GB616481A - Improvements in or relating to ignition systems for gas turbines - Google Patents

Improvements in or relating to ignition systems for gas turbines

Info

Publication number
GB616481A
GB616481A GB2675446A GB2675446A GB616481A GB 616481 A GB616481 A GB 616481A GB 2675446 A GB2675446 A GB 2675446A GB 2675446 A GB2675446 A GB 2675446A GB 616481 A GB616481 A GB 616481A
Authority
GB
United Kingdom
Prior art keywords
air
cylinder
chamber
auxiliary
casing
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
GB2675446A
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.)
DONALD MCCOMBIE GRASSICK
Original Assignee
DONALD MCCOMBIE GRASSICK
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
Priority to BE488953D priority Critical patent/BE488953A/xx
Application filed by DONALD MCCOMBIE GRASSICK filed Critical DONALD MCCOMBIE GRASSICK
Priority to GB2675446A priority patent/GB616481A/en
Publication of GB616481A publication Critical patent/GB616481A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • F23R3/48—Flame tube interconnectors, e.g. cross-over tubes

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Abstract

616,481. Igniting burners. GRASSICK, D. M. Sept. 5, 1946, No. 26754. [Class 75 (iii)] [Also in Group XII] To facilitate ignition, the combustion chambers of a gas turbine are combined with auxiliary combustion chambers each of which comprises a casing housing an enclosure which discharges into the main combustion chamber. The enclosure surrounds a fuel jet and electrical ignition means for igniting the fuel and is supplied with air from the casing through a restricted passage. The auxiliary chamber Fig. 2, consists of a pair of co-axial cylinders 15, 16 separated by flanges 17. One end of the cylinder 16 is closed by a plate 18 in which is mounted a fuel atomising nozzle 20 and the other end is provided with a flange 22 by which the auxiliary chamber is mounted on the casing 10 of the main chamber. Air holes 25 in the cylinder 15 admit air to the space 27 between the cylinders from the space between the air casing 10 and the flame tube 13. Air holes 26 form a restricted passage through which the air flows from the space 27 to the interior of the enclosure or cylinder 16. The inner end of the cylinder 16 is tapered at 21 to increase the velocity of the combustion gases. A sparking plug 28 is used for igniting the fuel-air mixture in the cylinder 16. In a modification, the auxiliary chambers of two adjacent combustion chambers are connected together and used as a balance pipe between the chambers. The invention may be applied to re-heat combustion chambers and the auxiliary chamber may be mounted as a pilot chamber in the primary zone of the main chamber.
GB2675446A 1946-09-05 1946-09-05 Improvements in or relating to ignition systems for gas turbines Expired GB616481A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
BE488953D BE488953A (en) 1946-09-05
GB2675446A GB616481A (en) 1946-09-05 1946-09-05 Improvements in or relating to ignition systems for gas turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2675446A GB616481A (en) 1946-09-05 1946-09-05 Improvements in or relating to ignition systems for gas turbines

Publications (1)

Publication Number Publication Date
GB616481A true GB616481A (en) 1949-01-21

Family

ID=10248685

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2675446A Expired GB616481A (en) 1946-09-05 1946-09-05 Improvements in or relating to ignition systems for gas turbines

Country Status (2)

Country Link
BE (1) BE488953A (en)
GB (1) GB616481A (en)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2810261A (en) * 1952-10-15 1957-10-22 Plessey Co Ltd Combustion control system
US2847826A (en) * 1952-09-10 1958-08-19 Ca Nat Research Council Pulsating torch igniter
US2929210A (en) * 1957-12-27 1960-03-22 Garrett Corp Pulsating ignition torch means
US2967224A (en) * 1956-10-08 1961-01-03 Ford Motor Co Hot wire igniter
US3035413A (en) * 1950-01-17 1962-05-22 Linderoth Erik Torvald Thermodynamic combustion device using pulsating gas pressure
US3106059A (en) * 1961-03-30 1963-10-08 United Aircraft Corp Oxidizer inlet and igniter for a rocket
EP0026595A1 (en) * 1979-09-28 1981-04-08 General Motors Corporation Automotive gas turbine engine
GB2443839A (en) * 2006-11-17 2008-05-21 Siemens Ag Interconnected Combustion Chambers
EP2136587A2 (en) 2006-08-18 2009-12-23 Fujitsu Limited communication systems
EP2527739A3 (en) * 2011-05-24 2013-09-18 General Electric Company System and method for flow control in gas turbine engine

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3035413A (en) * 1950-01-17 1962-05-22 Linderoth Erik Torvald Thermodynamic combustion device using pulsating gas pressure
US2847826A (en) * 1952-09-10 1958-08-19 Ca Nat Research Council Pulsating torch igniter
US2810261A (en) * 1952-10-15 1957-10-22 Plessey Co Ltd Combustion control system
US2967224A (en) * 1956-10-08 1961-01-03 Ford Motor Co Hot wire igniter
US2929210A (en) * 1957-12-27 1960-03-22 Garrett Corp Pulsating ignition torch means
US3106059A (en) * 1961-03-30 1963-10-08 United Aircraft Corp Oxidizer inlet and igniter for a rocket
EP0026595A1 (en) * 1979-09-28 1981-04-08 General Motors Corporation Automotive gas turbine engine
EP2136587A2 (en) 2006-08-18 2009-12-23 Fujitsu Limited communication systems
GB2443839A (en) * 2006-11-17 2008-05-21 Siemens Ag Interconnected Combustion Chambers
EP2527739A3 (en) * 2011-05-24 2013-09-18 General Electric Company System and method for flow control in gas turbine engine
US8919127B2 (en) 2011-05-24 2014-12-30 General Electric Company System and method for flow control in gas turbine engine

Also Published As

Publication number Publication date
BE488953A (en)

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