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GB1275062A - Gas turbine fan engine - Google Patents

Gas turbine fan engine

Info

Publication number
GB1275062A
GB1275062A GB3318868A GB3318868A GB1275062A GB 1275062 A GB1275062 A GB 1275062A GB 3318868 A GB3318868 A GB 3318868A GB 3318868 A GB3318868 A GB 3318868A GB 1275062 A GB1275062 A GB 1275062A
Authority
GB
United Kingdom
Prior art keywords
compressor
turbine
compressors
fan
blading
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
GB3318868A
Inventor
Geoffrey Light Wilde
James Alexander Petrie
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB3318868A priority Critical patent/GB1275062A/en
Priority to FR6923174A priority patent/FR2012730A1/fr
Priority to DE19691934843 priority patent/DE1934843A1/en
Publication of GB1275062A publication Critical patent/GB1275062A/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
    • F02K3/06—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 with front fan

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1275062 Gas turbine ducted fan engines ROLLS-ROYCE Ltd 7 July 1969 [11 July 1968] 33188/68 Heading F1J A gas turbine ducted fan engine comprises in flow series a plurality of compressors, combustion equipment and a plurality of turbines which drive the compressors, at least one of the compressors producing compression of the air supplied to the combustion equipment and at least another of the compressors having a single stage radially inner portion whose blading is disposed in the main flow duct and produces substantially no compression of the said air, the radially outer portion of the said blading constituting the fan of the engine and being disposed in a fan duct which surrounds the main flow duct. The engine shown comprises LP compressor 30, IP compressor 13, HP compressor 14, combustion equipment 15, HP turbine 16, IP turbine 20 and LP turbine 22 all disposed in flow series in the main flow duct 11. The HP, IP and LP turbines drive the respective compressors through shafts 17, 21 and 23. The LP compressor 30 is single stage and produces substantially no compression on the air passing through the duct 11; the IP compressor and the HP compressor are each five-stage compressors. The turbines shown are each single stage although the LP turbine preferably comprises two or more stages; the LP turbine comprises variable inlet guide vanes 27. The HP turbine 16 drives also an output shaft 24 through shaft 25 and gearing 26, the shaft 24 being arranged to drive engine auxiliary equipment. The LP compressor 30 carries three stages of fan blading 33, 34, 35 radially outwardly of the compressor blading, the fan being disposed in a duct 32 and being associated with variable stator blading 36. Reference has been directed by the Comptroller to Specification 980368.
GB3318868A 1968-07-11 1968-07-11 Gas turbine fan engine Expired GB1275062A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB3318868A GB1275062A (en) 1968-07-11 1968-07-11 Gas turbine fan engine
FR6923174A FR2012730A1 (en) 1968-07-11 1969-07-08
DE19691934843 DE1934843A1 (en) 1968-07-11 1969-07-09 Gas turbine jet engine with fan

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3318868A GB1275062A (en) 1968-07-11 1968-07-11 Gas turbine fan engine

Publications (1)

Publication Number Publication Date
GB1275062A true GB1275062A (en) 1972-05-24

Family

ID=10349713

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3318868A Expired GB1275062A (en) 1968-07-11 1968-07-11 Gas turbine fan engine

Country Status (3)

Country Link
DE (1) DE1934843A1 (en)
FR (1) FR2012730A1 (en)
GB (1) GB1275062A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2262778A (en) * 1991-12-24 1993-06-30 Snecma Variable cycle propulsion engine for supersonic aircraft.

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2262778A (en) * 1991-12-24 1993-06-30 Snecma Variable cycle propulsion engine for supersonic aircraft.
GB2262778B (en) * 1991-12-24 1995-05-10 Snecma Variable cycle propulsion engine for supersonic aircraft

Also Published As

Publication number Publication date
FR2012730A1 (en) 1970-03-20
DE1934843A1 (en) 1971-01-21

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Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees