GB989621A - Improvements in or relating to gas turbine aircraft engines - Google Patents

Improvements in or relating to gas turbine aircraft engines

Info

Publication number
GB989621A
GB989621A GB12721/61A GB1272161A GB989621A GB 989621 A GB989621 A GB 989621A GB 12721/61 A GB12721/61 A GB 12721/61A GB 1272161 A GB1272161 A GB 1272161A GB 989621 A GB989621 A GB 989621A
Authority
GB
United Kingdom
Prior art keywords
spark
choke
couplings
gas turbine
condenser
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
GB12721/61A
Inventor
Gordon Allan Halls
Leslie Barnes
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 GB12721/61A priority Critical patent/GB989621A/en
Priority to FR893198A priority patent/FR1319068A/en
Priority to DER32412A priority patent/DE1167595B/en
Publication of GB989621A publication Critical patent/GB989621A/en
Priority to US491476A priority patent/US3264825A/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
    • F02C7/264—Ignition
    • F02C7/266—Electric
    • 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)
  • Ignition Installations For Internal Combustion Engines (AREA)

Abstract

989,621. Gas turbine plant. ROLLS-ROYCE Ltd. April 3, 1962 [April 7, 1961], No. 12721/61. Heading F1G. [Also in Division F4] A combustion chamber for an aircraft gas turbine engine is provided with two spark igniters so that there is simultaneous operation of the igniters and the sparks produced are closely adjacent to or meet each other. Charging sources 26, 27 are each connected across a 24 volt D.C. supply and produce high voltage pulses. Choke couplings 31, 32 are connected to spark igniters 16, 17 by way of sealed spark gaps 35, 36 respectively. The spark gaps have trigger electrodes 37, 38 connected to the choke couplings 32, 31 respectively. If the condenser 33 is fully charged before the condenser 34, the spark gap will pass current to the igniter 16 and the current through the choke coupling 31 will trigger the spark gap 36 by the electrode 38 to pass current to the igniter 17. Alternatively the trigger electrodes may be replaced by third electrodes in the spark gaps or the choke couplings 31, 32 may be dispensed with and the lines 30, 30<SP>1</SP> coupled by chokes on a common core a transformer coupling or resistance coupling. Again, the choke couplings 31, 32 and the spark gaps 35, 36 may be replaced by a single common spark gap, whereby the discharge of one condenser would cause discharge of the other.
GB12721/61A 1961-04-07 1961-04-07 Improvements in or relating to gas turbine aircraft engines Expired GB989621A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB12721/61A GB989621A (en) 1961-04-07 1961-04-07 Improvements in or relating to gas turbine aircraft engines
FR893198A FR1319068A (en) 1961-04-07 1962-04-03 Combustion chamber of a gas turbo-engine
DER32412A DE1167595B (en) 1961-04-07 1962-04-03 Combustion chamber with two spark ignitors
US491476A US3264825A (en) 1961-04-07 1965-09-01 Gas turbine jet propulsion engine igniter

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB12721/61A GB989621A (en) 1961-04-07 1961-04-07 Improvements in or relating to gas turbine aircraft engines

Publications (1)

Publication Number Publication Date
GB989621A true GB989621A (en) 1965-04-22

Family

ID=10009884

Family Applications (1)

Application Number Title Priority Date Filing Date
GB12721/61A Expired GB989621A (en) 1961-04-07 1961-04-07 Improvements in or relating to gas turbine aircraft engines

Country Status (2)

Country Link
DE (1) DE1167595B (en)
GB (1) GB989621A (en)

Also Published As

Publication number Publication date
DE1167595B (en) 1964-04-09

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