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GB693932A - Improvements in liquid fuel supply systems for continuous combustion turbine engines - Google Patents

Improvements in liquid fuel supply systems for continuous combustion turbine engines

Info

Publication number
GB693932A
GB693932A GB36951A GB36951A GB693932A GB 693932 A GB693932 A GB 693932A GB 36951 A GB36951 A GB 36951A GB 36951 A GB36951 A GB 36951A GB 693932 A GB693932 A GB 693932A
Authority
GB
United Kingdom
Prior art keywords
conduit
fuel
pump
tube
liquid fuel
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
GB36951A
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.)
Dowty Equipment Ltd
Original Assignee
Dowty Equipment Ltd
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 Dowty Equipment Ltd filed Critical Dowty Equipment Ltd
Priority to GB36951A priority Critical patent/GB693932A/en
Publication of GB693932A publication Critical patent/GB693932A/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
    • F02C7/22—Fuel supply systems
    • 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
    • F02C7/22—Fuel supply systems
    • F02C7/228—Dividing fuel between various burners

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Feeding And Controlling Fuel (AREA)

Abstract

693,932. Supplying liquid fuel to vapour burners. DOWTY EQUIPMENT, Ltd., CAREY, F. H., and SIMMONS, H. C. Jan. 4, 1952 [Jan. 4, 1951], No. 369/51. Class 75 (i) In a liquid fuel supply system for a continuous combustion turbine engine of the type in which fuel is vaporized before entering the combustion chamber, the fuel is fed through a supply conduit 12, Fig 1, connected to each of a plurality of tubes 17, projecting each into a vaporizing tube (not shown), through a circular-section swirl chamber 19, Fig. 3, having one or more tangential inlets 20, a delivery orifice 21 connecting with the tube 17 and a spill orifice 24 leading to a common return conduit 14. The spill orifice 24 is preferably annular and communicates with the conduit 14 through a diffusing chamber 25, ports 26, and a perforated tube 27. The flow through the tube 17 is adjusted by regulating the resistance to the return flow. Fuel may be delivered to the conduit 12 by a single pump, and the return conduit 14 may lead back to the supply tank or to the inlet side of the pump. Alternatively two pumps may be provided, one pump circulating fuel through the conduit 12, the swirl chambers, and the return conduit 14, whilst the other pump, feeds fuel into the circulating- flow preferably at the inlet of the circulating pump.
GB36951A 1951-01-04 1951-01-04 Improvements in liquid fuel supply systems for continuous combustion turbine engines Expired GB693932A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB36951A GB693932A (en) 1951-01-04 1951-01-04 Improvements in liquid fuel supply systems for continuous combustion turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB36951A GB693932A (en) 1951-01-04 1951-01-04 Improvements in liquid fuel supply systems for continuous combustion turbine engines

Publications (1)

Publication Number Publication Date
GB693932A true GB693932A (en) 1953-07-08

Family

ID=9703194

Family Applications (1)

Application Number Title Priority Date Filing Date
GB36951A Expired GB693932A (en) 1951-01-04 1951-01-04 Improvements in liquid fuel supply systems for continuous combustion turbine engines

Country Status (1)

Country Link
GB (1) GB693932A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3213523A (en) * 1961-03-24 1965-10-26 Nord Aviation Method of making a multiple injection manifold device
WO2009078891A2 (en) * 2007-09-14 2009-06-25 Siemens Energy, Inc. Secondary fuel delivery system

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3213523A (en) * 1961-03-24 1965-10-26 Nord Aviation Method of making a multiple injection manifold device
WO2009078891A2 (en) * 2007-09-14 2009-06-25 Siemens Energy, Inc. Secondary fuel delivery system
WO2009078891A3 (en) * 2007-09-14 2010-04-15 Siemens Energy, Inc. Secondary fuel delivery system

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