GB1294898A – – Google Patents
GB1294898A – – Google Patents
Info
Publication number
GB1294898A
GB1294898A
GB6089969A
GB1294898DA
GB1294898A
GB 1294898 A
GB1294898 A
GB 1294898A
GB 6089969 A
GB6089969 A
GB 6089969A
GB 1294898D A
GB1294898D A
GB 1294898DA
GB 1294898 A
GB1294898 A
GB 1294898A
Authority
GB
United Kingdom
Prior art keywords
fan
engine
shaft
rotor
assembly
Prior art date
1969-12-13
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
GB6089969A
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.)
1969-12-13
Filing date
1969-12-13
Publication date
1972-11-01
1969-12-13
Application filed
filed
Critical
1972-11-01
Publication of GB1294898A
publication
Critical
patent/GB1294898A/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
F02K3/06—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
F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F01D7/00—Rotors with blades adjustable in operation; Control thereof
F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
F04—POSITIVE – DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
F04D—NON-POSITIVE-DISPLACEMENT PUMPS
F04D29/00—Details, component parts, or accessories
F04D29/26—Rotors specially for elastic fluids
F04D29/32—Rotors specially for elastic fluids for axial flow pumps
F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
F04D29/322—Blade mountings
F04D29/323—Blade mountings adjustable
F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
F05D2220/00—Application
F05D2220/30—Application in turbines
F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
F05D2260/00—Function
F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
F05D2260/74—Adjusting of angle of incidence or attack of rotating blades by turning around an axis perpendicular the rotor centre line
F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
F05D2260/00—Function
F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
F05D2260/76—Adjusting of angle of incidence or attack of rotating blades the adjusting mechanism using auxiliary power sources
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
Abstract
1294898 Gas turbine ducted fan engines DOWTY ROTOL Ltd 13 Nov 1970 [13 Dec 1969] 60899/69 Heading F1J The invention relates to a fan assembly for attachment to the front of a main gas turbine engine so as to provide an engine of the ducted fan by-pass type, the assembly being constructed as a unit which can be attached to or removed from the engine. The fan assembly is indicated as A in Fig.1 and the forward part of the gas turbine engine at B, the fan assembly being secured to the engine at the plane C. The fan assembly comprises fixed structure 10 in which the fan rotor assembly is rotatably mounted, the fixed structure also supporting the by-pass duct 13 through a series of stator vanes 14 disposed downstream of the fan rotor blades 12. The fan rotor shaft 28 is supported within the fixed structure 10 by means of bearings 29. The rotor blades 12 are of adjustable pitch, the pitch being adjusted by means of a vane type motor 15 which comprises two oppositely angularly movable members 18,19 formed with bevel gear wheels 22, 23 which mesh with bevel pinions 20 mounted at the roots of the rotor blades 12, angular movement of the members 18,19 thus resulting in adjustment of the pitch of the fan rotor blades. The fan rotor is driven from the engine shaft 31 by means of a quill shaft 30 which is in splined engagement with the engine shaft 31 and the fan rotor shaft 28. A spinner 24 forms part of the rotor assembly. A guard ring 25 is incorporated in the fan duct 13. In Fig.3 the fan rotor 11 is driven from the engine shaft 40 through reduction gearing 37, the stator structure 10 projecting forwardly to provide a bearing support for the fan rotor shaft. The angularly movable members 18,19 of the vane rotor 15 extend rearwardly as shown, the members