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GB1257497A - - Google Patents

Info

Publication number
GB1257497A
GB1257497A GB1936069A GB1257497DA GB1257497A GB 1257497 A GB1257497 A GB 1257497A GB 1936069 A GB1936069 A GB 1936069A GB 1257497D A GB1257497D A GB 1257497DA GB 1257497 A GB1257497 A GB 1257497A
Authority
GB
United Kingdom
Prior art keywords
fan
turbine
compressor
main fan
blades
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
GB1936069A
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 filed Critical
Publication of GB1257497A publication Critical patent/GB1257497A/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

1,257,497. Gas turbine by-pass type jet engines. ROLLS-ROYCE Ltd. April 15, 1970 [April 16, 1969], No. 19360/69. Heading F1J. A gas turbine by-pass type jet engine comprises compressor means, combustion means and turbine means, a rotatable main fan extending completely across the by-pass duct and a rotatable secondary fan is disposed upstream of the main fan and extends only partly across the by-pass duct, the secondary fan being driven by the turbine means. The engine shown in Fig. 1, comprises an LP compressor 16, HP compressor 22, combustion equipment 12, HP turbine 24, LP turbine 18 and a further turbine 44, the HP turbine 24 driving the HP compressor 22 through shaft 26, the LP turbine 18 driving the LP compressor 16 through shaft 20 and the further turbine 44 driving a secondary fan 40 through shaft 42. The engine comprises also a by-pass duct 30 in which is disposed a main fan 28 which extends wholly across the by-pass duct, the secondary fan extending only partly across the by-pass duct. The main fan 28 is mounted on the stator casing 32 of the LP compressor, the casing being mounted for rotation, the compressor "stator" blades 34 acting as turbine blades, whereby the main fan is driven. A splitter 38 extends from the main fan blades 28 and the secondary fan blades 40 extend to the splitter. In a second embodiment the stator casing 32 of the LP compressor is fixed and the main fan 28 is rotatably mounted thereon, the main fan blades being driven by air from the secondary fan 40 acting on the radially inner portions of the fan blades. In a further embodiment the main fan 28 is mounted for rotation in bearings disposed adjacent the inner shaft 42 and not on the stator casing 32; the main fan is again driven by air from the secondary fan 40 acting on the radially inner portions of the fan blades.
GB1936069A 1969-04-16 1969-04-16 Expired GB1257497A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1936069 1969-04-16

Publications (1)

Publication Number Publication Date
GB1257497A true GB1257497A (en) 1971-12-22

Family

ID=10128051

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1936069A Expired GB1257497A (en) 1969-04-16 1969-04-16

Country Status (4)

Country Link
US (1) US3620020A (en)
DE (1) DE2018077C3 (en)
FR (1) FR2039215B1 (en)
GB (1) GB1257497A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6722847B2 (en) 2001-11-23 2004-04-20 Rolls-Royce Plc Fan for a turbofan gas turbine engine
DE102014226696A1 (en) * 2014-12-19 2016-06-23 Rolls-Royce Deutschland Ltd & Co Kg Pre-compressor device, retrofit kit and aircraft engine

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3747343A (en) * 1972-02-10 1973-07-24 United Aircraft Corp Low noise prop-fan
US3861139A (en) * 1973-02-12 1975-01-21 Gen Electric Turbofan engine having counterrotating compressor and turbine elements and unique fan disposition
GB0809759D0 (en) * 2008-05-30 2008-07-09 Rolls Royce Plc Gas turbine engine
US8166748B2 (en) 2008-11-21 2012-05-01 General Electric Company Gas turbine engine booster having rotatable radially inwardly extending blades and non-rotatable vanes
US20150345426A1 (en) 2012-01-31 2015-12-03 United Technologies Corporation Geared turbofan gas turbine engine architecture
US10287914B2 (en) 2012-01-31 2019-05-14 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section and bearing support features
US8935913B2 (en) 2012-01-31 2015-01-20 United Technologies Corporation Geared turbofan gas turbine engine architecture
US10125693B2 (en) 2012-04-02 2018-11-13 United Technologies Corporation Geared turbofan engine with power density range
US10036350B2 (en) 2012-04-30 2018-07-31 United Technologies Corporation Geared turbofan with three turbines all co-rotating
CA2923331A1 (en) * 2015-03-19 2016-09-19 David P. Houston Geared turbofan gas turbine engine architecture

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6722847B2 (en) 2001-11-23 2004-04-20 Rolls-Royce Plc Fan for a turbofan gas turbine engine
DE102014226696A1 (en) * 2014-12-19 2016-06-23 Rolls-Royce Deutschland Ltd & Co Kg Pre-compressor device, retrofit kit and aircraft engine

Also Published As

Publication number Publication date
DE2018077B2 (en) 1974-06-20
FR2039215A1 (en) 1971-01-15
DE2018077A1 (en) 1970-11-19
DE2018077C3 (en) 1975-02-06
US3620020A (en) 1971-11-16
FR2039215B1 (en) 1974-11-08

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLNP Patent lapsed through nonpayment of renewal fees