| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 221 | Hybrid piston-pulsed detonation engine | US10706192 | 2003-11-12 | US06978616B1 | 2005-12-27 | Frederick R. Schauer |
| A hybrid piston engine-pulsed detonation engine structure is provided for obtaining shaft power from a pulsed detonation engine wherein a piston engine operatively connected to a PDE. A deflagration to detonation transition is used to achieve detonations. The piston engine has a piston that is located in the deflagration region of the deflagration to detonation transition. The hybrid engine has a critical starting frequency, above which the engine will self-actuate and produce excess power. | ||||||
| 222 | Pulse detonation engine having an aerodynamic valve | US10603845 | 2003-06-25 | US20040000134A1 | 2004-01-01 | David E. Tew; Wendell V. Twelves JR. |
| A pulse detonation engine (10) is provided with an aerovalve (14) for controlling the pressure of injected propellants (Ox, Fuel) in an open-ended detonation chamber (26). The propellants are injected at such pressure and velocity, and in a direction generally toward a forward thrust wall end (16) of the detonation chamber (26), an aerovalve (14) is formed which effectively inhibits or prevents egress of the propellant from the detonation chamber (26). A shock wave (34) formed by the injected propellant acts, after reflection by the thrust wall end (16) and in combination with the aerovalve (14), to compress and conserve, or increase, the pressure of the injected propellant. Carefully timed ignition (28) effects a detonation pulse under desired conditions of maintained, or increased, pressure. Termination of the propellant injection serves to nullopennull the aerovalve (14), and exhaust of the combusted propellants occurs to produce thrust. Alternate embodiments of propellant injection mechanisms (12, 112) provide pulse valves (24, 122, 124) each having a fixed slotted disk (40, 140, 240) and a rotating slotted disk (42, 142, 242) to provide the desired high speed valving of discrete pulses of propellant for injection. | ||||||
| 223 | Rotary valve multiple combustor pulse detonation engine | US205505 | 1994-03-04 | US5513489A | 1996-05-07 | Thomas R. A. Bussing |
| A pulse detonation engine is provided with at least one detonation combustor selectively coupled to an air inlet and fuel source. The detonation combustors are equipped with either active or passive means to dissipate the heat of detonation. Fuel, air, and an oxidizer can be fed to said detonation combustors either through a rotary valve or through a conically shaped injector head. | ||||||
| 224 | Rotary valve multiple combustor pulse detonation engine | US045771 | 1993-04-14 | US5345758A | 1994-09-13 | Thomas R. Bussing |
| A pulse detonation engine is provided with several detonation combustors selectively coupled to an air inlet and fuel source by a rotary valve. The rotary valve isolates the steady operation of the air inlet and fuel system from the unsteady nature of the detonation process, and allows the fueling of some of the detonation chambers while detonation occurs in other detonation chambers. The fuel system may use a solid fueled gas generator. | ||||||
| 225 | INLET MANIFOLD FOR MULTI-TUBE PULSE DETONATION ENGINE | US15109049 | 2014-12-19 | US20160326956A1 | 2016-11-10 | James D. Hill; Michael J. Cuozzo |
| An inlet manifold for a multi-tube pulse detonation engine includes a vaneless diffuser disposed in a first zone to collect an air discharged from a compressor; a vaned diffuser including a plurality of guide vanes disposed in a second zone to slow the air from the compressor; a plenum disposed in a third zone located next to second zone to provide the air from the compressor to chambers; and a splitter disposed in a fourth zone to split the air from the compressor into an airflow required by each pulse detonation tube for detonation. | ||||||
| 226 | HELICAL CROSS FLOW (HCF) PULSE DETONATION ENGINE | US13886030 | 2013-05-02 | US20130263569A1 | 2013-10-10 | Daniel P. Guinan; Christopher D. Gettinger |
| A helical cross flow pulse detonation engine. | ||||||
| 227 | Timing control system for pulse detonation engines | US11651188 | 2007-01-08 | US08015792B2 | 2011-09-13 | Bernard J. Raver |
| An engine timing input system is described for pulse detonation engines that allows for accurate engine timing when rotary or cylindrical valves are used to distribute an air/fuel mixture for combustion. The invention uses a profile disk having a predetermined circumferential edge corresponding to valve position to provide for accurate engine timing. A frequency wheel is used in conjunction with the profile disk to provide a more accurate representation of valve position by partitioning the valve position into multiple pulses during each rotation of the rotary or cylindrical valve. The profile disk and frequency wheel when used with programmable timing circuitry signal fuel valve timing and ignition relative to the rotating valve. | ||||||