being formed with bevel gears which engage bevel pinions 20 on the fan rotor blades as in Fig.1. The fan blades are two-tiered comprising an outer part 12 of angularly adjustable pitch and an inner part 32 of fixed pitch, the pitch change shaft of the part 12 extending through the inner part 32. The fan stator structure comprises a splitter member 41 which defines the inner wall of the fan duct and the outer wall of a duct leading air from the inner blade parts 32 to the intake 27 of the engine compressor. In Fig.4 (not shown), a drive for engine auxiliaries is taken from the reduction gearing 37 through a radially-extending shaft (45) and a horizontally-extending shaft (48). (For Figures see next page)
GB6089969A
1969-12-13
1969-12-13
Expired
GB1294898A
(en)
Applications Claiming Priority (2)
Application Number
Priority Date
Filing Date
Title
GB6089969
1969-12-13
US9100070A
1970-11-19
1970-11-19
Publications (1)
Publication Number
Publication Date
GB1294898A
true
GB1294898A
(en)
1972-11-01
Family
ID=26267838
Family Applications (1)
Application Number
Title
Priority Date
Filing Date
GB6089969A
Expired
GB1294898A
(en)
1969-12-13
1969-12-13
Country Status (4)
Country
Link
US
(1)
US3720060A
(en)
DE
(1)
DE2061425C3
(en)
FR
(1)
FR2070846B1
(en)
GB
(1)
GB1294898A
(en)
Cited By (2)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
US5419112A
(en)
*
1989-06-05
1995-05-30
General Electric Company
Gas turbine powerplant
CN104520542A
(en)
*
2012-08-09
2015-04-15
斯奈克玛
Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan
Families Citing this family (86)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
US3811791A
(en)
*
1971-08-12
1974-05-21
R Cotton
Thrust augmenting device for jet aircraft
DE2218874C3
(en)
*
1972-04-19
1979-05-17
Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen
Device for adjusting the fan blades of a turbine jet engine
DE2307656C3
(en)
*
1973-02-16
1979-01-04
Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen
Device for adjusting the fan blades of an impeller for turbine jet engines
US3942911A
(en)
*
1973-02-17
1976-03-09
Dowty Rotol Limited
Bladed rotors
US3893783A
(en)
*
1973-02-17
1975-07-08
Dowty Rotol Ltd
Gas turbine engines and bladed rotors therefor
GB1444754A
(en)
*
1973-04-18
1976-08-04
Dowty Rotol Ltd
Rotary actuators suitable for bladed rotors
GB1444753A
(en)
*
1973-04-18
1976-08-04
Dowty Rotol Ltd
Rotary actuators suitable for bladed rotors
US3904315A
(en)
*
1974-07-31
1975-09-09
United Aircraft Corp
Pitch change signal means with differential gearing
US3912418A
(en)
*
1974-10-01
1975-10-14
United Technologies Corp
Lubrication system for a rotor
US4005574A
(en)
*
1975-04-21
1977-02-01
The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration
Reverse pitch fan with divided splitter
US4010919A
(en)
*
1975-12-05
1977-03-08
Breuner Gerald L
Autogyro having blade tip jets
US4239452A
(en)
*
1978-06-26
1980-12-16
United Technologies Corporation
Blade tip shroud for a compression stage of a gas turbine engine
JPS6318799Y2
(en)
*
1980-12-02
1988-05-26
US4566269A
(en)
*
1983-10-11
1986-01-28
United Technologies Corporation
Jet engine removable support assembly
GB2192233B
(en)
*
1986-07-02
1990-11-28
Rolls Royce Plc
A gas turbine engine load transfer structure
US4750862A
(en)
*
1986-11-28
1988-06-14
United Technologies Corporation
Modular propeller blade pitch actuation system
US4744214A
(en)
*
1987-06-29
1988-05-17
United Technologies Corporation
Engine modularity
US4976102A
(en)
*
1988-05-09
1990-12-11
General Electric Company
Unducted, counterrotating gearless front fan engine
US4934140A
(en)
*
1988-05-13
1990-06-19
United Technologies Corporation
Modular gas turbine engine
US4968217A
(en)
*
1989-09-06
1990-11-06
Rolls-Royce Plc
Variable pitch arrangement for a gas turbine engine
US5222360A
(en)
*
1991-10-30
1993-06-29
General Electric Company
