GB1252077A – – Google Patents
GB1252077A – – Google Patents
Info
Publication number
GB1252077A
GB1252077A
GB1233869A
GB1252077DA
GB1252077A
GB 1252077 A
GB1252077 A
GB 1252077A
GB 1233869 A
GB1233869 A
GB 1233869A
GB 1252077D A
GB1252077D A
GB 1252077DA
GB 1252077 A
GB1252077 A
GB 1252077A
Authority
GB
United Kingdom
Prior art keywords
nozzles
duct
nozzle
terminating
aircraft
Prior art date
1969-03-08
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
GB1233869A
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.)
1969-03-08
Filing date
1969-03-08
Publication date
1971-11-03
1969-03-08
Application filed
filed
Critical
1971-11-03
Publication of GB1252077A
publication
Critical
patent/GB1252077A/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
F02K3/025—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 by-pass flow being at least partly used to create an independent thrust component
B—PERFORMING OPERATIONS; TRANSPORTING
B64—AIRCRAFT; AVIATION; COSMONAUTICS
B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
B64D27/02—Aircraft characterised by the type or position of power plant
B64D27/16—Aircraft characterised by the type or position of power plant of jet type
B64D27/18—Aircraft characterised by the type or position of power plant of jet type within or attached to wing
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
F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
F02K3/105—Heating the by-pass flow
F02K3/11—Heating the by-pass flow by means of burners or combustion chambers
Abstract
1,252,077. V.T.O.L. aircraft. ROLLS-ROYCE Ltd. 4 March, 1970 [8 March, 1969 (2)], Nos. 12338/69 and 12339/69. Heading B7G. [Also in Division F1] An aircraft jet propulsion power plant comprises a duct 10 containing in flow series a compressor 11, combustion equipment 12, a turbine 13 driving the compressor and a first nozzle N1; the plant also comprises a second duet 21 connected to the first duct to receive pressure fluid therefrom, and terminating in a plurality of second nozzles N2, the second duct being connected to the first duct at a point where pressure is sufficiently high in relation to the individual second nozzles to produce from the second nozzles a jet flow the noise spectrum of which has its peak at an ultrasonic frequency. In the engine shown the second duct 21 divides into two passages 23, 25 and air flowing through the duct 21 may be passed to either passage under control of valves 22, the passage 25 terminating in two parallel rows of downwardly directed nozzles N2 for use when vertical lift is required, and the passage 23 terminating in a rearwardly-directed nozzle 24 for use when forward thrust is required. A cowl 16 is associated with the nozzle N1 being movable between retracted and projected positions for rearward- and downwardly-directed thrust. The nozzles N2 are shown in Figs. 5 and 6 each comprising a combustion chamber 27 and fuel supply 28; a U-sectioned member is provided in each outlet and the outlets so formed are split up by baffles 29 so as to provide the plurality of nozzles N2. In the example described there are 346 nozzles each 0À2 square inch area. Adjustable baffle plates 34 are disposed laterally of the nozzles N2. In the example, with a by-pass pressure ratio of 15 : 1 nozzle entry temperature of 1000‹ K., and jet velocity of 3500 ft./sec., the 346 nozzles each 0À2 square inch area produces a thrust of 20,000 lb. In an aircraft comprising a plurality of such engines, the passages 25 of the engines are interconnected so as to allow for failure of an engine when vertical lift is in operation.
GB1233869A
1969-03-08
1969-03-08
Expired
GB1252077A
(en)
Applications Claiming Priority (1)
Application Number
Priority Date
Filing Date
Title
GB1233869
1969-03-08
Publications (1)
Publication Number
Publication Date
GB1252077A
true
GB1252077A
(en)
1971-11-03
Family
ID=10002660
Family Applications (1)
Application Number
Title
Priority Date
Filing Date
GB1233869A
Expired
GB1252077A
(en)
1969-03-08
1969-03-08
Country Status (1)
Country
Link
GB
(1)
GB1252077A
(en)
Cited By (4)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
DE3520015A1
(en)
*
1985-06-04
1987-01-08
Gerhard Nerenberg
Nozzle arrangement in the case of a powerplant
GB2231009A
(en)
*
1984-11-17
1990-11-07
Rolls Royce
Diverter valve with bypass duct obturator for twin gas turbine engine installation
US4979363A
(en)
*
1984-11-17
1990-12-25
Rolls-Royce Plc
Diverter valve with bypass duct obturator
GB2391846A
(en)
*
2002-06-28
2004-02-18
Ashley Christopher Bryant
Ducted air power plant
1969
1969-03-08
GB
GB1233869A
patent/GB1252077A/en
not_active
Expired
Cited By (7)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
GB2231009A
(en)
*
1984-11-17
1990-11-07
Rolls Royce
Diverter valve with bypass duct obturator for twin gas turbine engine installation
US4979363A
(en)
*
1984-11-17
1990-12-25
Rolls-Royce Plc
Diverter valve with bypass duct obturator
GB2231009B
(en)
*
1984-11-17
1991-01-23
Rolls Royce
Diverter valve with bypass duct obturator
DE3520015A1
(en)
*
1985-06-04
1987-01-08
Gerhard Nerenberg
Nozzle arrangement in the case of a powerplant
GB2391846A
(en)
*
2002-06-28
2004-02-18
Ashley Christopher Bryant
Ducted air power plant
GB2391846B
(en)
*
2002-06-28
2005-10-05
Ashley Christopher Bryant
Ducted air power plant
US7581381B2
(en)
2002-06-28
2009-09-01
Vtol Technologies Limited
Ducted air power plant
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Legal Events
Date
Code
Title
Description
1972-08-23
PS
Patent sealed
1977-09-28
PLNP
Patent lapsed through nonpayment of renewal fees
