GB706841A - Improvements relating to turbine jet propulsion power units - Google Patents

Improvements relating to turbine jet propulsion power units

Info

Publication number
GB706841A
GB706841A GB1923848A GB1923848A GB706841A GB 706841 A GB706841 A GB 706841A GB 1923848 A GB1923848 A GB 1923848A GB 1923848 A GB1923848 A GB 1923848A GB 706841 A GB706841 A GB 706841A
Authority
GB
United Kingdom
Prior art keywords
turbine
blades
compressor
feed tube
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
GB1923848A
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 GB1923848A priority Critical patent/GB706841A/en
Publication of GB706841A publication Critical patent/GB706841A/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
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/077—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • 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
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

706,841. Gas turbine jet propulsion plant. SHARMA, D. N. July 16, 1949 [July 17, 1948], No. 19238/48. Class 110(3) A gas turbine jet propulsion plant has two coaxially arranged air paths leading to a common axial jet exhaust, the outer path leading from a compressor and burners to said exhaust, and the inner path, which is a central path along the axis of the turbine, including burners which lie in said path. The gas turbine plant shown comprises a central feed tube 115 axially disposed with respect to the casing 117. A compressor rotor 118 supported on bearings 119, 120, 121 and mounted between the tube 115 and casing 117 carries inwardly directed blades 122 and outwardly extending blades 123 which co-operate with stator blades 124, 125 carried by the tube 115 and casing 117 respectively. The rotor 118 also drives a propeller 135 through gearing 126. 127, 130, 132. Compressed air from the compressor passes through apertures 136 to a combustion chamber 137 in which liquid or gaseous fuel supplied through conduits 139 is burnt. The hot gases leaving the combustion chamber 137 are mixed in the space 142 with air from the feed tube 115 delivered through apertures 143, 144, before they are used to drive the turbine blades, 145. 146. The exhaust gases from the turbine pass through the pipe 149 and are controlled by vanes 150. 151, 152 and 153. The area 154 adjacent the rear of the feed tube 118 contains a number of additional burners (not shown). The turbine end of the rotor 118 is supported from the feed tube 115 by bearings 147. The two tiers of compressor blades may be arranged in series or in parallel. It is also stated that the plant may employ atomic energy as a source of heat.
GB1923848A 1948-07-17 1948-07-17 Improvements relating to turbine jet propulsion power units Expired GB706841A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1923848A GB706841A (en) 1948-07-17 1948-07-17 Improvements relating to turbine jet propulsion power units

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1923848A GB706841A (en) 1948-07-17 1948-07-17 Improvements relating to turbine jet propulsion power units

Publications (1)

Publication Number Publication Date
GB706841A true GB706841A (en) 1954-04-07

Family

ID=10126004

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1923848A Expired GB706841A (en) 1948-07-17 1948-07-17 Improvements relating to turbine jet propulsion power units

Country Status (1)

Country Link
GB (1) GB706841A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3289946A (en) * 1963-08-07 1966-12-06 Gen Electric Annular convergent-divergent exhaust nozzle
DE1233210B (en) * 1963-09-27 1967-01-26 Christian Hoefer Gas turbine jet engine
GB2289504A (en) * 1994-05-11 1995-11-22 British Aerospace Gas turbine propulsion unit
WO2001048365A1 (en) * 1999-12-23 2001-07-05 Mathias Meyer Turbojet engine
CN102374069A (en) * 2010-06-21 2012-03-14 靳北彪 Hot-stamping engine

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3289946A (en) * 1963-08-07 1966-12-06 Gen Electric Annular convergent-divergent exhaust nozzle
DE1233210B (en) * 1963-09-27 1967-01-26 Christian Hoefer Gas turbine jet engine
GB2289504A (en) * 1994-05-11 1995-11-22 British Aerospace Gas turbine propulsion unit
GB2289504B (en) * 1994-05-11 1998-01-14 British Aerospace Gas turbine propulsion unit
WO2001048365A1 (en) * 1999-12-23 2001-07-05 Mathias Meyer Turbojet engine
EP1469184A1 (en) * 1999-12-23 2004-10-20 Mathias Meyer Turbo jet engine
CN102374069A (en) * 2010-06-21 2012-03-14 靳北彪 Hot-stamping engine

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