Apparatus for removably attaching a core frame to a vane frame with a stable mid ring
US5205513A
(en)
*
1991-09-26
1993-04-27
General Electric Company
Method and system for the removal of large turbine engines
CA2533425C
(en)
*
2003-07-29
2012-09-25
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
WO2006059995A1
(en)
*
2004-12-01
2006-06-08
United Technologies Corporation
Gearbox lubrication supply system for a tip turbine engine
US7980054B2
(en)
*
2004-12-01
2011-07-19
United Technologies Corporation
Ejector cooling of outer case for tip turbine engine
DE602004029950D1
(en)
*
2004-12-01
2010-12-16
United Technologies Corp
SLIDED GEAR ASSEMBLY FOR A TOP TURBINE ENGINE
DE602004023769D1
(en)
*
2004-12-01
2009-12-03
United Technologies Corp
STACKED RINGING COMPONENTS FOR TURBINE ENGINES
WO2006110122A2
(en)
2004-12-01
2006-10-19
United Technologies Corporation
Inflatable bleed valve for a turbine engine and a method of operating therefore
WO2006059985A1
(en)
2004-12-01
2006-06-08
United Technologies Corporation
Axial compressor for tip turbine engine
US8033094B2
(en)
*
2004-12-01
2011-10-11
United Technologies Corporation
Cantilevered tip turbine engine
WO2006060006A1
(en)
2004-12-01
2006-06-08
United Technologies Corporation
Tip turbine engine non-metallic tailcone
EP1825117B1
(en)
*
2004-12-01
2012-06-13
United Technologies Corporation
Turbine engine with differential gear driven fan and compressor
US7976273B2
(en)
*
2004-12-01
2011-07-12
United Technologies Corporation
Tip turbine engine support structure
US7883314B2
(en)
*
2004-12-01
2011-02-08
United Technologies Corporation
Seal assembly for a fan-turbine rotor of a tip turbine engine
WO2006059973A1
(en)
*
2004-12-01
2006-06-08
United Technologies Corporation
Tip turbine engine with a heat exchanger
WO2006059980A2
(en)
2004-12-01
2006-06-08
United Technologies Corporation
Diffuser aspiration for a tip turbine engine
DE602004031986D1
(en)
*
2004-12-01
2011-05-05
United Technologies Corp
BLOWER TURBINE ROTOR ASSEMBLY FOR A TOP TURBINE ENGINE
DE602004028297D1
(en)
*
2004-12-01
2010-09-02
United Technologies Corp
COMPREHENSIVE COMBUSTION CHAMBER FOR TOP TURBINE ENGINE
EP1834071B1
(en)
*
2004-12-01
2013-03-13
United Technologies Corporation
Inducer for a fan blade of a tip turbine engine
EP1841960B1
(en)
*
2004-12-01
2011-05-25
United Technologies Corporation
Starter generator system for a tip turbine engine
WO2006060009A1
(en)
*
2004-12-01
2006-06-08
United Technologies Corporation
Turbine blade engine comprising turbine clusters and radial attachment lock arrangement therefor
WO2006059997A2
(en)
2004-12-01
2006-06-08
United Technologies Corporation
Annular turbine ring rotor
WO2006112807A2
(en)
2004-12-01
2006-10-26
United Technologies Corporation
Turbine engine and method for starting a turbine engine
US7882694B2
(en)
2004-12-01
2011-02-08
United Technologies Corporation
Variable fan inlet guide vane assembly for gas turbine engine
EP1841959B1
(en)
*
2004-12-01
2012-05-09
United Technologies Corporation
Balanced turbine rotor fan blade for a tip turbine engine
WO2006060011A1
(en)
*
2004-12-01
2006-06-08
United Technologies Corporation
Tip turbine engine comprising a nonrotable compartment
EP2333287A1
(en)
*
2004-12-01
2011-06-15
United Technologies Corporation
Vectoring transition duct for turbine engine
US8641367B2
(en)
2004-12-01
2014-02-04
United Technologies Corporation
Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
US7874802B2
(en)
*
2004-12-01
2011-01-25
United Technologies Corporation
Tip turbine engine comprising turbine blade clusters and method of assembly
US7959532B2
(en)
*
2004-12-01
2011-06-14
United Technologies Corporation
Hydraulic seal for a gearbox of a tip turbine engine
WO2006060005A1
(en)
*
2004-12-01
2006-06-08
United Technologies Corporation
Fan-turbine rotor assembly with integral inducer section for a tip turbine engine
