GB737081A - Improvements relating to jet propulsion engines - Google Patents

Improvements relating to jet propulsion engines

Info

Publication number
GB737081A
GB737081A GB3165949A GB3165949A GB737081A GB 737081 A GB737081 A GB 737081A GB 3165949 A GB3165949 A GB 3165949A GB 3165949 A GB3165949 A GB 3165949A GB 737081 A GB737081 A GB 737081A
Authority
GB
United Kingdom
Prior art keywords
turbine
compressor
cone
exhaust nozzle
air
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
GB3165949A
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.)
DEVENDRA NATH SHARMA
Original Assignee
DEVENDRA NATH SHARMA
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 DEVENDRA NATH SHARMA filed Critical DEVENDRA NATH SHARMA
Priority to GB3165949A priority Critical patent/GB737081A/en
Publication of GB737081A publication Critical patent/GB737081A/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
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/16—Composite ram-jet/turbo-jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

737,081. Gas turbine plant. SHARMA, D. N. Dec. 11, 1950 [Dec. 9, 1949], No. 31659/49. Class 110 (3). A gas turbine jet propulsion engine with an axial flow compressor has the air discharged from the compressor divided into two paths leading directly to two sets of heat generating sources located at the periphery of the engine casing, the air from one path being led to a turbine which drives the compressor and the air from the other path by-passes the turbine and discharges into the exhaust nozzle. The gas turbine shown has an axial flow compressor 4, 11, the discharge of which feeds sets of combustion chamber 7, 7A located at the periphery of the engine casing. The set of combustion chambers 7 supply gas to the turbines 9, 10 and the set of combustion chambers 7A supply gas direct to the exhaust nozzle 24, by-passing the turbines 9, 10. The turbine 10 drives a propeller through the shaft 26. The compressor drum 21 has compressor blades 22 which compress air sucked through apertures 20 and discharge it over the bearings and the parts of the turbine 23 to the exhaust nozzle 24. Burners may be fitted at the positions marked X. When the combustion chambers 7A are in operation, the reaction cone 32 is retracted by means of an electric motor 29 acting through a shaft 14A and nut 27. The movement of the cone may be used to operate the fuel supply cocks to the combustion chamber 7A. The cone 32 may have extra burners located at the tip.
GB3165949A 1949-12-09 1949-12-09 Improvements relating to jet propulsion engines Expired GB737081A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB3165949A GB737081A (en) 1949-12-09 1949-12-09 Improvements relating to jet propulsion engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3165949A GB737081A (en) 1949-12-09 1949-12-09 Improvements relating to jet propulsion engines

Publications (1)

Publication Number Publication Date
GB737081A true GB737081A (en) 1955-09-21

Family

ID=10326469

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3165949A Expired GB737081A (en) 1949-12-09 1949-12-09 Improvements relating to jet propulsion engines

Country Status (1)

Country Link
GB (1) GB737081A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2389772A1 (en) * 1977-05-05 1978-12-01 Mordellet Roger Jet engine for subsonic aircraft - has hollow rotor with internal blades to produce secondary stream of air within annular primary stream
FR2605679A1 (en) * 1986-10-24 1988-04-29 Culica Georges Francois Multi-spool multi-bypass turbo jet engine with a drum rotor
FR2682719A1 (en) * 1991-10-16 1993-04-23 Snecma Engine for hypersonic vehicle with turbojet and ramjet operations
EP1469184A1 (en) * 1999-12-23 2004-10-20 Mathias Meyer Turbo jet engine
CN114426101A (en) * 2022-01-29 2022-05-03 中国航发湖南动力机械研究所 Cross-medium power device
CN114893319A (en) * 2022-04-29 2022-08-12 南京航空航天大学 Turbojet core machine nozzle structure

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2389772A1 (en) * 1977-05-05 1978-12-01 Mordellet Roger Jet engine for subsonic aircraft - has hollow rotor with internal blades to produce secondary stream of air within annular primary stream
FR2605679A1 (en) * 1986-10-24 1988-04-29 Culica Georges Francois Multi-spool multi-bypass turbo jet engine with a drum rotor
FR2682719A1 (en) * 1991-10-16 1993-04-23 Snecma Engine for hypersonic vehicle with turbojet and ramjet operations
US5284014A (en) * 1991-10-16 1994-02-08 Societe Nationale D'etude Et De Construction De Moteurs D'aviation ("S.N.E.C.M.A.") Turbojet-ramjet hypersonic aircraft engine
EP1469184A1 (en) * 1999-12-23 2004-10-20 Mathias Meyer Turbo jet engine
CN114426101A (en) * 2022-01-29 2022-05-03 中国航发湖南动力机械研究所 Cross-medium power device
CN114426101B (en) * 2022-01-29 2023-11-17 中国航发湖南动力机械研究所 Cross-medium power device
CN114893319A (en) * 2022-04-29 2022-08-12 南京航空航天大学 Turbojet core machine nozzle structure

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