GB670736A - 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
GB670736A
GB670736A GB1798049A GB1798049A GB670736A GB 670736 A GB670736 A GB 670736A GB 1798049 A GB1798049 A GB 1798049A GB 1798049 A GB1798049 A GB 1798049A GB 670736 A GB670736 A GB 670736A
Authority
GB
United Kingdom
Prior art keywords
assemblies
compressor
inlet
passages
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
GB1798049A
Inventor
Herbert Sammons
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.)
Napier Turbochargers Ltd
Original Assignee
D Napier and Son 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 D Napier and Son Ltd filed Critical D Napier and Son Ltd
Priority to GB1798049A priority Critical patent/GB670736A/en
Publication of GB670736A publication Critical patent/GB670736A/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
    • F02K3/12—Plants including a gas turbine driving a compressor or a ducted fan characterised by having more than one gas turbine
    • 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
    • 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
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)

Abstract

670,736. Jet propulsion plant. NAPIER & SON, Ltd., D. June 29, 1950 [July 7, 1949], No. 17980/49. Class 110(iii) [Also in Groups XXIV and XXXIII] A turbo-jet comprises three independently operable I.C. turbine assemblies B, C, D which are arranged with their axes on the apices of an isosceles triangle, preferably one having the base larger than the sides, and each assembly comprises a rotary air compressor which receives air direct from the atmosphere through an inlet passage, a turbine which is co-axial with the compressor and one or more combustion chambers therebetween. The assemblies may have a common nozzle, separate nozzles or a nozzle which is subdivided by partitions and one or more exhaust reheaters may be used therein. Each compressor has a separate inlet or, as shown, an inlet which is divided into two passages E<SP>1</SP>, E<SP>2</SP> which merge into three inlets. Auxiliaries positioned in the space bounded by the assemblies, are driven through a differential gearing (see Group XXIV). A cockpit is arranged in the space F bounded by the passages E<SP>1</SP>, E<SP>2</SP>. Specification 593,403 is referred to.
GB1798049A 1949-07-07 1949-07-07 Improvements in or relating to internal combustion turbine power plants Expired GB670736A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1798049A GB670736A (en) 1949-07-07 1949-07-07 Improvements in or relating to internal combustion turbine power plants

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1798049A GB670736A (en) 1949-07-07 1949-07-07 Improvements in or relating to internal combustion turbine power plants

Publications (1)

Publication Number Publication Date
GB670736A true GB670736A (en) 1952-04-23

Family

ID=10104564

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1798049A Expired GB670736A (en) 1949-07-07 1949-07-07 Improvements in or relating to internal combustion turbine power plants

Country Status (1)

Country Link
GB (1) GB670736A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1022912B (en) * 1953-04-08 1958-01-16 Schmidt Paul Airplane with a tubular recoil drive that works periodically and with shock wave ignition
DE1129380B (en) * 1959-09-17 1962-05-10 Hamburger Flugzeugbau G M B H Propulsion unit with several jet engines
EP0147351A1 (en) * 1983-12-05 1985-07-03 United Technologies Corporation Bearing support structure
JP2008106742A (en) * 2006-10-13 2008-05-08 Snecma Turbojet engine auxiliary machine gear box drive shaft, and modular additional auxiliary machine

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1022912B (en) * 1953-04-08 1958-01-16 Schmidt Paul Airplane with a tubular recoil drive that works periodically and with shock wave ignition
DE1129380B (en) * 1959-09-17 1962-05-10 Hamburger Flugzeugbau G M B H Propulsion unit with several jet engines
EP0147351A1 (en) * 1983-12-05 1985-07-03 United Technologies Corporation Bearing support structure
JP2008106742A (en) * 2006-10-13 2008-05-08 Snecma Turbojet engine auxiliary machine gear box drive shaft, and modular additional auxiliary machine

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