WO2006060003A2
(en)
*
2004-12-01
2006-06-08
United Technologies Corporation
Fan blade with integral diffuser section and tip turbine blade section for a tip turbine engine
WO2006059990A1
(en)
*
2004-12-01
2006-06-08
United Technologies Corporation
Regenerative turbine blade and vane cooling for a tip turbine engine
WO2006059971A2
(en)
*
2004-12-01
2006-06-08
United Technologies Corporation
Tip turbine engine integral fan, combustor, and turbine case
WO2006059979A1
(en)
*
2004-12-01
2006-06-08
United Technologies Corporation
Tip turbine engine integral case, vane, mount, and mixer
EP1831520B1
(en)
*
2004-12-01
2009-02-25
United Technologies Corporation
Tip turbine engine and corresponding operating method
US7631480B2
(en)
*
2004-12-01
2009-12-15
United Technologies Corporation
Modular tip turbine engine
WO2006059969A1
(en)
*
2004-12-01
2006-06-08
United Technologies Corporation
Counter-rotating compressor case and assembly method for tip turbine engine
US7934902B2
(en)
*
2004-12-01
2011-05-03
United Technologies Corporation
Compressor variable stage remote actuation for turbine engine
US20090148273A1
(en)
*
2004-12-01
2009-06-11
Suciu Gabriel L
Compressor inlet guide vane for tip turbine engine and corresponding control method
US7883315B2
(en)
*
2004-12-01
2011-02-08
United Technologies Corporation
Seal assembly for a fan rotor of a tip turbine engine
EP1825113B1
(en)
*
2004-12-01
2012-10-24
United Technologies Corporation
Counter-rotating gearbox for tip turbine engine
US8096753B2
(en)
*
2004-12-01
2012-01-17
United Technologies Corporation
Tip turbine engine and operating method with reverse core airflow
WO2006060004A1
(en)
2004-12-01
2006-06-08
United Technologies Corporation
Combustor for turbine engine
US8104257B2
(en)
*
2004-12-01
2012-01-31
United Technologies Corporation
Tip turbine engine with multiple fan and turbine stages
US9003759B2
(en)
*
2004-12-01
2015-04-14
United Technologies Corporation
Particle separator for tip turbine engine
US9109537B2
(en)
*
2004-12-04
2015-08-18
United Technologies Corporation
Tip turbine single plane mount
FR2911644B1
(en)
*
2007-01-23
2012-06-01
Snecma
TURBOPROPULSEUR COMPRISING A PROPELLED PROPELLER OF BLADES WITH ADJUSTABLE ORIENTATION.
US8967945B2
(en)
2007-05-22
2015-03-03
United Technologies Corporation
Individual inlet guide vane control for tip turbine engine
US20100187825A1
(en)
*
2009-01-28
2010-07-29
Fred Carr
Microprocessor system for controlling rotor pitch
RU2523928C2
(en)
*
2009-02-27
2014-07-27
Снекма
Fan blades with variable pitch angle
US8602731B2
(en)
*
2009-12-30
2013-12-10
Fred K. Carr
Microprocessor system for controlling rotor pitch
DE102012000889A1
(en)
2012-01-18
2013-07-18
Rolls-Royce Deutschland Ltd & Co Kg
Air turbine with adjustable fan
US9476323B2
(en)
2012-05-31
2016-10-25
United Technologies Corporation
Turbine gear assembly support having symmetrical removal features
US9103376B2
(en)
*
2013-10-23
2015-08-11
Hamilton Sundstrand Corporation
Chambered shaft for improved bearing lubrication
US10215096B2
(en)
*
2015-11-04
2019-02-26
United Technologies Corporation
Engine with nose cone heat exchanger and radially outer discharge
US10436151B2
(en)
*
2015-11-17
2019-10-08
General Electric Company
Modular fan for a gas turbine engine
US20170218975A1
(en)
*
2016-01-29
2017-08-03
United Technologies Corporation
Variable pitch fan blade arrangement for gas turbine engine
US11130456B2
(en)
*
2016-05-18
2021-09-28
Rolls-Royce North American Technologies Inc.
Low pressure generator for gas turbine engine
US11022042B2
(en)
2016-08-29
2021-06-01
Rolls-Royce North American Technologies Inc.
Aircraft having a gas turbine generator with power assist
US10415405B2
(en)
*
2017-04-21
2019-09-17
United Technologies Corporation
Variable pitch fan blade system
US11255215B2
(en)
2017-07-06
2022-02-22
Rolls-Royce North American Technologies Inc.
