# US 2014/0196460 A1 · Ramjet including a detonation chamber and aircraft comprising such a ramjet > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0196460 A1 - Document ID: US20140196460A1 - Status: Published application - Kind: A1 - Application number: 14/116,003 - Filed: 2012-05-09 - Published: 2014-07-17 - Earliest claimed: 2011-05-16 - Assignees: Mbda France - Inventors: François Falempin; Bruno Le Naour - Web page: https://patentgrep.com/patent/US20140196460A1 ## CPC - F02K 7/20: Composite ram-jet/pulse-jet engines - F02K 7/08: the jet being continuous - F02K 7/10: characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines - F23R 7/00: Intermittent or explosive combustion chambers - F02K 7/00: 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 (rocket-engine plants F02K9/00) - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16) ## Abstract The invention relates to a ramjet including a detonation chamber and an aircraft comprising such a ramjet. According to the invention, the ramjet (S1) comprises an annular detonation chamber (2) having a continuous detonation wave and fuel injection means (6) for continuously injecting fuel (F2) directly into the chamber (2) just downstream of an air injection base (3). The fuel (F2) and the air (F1) are injected separately into the detonation chamber (2) in a permanent manner throughout the operation of the ramjet (S1). ## Claims ### Claim 1 Ramjet which operates with an explosive fuel-air mixture and comprises: at least one detonation chamber (2, 2A, 2B) which is equipped, at its upstream end, with an air injection base (3) and which terminates, at its downstream end, with an exhaust nozzle (4); at least one air intake (5) connected to said detonation chamber (2, 2A, 2B) in order to be able to supply it with air (F1); and means (6) for injecting fuel into said detonation chamber (2, 2A, 2B), wherein: said detonation chamber (2, 2A, 2B) is annular and of the continuous detonation wave type; said fuel injection means (6) are formed for continuously injecting fuel (F2) directly into said detonation chamber just downstream of said air injection base; and the injection of fuel and the injection of air into said detonation chamber are carried out continuously separately from one another in the course of operation of said ramjet (S1, S2, S3). ### Claim 2 (depends on 1) Ramjet according to claim 1, wherein it also comprises an air injection system (7) which is interposed between said air inlet (5) and said detonation chamber (2, 2A, 2B) and which comprises at least one channel (8), for example in the form of an annular slot, which opens into said detonation chamber in order to supply it with air. ### Claim 3 (depends on 1) Ramjet according to claim 1, wherein it comprises means (13) for local control of the flow of fresh air entering said detonation chamber (2, 2A, 2B). ### Claim 4 (depends on 1) Ramjet according to claim 1, wherein it comprises at least one circuit (14) for cooling of said detonation chamber (2A, 2B) in which fuel (F2) can circulate before its injection therein. ### Claim 5 (depends on 4) Ramjet according to claim 4, wherein said cooling circuit (14) extends along at least one side wall of said detonation chamber (2A, 2B), over at least a portion of the length thereof. ### Claim 6 (depends on 1) Ramjet according to of claim 1, wherein said exhaust nozzle (4) has no sonic throat. ### Claim 7 (depends on 1) Ramjet according to of claim 1, wherein said fuel injection means comprise at least four supply units (6) regularly distributed along the circumference of said detonation chamber (2, 2A, 2B), of which the associated fuel flows are either identical, or different, or modifiable over time independently of one another. ### Claim 8 (depends on 7) Ramjet according to claim 7, wherein: said diametrically opposite supply units (6) are coupled two by two; and the fuel supply flow of said coupled supply units is controlled by means of a variable-flow distributor (12). ### Claim 9 (depends on 1) Ramjet according to claim 1, wherein: it comprises at least two concentric detonation chambers (2A, 2B) of the continuous detonation wave type capable of being continuously supplied with air; and said fuel injection means (6) are formed for continuously injecting fuel (F2) directly into at least one of said concentric detonation chambers (2A, 2B). ### Claim 10 (depends on 1) Ramjet according to any one of claim 1, wherein said air intake (5) is axially symmetrical. ### Claim 11 (depends on 1) Aircraft, wherein it comprises at least one ramjet (S1, S2, S3) of the type specified in claim 1.