GB655871A - Improvements in or relating to internal combustion turbine power plants - Google Patents

Improvements in or relating to internal combustion turbine power plants

Info

Publication number
GB655871A
GB655871A GB1159/44A GB115944A GB655871A GB 655871 A GB655871 A GB 655871A GB 1159/44 A GB1159/44 A GB 1159/44A GB 115944 A GB115944 A GB 115944A GB 655871 A GB655871 A GB 655871A
Authority
GB
United Kingdom
Prior art keywords
shaft
blades
compressed
internal combustion
turbine power
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
GB1159/44A
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 GB1159/44A priority Critical patent/GB655871A/en
Publication of GB655871A publication Critical patent/GB655871A/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
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • 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
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

655,871. Gas turbine plant. SHARMA, D. N. April 24, 1948, No. 1159. '[Class 110(iii)] An internal combustion turbine power plant comprises a hollow cylindrical shaft 1, two multi-stage compressors 8, 10 associated with and surrounding said shaft which is coupled with a multi-stage turbine rotor 2, mounted on another shaft coaxially placed within the hollow shaft by means of compressor blades 3, the hollow shaft driving a propellor or shaft for traction purposes through gearing 11. The arrangement is such that part of the incoming cold air is first compressed by the blades 3 then used to cool the bearings 14 and finally compressed, before entering the combustion chambers 13, by the compressor 8. The remaining part of the incoming air is compressed by the blades 10 and supplied direct to the combustion chambers for cooling and combustion purposes. The turbine exhaust gases pass through the opening 4. The air entering through the shaft takes up heat from the rotating parts.
GB1159/44A 1948-04-24 1948-04-24 Improvements in or relating to internal combustion turbine power plants Expired GB655871A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1159/44A GB655871A (en) 1948-04-24 1948-04-24 Improvements in or relating to internal combustion turbine power plants

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1159/44A GB655871A (en) 1948-04-24 1948-04-24 Improvements in or relating to internal combustion turbine power plants

Publications (1)

Publication Number Publication Date
GB655871A true GB655871A (en) 1951-08-08

Family

ID=9717203

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1159/44A Expired GB655871A (en) 1948-04-24 1948-04-24 Improvements in or relating to internal combustion turbine power plants

Country Status (1)

Country Link
GB (1) GB655871A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2605679A1 (en) * 1986-10-24 1988-04-29 Culica Georges Francois Multi-spool multi-bypass turbo jet engine with a drum rotor
GB2289504A (en) * 1994-05-11 1995-11-22 British Aerospace Gas turbine propulsion unit

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2605679A1 (en) * 1986-10-24 1988-04-29 Culica Georges Francois Multi-spool multi-bypass turbo jet engine with a drum rotor
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

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