Gas turbine engine with microchannel cooled electric device
FR3080886B1
(en)
*
2018-05-02
2020-10-30
Safran Aircraft Engines
FAIRING BLOWER TURBOMACHINE
FR3087232B1
(en)
*
2018-10-12
2021-06-25
Safran Aircraft Engines
TURBOMACHINE INCLUDING A ROTOR WITH VARIABLE TIMING BLADES
FR3100563B1
(en)
*
2019-09-06
2021-08-06
Safran Aircraft Engines
Polyspherical turbomachine hub for variable pitch blades
Family Cites Families (9)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
US2528635A
(en)
*
1943-06-22
1950-11-07
Rolls Royce
Power gas generator for internalcombustion power units
US2711631A
(en)
*
1949-06-21
1955-06-28
Hartford Nat Bank & Trust Co
Gas turbine power plant
US3476486A
(en)
*
1966-04-12
1969-11-04
Dowty Rotol Ltd
Gas turbine engines
CH457976A
(en)
*
1966-05-25
1968-06-15
Dowty Rotol Ltd
Turboprop
FR1545548A
(en)
*
1966-12-05
1968-11-08
Rolls Royce
Fan intended in particular for gas turbine engines
FR1518513A
(en)
*
1967-04-12
1968-03-22
Dowty Rotol Ltd
Gas turbine engine machines
FR1518519A
(en)
*
1967-04-12
1968-03-22
Dowty Rotol Ltd
Improvements to gas turbines featuring a blower with adjustable blades
US3390527A
(en)
*
1967-07-19
1968-07-02
Avco Corp
High bypass ratio turbofan
US3616616A
(en)
*
1968-03-11
1971-11-02
Tech Dev Inc
Particle separator especially for use in connection with jet engines
1969
1969-12-13
GB
GB6089969A
patent/GB1294898A/en
not_active
Expired
1970
1970-11-19
US
US00091000A
patent/US3720060A/en
not_active
Expired – Lifetime
1970-12-11
FR
FR7044733A
patent/FR2070846B1/fr
not_active
Expired
1970-12-14
DE
DE2061425A
patent/DE2061425C3/en
not_active
Expired
Cited By (3)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
US5419112A
(en)
*
1989-06-05
1995-05-30
General Electric Company
Gas turbine powerplant
CN104520542A
(en)
*
2012-08-09
2015-04-15
斯奈克玛
Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan
CN104520542B
(en)
*
2012-08-09
2016-04-13
斯奈克玛
Comprise multiple turbines being installed in the fixed radial blades of fan upstream
Also Published As
Publication number
Publication date
DE2061425C3
(en)
1980-01-03
FR2070846A1
(en)
1971-09-17
DE2061425B2
(en)
1977-05-18
US3720060A
(en)
1973-03-13
DE2061425A1
(en)
1971-06-24
FR2070846B1
(en)
1975-02-21
Similar Documents
Publication
Publication Date
Title
GB1294898A
(en)
1972-11-01
JP2755417B2
(en)
1998-05-20
Prop fan-turbine engine
GB1445015A
(en)
1976-08-04
Gas turbine engines
US2454738A
(en)
1948-11-23
Internal-combustion turbine power plant
GB1233718A
(en)
1971-05-26
GB978658A
(en)
1964-12-23
Gas turbine by-pass engines
GB1141816A
(en)
1969-02-05
Improvements in turbofan engines having contra-rotating compressors
GB1294324A
(en)
1972-10-25
Engine installations
GB1113542A
(en)
1968-05-15
Gas turbine engine
GB958842A
(en)
1964-05-27
Ducted fan lift engine
US3663119A
(en)
1972-05-16
Bladed rotors
US3020004A
(en)
1962-02-06
Turbine-propeller power units for aircraft
GB1454233A
(en)
1976-11-03
Variable pitch ducted fan propulsion assembly
GB1118898A
(en)
1968-07-03
Fluid flow machine
US3620021A
(en)
1971-11-16
Gas turbine engines
US3528752A
(en)
1970-09-15
Gas turbine engines
US3462953A
(en)
1969-08-26
Gas turbine jet propulsion engine
US3423048A
(en)
1969-01-21
Gas turbine compound helicopter power plant
GB1274226A
(en)
1972-05-17
Variable-pitch bladed rotors
GB2194593A
(en)
1988-03-09
High bypass ratio, counter rotating gearless front fan engine
US3487880A
(en)
1970-01-06
Variable pitch fans
GB626036A
(en)
1949-07-07
Improvements in or relating to gas-turbine engines
GB1278570A
(en)
1972-06-21
Ducted fan gas turbine engines
GB1072020A
(en)
1967-06-14
Gas turbine engine
US2490623A
(en)
1949-12-06
Jet propeller aircraft engine
Legal Events
Date
Code
Title
Description
1973-03-14
PS
Patent sealed [section 19, patents act 1949]
1982-06-23
PCNP
Patent ceased through non-payment of renewal fee
