GB758403A - Improvements relating to aircraft - Google Patents

Improvements relating to aircraft

Info

Publication number
GB758403A
GB758403A GB17164/54A GB1716454A GB758403A GB 758403 A GB758403 A GB 758403A GB 17164/54 A GB17164/54 A GB 17164/54A GB 1716454 A GB1716454 A GB 1716454A GB 758403 A GB758403 A GB 758403A
Authority
GB
United Kingdom
Prior art keywords
compressor
turbine
supplied
aircraft
air
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
GB17164/54A
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of GB758403A publication Critical patent/GB758403A/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
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/16—Composite ram-jet/turbo-jet engines
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/74—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/74—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant
    • F02K9/78—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with an air-breathing jet-propulsion plant

Abstract

758,403. Gas turbine engines; jet propulsion engines. SMURIK, J. Jan. 11, 1954 [Jan. 11, 1953], No. 17164/54. Class 110(3) [Also in Group XXXIII] An aircraft is propelled by three power plants located in openended channels 25, 26 and 27 positioned between the underside of the fuselage and a curved wing 11, the plants being so arranged that they may optionally function as turbo-jets, ram-jets or rockets. The nose of the fuselage has a variable-area air intake 35 and each channel terminates in a propulsion nozzle, one, 31, being shown in Fig. 2. Each jet-propulsion plant comprises the elements shown in Fig. 2 wherein a combustion chamber 40 is supplied with air from a compressor 49 and the jet efflux passes to a turbine 50 and the propulsion nozzle 31. This nozzle has pivoted flap valves 65, 89, 70 and 71 operated by jacks 73, 73d to vary the outlet area. The combustion chamber 40 is provided with spaced air inlets 41 along its sides and a sleeve 42 with corresponding apertures is arranged to be mounted on the burner for sliding movement under the action of a jack 43. Inlets- 63, Fig. 5, are masked by an apertured sliding shutter 87 operated by a jack 88. The turbine 50 drives the compressor 49 through a gear train 52, 53, 55, 57 and 58, and gears 59, 60 drive a fuel pump 48. The turbine shaft 51 is hollow and is connected by a. rotary coupling with a conduit supplied with compressed air from the compressor, in order that the turbine blades may be cooled. In operation, the compressor and turbine are started in the usual manner and fuel is supplied to the combustion chamber 40 with the shutter 87 and sleeve 42 arranged to admit maximum air from the intake 28, the flap valves in the exhaust nozzle 31 being partially closed. When the aircraft has reached an appropriate speed the combustion chambers in the channels 26 and 27 are supplied with fuel, and air from the compressor, and are placed in communication with the chamber 40 to initiate combustion. The aircraft is then operating with all three units acting as turbojets and if valves between the compressor and the side combustion chambers are closed and the fuel supply is cut off the aircraft will be propelled by the side units acting as ram-jets and at high altitudes these engines may be supplied with oxygen from the tanks 17, 38 and 39 whereby they function as rockets.
GB17164/54A 1953-01-11 1954-01-11 Improvements relating to aircraft Expired GB758403A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US758403XA 1953-01-11 1953-01-11

Publications (1)

Publication Number Publication Date
GB758403A true GB758403A (en) 1956-10-03

Family

ID=22128311

Family Applications (1)

Application Number Title Priority Date Filing Date
GB17164/54A Expired GB758403A (en) 1953-01-11 1954-01-11 Improvements relating to aircraft

Country Status (1)

Country Link
GB (1) GB758403A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2190964A (en) * 1986-05-28 1987-12-02 Messerschmitt Boelkow Blohm Combined turbojet, ramjet, rocket propulsion unit
GB2240815A (en) * 1983-12-23 1991-08-14 Alan Bond Dual-mode aerospace propulsion engine.
GB2408971A (en) * 2003-11-05 2005-06-15 Peter Antony Hulmes Aircraft using both turbojet and rocket propulsion

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2240815A (en) * 1983-12-23 1991-08-14 Alan Bond Dual-mode aerospace propulsion engine.
GB2240815B (en) * 1983-12-23 1991-12-18 Alan Bond Improvements in aerospace propulsion
US5101622A (en) * 1983-12-23 1992-04-07 Rolls-Royce Plc Aerospace propulsion
GB2190964A (en) * 1986-05-28 1987-12-02 Messerschmitt Boelkow Blohm Combined turbojet, ramjet, rocket propulsion unit
GB2408971A (en) * 2003-11-05 2005-06-15 Peter Antony Hulmes Aircraft using both turbojet and rocket propulsion

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