GB935544A - Improvements in or relating to gas turbine jet propulsion engines - Google Patents

Improvements in or relating to gas turbine jet propulsion engines

Info

Publication number
GB935544A
GB935544A GB21181/60A GB2118160A GB935544A GB 935544 A GB935544 A GB 935544A GB 21181/60 A GB21181/60 A GB 21181/60A GB 2118160 A GB2118160 A GB 2118160A GB 935544 A GB935544 A GB 935544A
Authority
GB
United Kingdom
Prior art keywords
pass
gases
combustion chambers
combustion
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
GB21181/60A
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.)
KENNETH HAROLD GREAGER
Original Assignee
KENNETH HAROLD GREAGER
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 KENNETH HAROLD GREAGER filed Critical KENNETH HAROLD GREAGER
Publication of GB935544A publication Critical patent/GB935544A/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
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/105—Heating the by-pass flow
    • F02K3/11—Heating the by-pass flow by means of burners or combustion chambers
    • 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)
  • Supercharger (AREA)

Abstract

935,544. Jet propulsion plant. K. H. GREAGER. June 16, 1960 [June 28, 1959], No. 21181/60. Class 110 (3). In a gas turbine jet propulsion engine of the by-pass type, combustion equipment is disposed in the by-pass duct and valve means are provided to control the air supplied to the by-pass combustion equipment. The main combustion equipment, also the by-pass combustion equipment, are each of the kind comprising a plurality of combustion chambers or flame tubes. The engine shown in Fig. 1 comprises an air compressor 6, main combustion equipment 1 comprising a circumferential series of separate combustion chambers, and a turbine 8 driven by gases from the combustion equipment 1 and driving the air compressor 6. The exhaust gases from the turbine pass to the jet pipe 15. A portion of the air delivered by the compressor is by-passed through ducts 19 having control valves 18 and flows through combustion chambers 9 where fuel is burned in it, the resulting gases passing through outlets 14 and being guided by vanes 16 to intermix with the turbine exhaust gases in the jet pipe 15. In a second embodiment, Fig. 4, the by-pass combustion chambers 9 are disposed further downstream and the gases therefrom flow through an annular duct 22 disposed around the turbine exhaust duct 24; apertures 23 are provided in the wall of the duct 24. The by-pass combustion chambers 9 are connected to the main combustion chambers by pipes 17, whereby ignition of the gases in the chambers 9 may be effected.
GB21181/60A 1959-06-28 1960-06-16 Improvements in or relating to gas turbine jet propulsion engines Expired GB935544A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
ZW27259 1959-06-28

Publications (1)

Publication Number Publication Date
GB935544A true GB935544A (en) 1963-08-28

Family

ID=25590674

Family Applications (1)

Application Number Title Priority Date Filing Date
GB21181/60A Expired GB935544A (en) 1959-06-28 1960-06-16 Improvements in or relating to gas turbine jet propulsion engines

Country Status (1)

Country Link
GB (1) GB935544A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3352110A (en) * 1967-11-14 Cresswell gas turbine by-pass engine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3352110A (en) * 1967-11-14 Cresswell gas turbine by-pass engine

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