link
GB (1) GB971690A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1995002120A1 (en) * 1993-07-06 1995-01-19 Rolls-Royce Plc Shaft power transfer in gas turbine engines
FR2826052A1 (en) * 2001-06-19 2002-12-20 Snecma Moteurs Emergency device for relighting turbojet in airplane, has braking system to slowdown or block differential having annular gear rotating about coaxial shafts when turbojet shuts down
FR2863312A1 (en) * 2003-12-09 2005-06-10 Snecma Moteurs Twin-spool turbine for aircraft, has electrical generators driven through differential gear having two planet wheels driven by high and low pressure rotor shafts of high and low pressure bodies, and planet gear driven by wheels

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1995002120A1 (en) * 1993-07-06 1995-01-19 Rolls-Royce Plc Shaft power transfer in gas turbine engines
US5694765A (en) * 1993-07-06 1997-12-09 Rolls-Royce Plc Shaft power transfer in gas turbine engines with machines operable as generators or motors
FR2826052A1 (en) * 2001-06-19 2002-12-20 Snecma Moteurs Emergency device for relighting turbojet in airplane, has braking system to slowdown or block differential having annular gear rotating about coaxial shafts when turbojet shuts down
EP1270903A1 (en) * 2001-06-19 2003-01-02 Snecma Moteurs Safety device for restarting windmilling turbojet
US6672049B2 (en) 2001-06-19 2004-01-06 Snecma Moteurs Emergency device for relighting a windmilling turbojet
FR2863312A1 (en) * 2003-12-09 2005-06-10 Snecma Moteurs Twin-spool turbine for aircraft, has electrical generators driven through differential gear having two planet wheels driven by high and low pressure rotor shafts of high and low pressure bodies, and planet gear driven by wheels
EP1541834A1 (en) * 2003-12-09 2005-06-15 Snecma Moteurs Power take-off for the accessories of a twin spool turbo-jet engine
US7168913B2 (en) 2003-12-09 2007-01-30 Snecma Moteurs Twin-spool turbojet with means for driving ancillary machines

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