GB1229007A – – Google Patents
GB1229007A – – Google Patents
Info
Publication number
GB1229007A
GB1229007A
GB5759968A
GB1229007DA
GB1229007A
GB 1229007 A
GB1229007 A
GB 1229007A
GB 5759968 A
GB5759968 A
GB 5759968A
GB 1229007D A
GB1229007D A
GB 1229007DA
GB 1229007 A
GB1229007 A
GB 1229007A
Authority
GB
United Kingdom
Prior art keywords
turbine
fan
compressor
vanes
duct
Prior art date
1968-12-04
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
GB5759968A
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.)
1968-12-04
Filing date
1968-12-04
Publication date
1971-04-21
1968-12-04
Application filed
filed
Critical
1971-04-21
Publication of GB1229007A
publication
Critical
patent/GB1229007A/en
Status
Expired
legal-status
Critical
Current
Links
Espacenet
Global Dossier
Discuss
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
F02K3/065—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 and aft fans
Abstract
1,229,007. Gas turbine ducted fan engines. ROLLS-ROYCE Ltd. Nov.27, 1969 [Dec. 4, 1968], No.57599/68. Heading F1J. A gas turbine ducted fan engine comprises an inner duct in which are located a gas turbine type gas generator and a separate turbine driven by gases from the gas generator, and an outer duct in which are located two fans axially spaced apart so that in operation substantially no wake interaction occurs between them, one of the fans being drivingly connected to the gas generator and the other being drivingly connected to the separate turbine. The engine shown comprises an inner duct 12 in which are located in series flow an LP compressor 15, IP compressor 26, HP compressor 16, combustion equipment 17, single stage HP turbine 18, three-stage IP turbine 19, singlestage LP turbine 20 and three-stage separate power turbine 35, the HP, IP and LP turbines being connected to the HP, IP and LP compressors by shafts 22, 24, 23, respectively. The IP compressor 26 comprises also a rotatable wall portion 27 on which are mounted inlet rotor vanes 30 and interstage vanes 29, the inner fairing portion 31 being connected to the inner ends of the inlet rotor vanes 30. A fan duct 13 is disposed around the inner duct 12 and in it are disposed an upstream fan 40 and a downstream fan 45, rows of stator vanes 48 and 49 being disposed between the two fans and a row of outlet guide vanes 50 being disposed downstream of the fan 45. The upstream fan 40 is drivingly connected to the IP compressor 26 and so to the IP turbine 19, by a drive connection 41. The downstream fan 45 is drivingly connected to the separate power turbine 35 by a drive connection 46 connected to the outer ends of the second stage blades 37 of the separate turbine.
GB5759968A
1968-12-04
1968-12-04
Expired
GB1229007A
(en)
Applications Claiming Priority (1)
Application Number
Priority Date
Filing Date
Title
GB5759968
1968-12-04
Publications (1)
Publication Number
Publication Date
GB1229007A
true
GB1229007A
(en)
1971-04-21
Family
ID=10479561
Family Applications (1)
Application Number
Title
Priority Date
Filing Date
GB5759968A
Expired
GB1229007A
(en)
1968-12-04
1968-12-04
Country Status (4)
Country
Link
US
(1)
US3620009A
(en)
DE
(1)
DE1960479B2
(en)
FR
(1)
FR2025182A1
(en)
GB
(1)
GB1229007A
(en)
Cited By (2)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
US8562284B2
(en)
2009-06-29
2013-10-22
Rolls-Royce Plc
Propulsive fan system
GB2603148A
(en)
*
2021-01-28
2022-08-03
Rolls Royce Plc
Gas turbine engine
Families Citing this family (17)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
US3861139A
(en)
*
1973-02-12
1975-01-21
Gen Electric
Turbofan engine having counterrotating compressor and turbine elements and unique fan disposition
FR2461820A1
(en)
*
1979-07-16
1981-02-06
Snecma
MULTIFLUX TURBOREACTOR WITH A DILUTION RATE
US4611464A
(en)
*
1984-05-02
1986-09-16
United Technologies Corporation
Rotor assembly for a gas turbine engine and method of disassembly
US4685286A
(en)
*
1984-05-02
1987-08-11
United Technologies Corporation
Method of disassembly for a gas turbine engine
US4704862A
(en)
*
1985-05-29
1987-11-10
United Technologies Corporation
Ducted prop engine
US4860537A
(en)
*
1986-08-29
1989-08-29
Brandt, Inc.
High bypass ratio counterrotating gearless front fan engine
US4790133A
(en)
*
1986-08-29
1988-12-13
General Electric Company
High bypass ratio counterrotating turbofan engine
US4900221A
(en)
*
1988-12-16
1990-02-13
General Electric Company
Jet engine fan and compressor bearing support
FR2645911B1
(en)
*
1989-04-18
1991-06-07
Snecma
HIGH DILUTION MOTOR WITH UPSTREAM BLOWER AND DOWNSTREAM BLOWER
EP1777379A3
(en)
*
2003-07-29
2011-03-09
Pratt & Whitney Canada Corp.
Turbofan case and method of making
US7370467B2
(en)
*
2003-07-29
2008-05-13
Pratt & Whitney Canada Corp.
Turbofan case and method of making
EP1607612B1
(en)
*
2004-05-28
2009-03-04
Rolls-Royce Plc
Gas turbine engine
FR2908452A1
(en)
*
2006-11-15
2008-05-16
Snecma Sa
Fastener device for a gas turbine engine has a flange that provides releasable connections by mutual engagement between turbine stator and a gas generator casing and a sliding joint that provides centering of turbine stator on the casing
FR2966522B1
(en)
*
2010-10-26
2015-04-24
Snecma
DOUBLE BLOWER TURBOMACHINE AND TRIPLE FLUX
US9498850B2
(en)
2012-03-27
2016-11-22
Pratt & Whitney Canada Corp.
Structural case for aircraft gas turbine engine
GB201510167D0
(en)
*
2015-06-11
2015-07-29
Rolls Royce Plc
Gas turbine engine
US10711702B2
(en)
*
2015-08-18
2020-07-14
General Electric Company
Mixed flow turbocore
1968
1968-12-04
GB
GB5759968A
patent/GB1229007A/en
not_active
Expired
1969
1969-12-02
US
US881374A
patent/US3620009A/en
not_active
Expired – Lifetime
1969-12-02
FR
FR6941531A
patent/FR2025182A1/fr
not_active
Withdrawn
1969-12-02
DE
DE19691960479
patent/DE1960479B2/en
active
Granted
Cited By (2)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
US8562284B2
(en)
2009-06-29
2013-10-22
Rolls-Royce Plc
Propulsive fan system
GB2603148A
(en)
*
2021-01-28
2022-08-03
Rolls Royce Plc
Gas turbine engine
Also Published As
Publication number
Publication date
DE1960479B2
(en)
1976-11-18
US3620009A
(en)
1971-11-16
DE1960479A1
(en)
1970-08-06
FR2025182A1
(en)
1970-09-04
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Legal Events
Date
Code
Title
Description
1972-07-26
PS
Patent sealed [section 19, patents act 1949]
1978-11-15
PLE
Entries relating assignments, transmissions, licences in the register of patents
1979-06-27
PCNP
Patent ceased through non-payment of renewal fee
