GB701121A - Improvements relating to gas turbine engine starter systems - Google Patents

Improvements relating to gas turbine engine starter systems

Info

Publication number
GB701121A
GB701121A GB834151A GB834151A GB701121A GB 701121 A GB701121 A GB 701121A GB 834151 A GB834151 A GB 834151A GB 834151 A GB834151 A GB 834151A GB 701121 A GB701121 A GB 701121A
Authority
GB
United Kingdom
Prior art keywords
rotor assembly
electrical machine
speed
generator
turbine
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
GB834151A
Inventor
Harold Edward William West
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 GB834151A priority Critical patent/GB701121A/en
Publication of GB701121A publication Critical patent/GB701121A/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
    • F02C7/26—Starting; Ignition
    • F02C7/262—Restarting after flame-out
    • 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
    • F02C7/26—Starting; Ignition
    • F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
    • F02C7/275—Mechanical drives

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Eletrric Generators (AREA)
  • Dc Machiner (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)

Abstract

701,121. Cas turbine plant. ROLLS-ROYCE, Ltd. June 19, 1952 [April 10, 1951], No. 8341/51. Class 110 (3). [Also in Group XXVIII An aircraft gas turbine starting system comprises a starter motor arranged to drive a turbinecompressor rotor assembly of the engine in starting under normal ground conditions and an electrical machine adapted to act as a starter motor in flight and as a generator when the engine has started. The compressor-turbine rotor assembly 10a, 13, 12a is started on the ground by starting mechanism comprising a cartridge firing device 15 and a combined turbine and reduction gear unit 16. The clutch mechanism 17 automatically disengages when the engine becomes self-driving. This starting mechanism is arranged to rotate the rotor assembly to a speed, say 3,000 r.p.m. which will be sufficient to allow the unit to become self-driving on the ground. Since at altitude, this rotational speed in not sufficient, an electrical machine 18 which may operate either as a motor or generator is provided. The electrical machine is geared to the rotor assembly 10a, 13, 12a, through gearing 19, 20 which has a ration of 1 : 1 and drives the rotor assembly at high speed, say 5,000 to 6,000 r.p.m. The machine 18 which has a shunt winding 18a and a carbon pile regulator 18b, is connected to the aircraft battery 21 and the load 24 through switches 23, 25 and a reverse current cut-out device 22. The arrangement is such that the electrical machine 18 acts as a motor below a predetermined speed and above that speed as a generator.
GB834151A 1951-04-10 1951-04-10 Improvements relating to gas turbine engine starter systems Expired GB701121A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB834151A GB701121A (en) 1951-04-10 1951-04-10 Improvements relating to gas turbine engine starter systems

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB834151A GB701121A (en) 1951-04-10 1951-04-10 Improvements relating to gas turbine engine starter systems

Publications (1)

Publication Number Publication Date
GB701121A true GB701121A (en) 1953-12-16

Family

ID=9850682

Family Applications (1)

Application Number Title Priority Date Filing Date
GB834151A Expired GB701121A (en) 1951-04-10 1951-04-10 Improvements relating to gas turbine engine starter systems

Country Status (1)

Country Link
GB (1) GB701121A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2260577A (en) * 1991-10-16 1993-04-21 Rolls Royce Plc Gas turbine engine starting

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2260577A (en) * 1991-10-16 1993-04-21 Rolls Royce Plc Gas turbine engine starting
US5253470A (en) * 1991-10-16 1993-10-19 Rolls-Royce Plc Gas turbine engine starting
GB2260577B (en) * 1991-10-16 1994-10-05 Rolls Royce Plc Gas turbine engine starting

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