| 228 | HELICAL CROSS FLOW (HCF) PULSE DETONATION ENGINE | US12414281 | 2009-03-30 | US20100242435A1 | 2010-09-30 | Daniel P. Guinan; Christopher Gettinger |
| A helical cross flow pulse detonation engine. | ||||||
| 229 | PULSE DETONATION ENGINE OPERATING WITH AN AIR-FUEL MIXTURE | US12667486 | 2008-06-19 | US20100186370A1 | 2010-07-29 | Emeric Daniau; Francois Falempin; Etienne Bobo; Jean-Pierre Minard |
| The invention relates to a pulse detonation engine operating with an air-fuel mixture. According to the invention, the engine (1) includes at least two predetonation tubes (4, 5) which operate under conditions close to thermal cutoff conditions and the shock waves from which are focused in the combustion chamber (19). | ||||||
| 230 | Performance improvements for pulse detonation engines | US11509311 | 2006-08-24 | US20090320446A1 | 2009-12-31 | Ephraim J. Gutmark; Daniel C. Allgood |
| A device and method for improving the performance of a pulse detonation engine. The device includes at least one of an exhaust structure and an ejector. The exhaust structure can be configured as a straight, converging or diverging nozzle device, and connected to the engine to control the flow of a primary fluid produced during a detonation reaction. The ejector is fluidly coupled to the engine, using the movement of the primary fluid to promote entrainment of a secondary fluid that can be mixed with the primary fluid. The secondary fluid can be used to increase the mass flow of the primary fluid to increase thrust, as well as be used to cool engine components. Device positioning, sizing, shaping and integration with other engine operating parameters, such as fill fraction, choice of fuel and equivalence ratio, can be used to improve engine performance. In addition to thrust augmentation and enhanced cooling, the disclosed device can be used for engine noise reduction. | ||||||
| 231 | Pulse detonation engine system for driving turbine | US10511906 | 2004-02-10 | US20050210879A1 | 2005-09-29 | Motohide Murayama; Shigemichi Yamawaki; Hidemi Toh; Hideo Kobayashi; Katsuyoshi Takahashi; Kaoru Chiba; Shigeharu Ohyagi |
| A pulse detonation engine system (1) for driving a turbine is comprises a detonation generator section (5) including a detonation tube (7) having a tubular hollow section for permitting detonation to be generated therein during combustion stage of a mixture gas combined with a gas and a fuel, a gas supply section (17) for feeding the gas into the tubular hollow section of the detonation tube (7) at given time intervals, a fuel valve (19) for feeding the fuel into the tubular hollow section of the detonation tube (7) at the given time intervals, and an ignition plug (15) for igniting the mixture gas in the tubular hollow section of the detonation tube (7), and a pulse detonation driven turbine (9) driven directly or indirectly by energy of detonations that are intermittently generated in the tubular hollow section of the detonation tube (7). | ||||||
| 232 | Pulse detonation engine having an aerodynamic valve | US10603845 | 2003-06-25 | US06883543B2 | 2005-04-26 | David E. Tew; Wendell V. Twelves, Jr. |
| A pulse detonation engine (10) is provided with an aerovalve (14) for controlling the pressure of injected propellants (Ox, Fuel) in an open-ended detonation chamber (26). The propellants are injected at such pressure and velocity, and in a direction generally toward a forward thrust wall end (16) of the detonation chamber (26), an aerovalve (14) is formed which effectively inhibits or prevents egress of the propellant from the detonation chamber (26). A shock wave (34) formed by the injected propellant acts, after reflection by the thrust wall end (16) and in combination with the aerovalve (14), to compress and conserve, or increase, the pressure of the injected propellant. Carefully timed ignition (28) effects a detonation pulse under desired conditions of maintained, or increased, pressure. Termination of the propellant injection serves to “open” the aerovalve (14), and exhaust of the combusted propellants occurs to produce thrust. Alternate embodiments of propellant injection mechanisms (12, 112) provide pulse valves (24, 122, 124) each having a fixed slotted disk (40, 140, 240) and a rotating slotted disk (42, 142, 242) to provide the desired high speed valving of discrete pulses of propellant for injection. | ||||||
| 233 | Pulse detonation engine having an aerodynamic valve | US10026236 | 2001-12-21 | US06584765B1 | 2003-07-01 | David E. Tew; Torger J. Anderson; Roy N. Guile; David R. Sobel; Wendell V. Twelves, Jr.; Gary D. Jones |
| A pulse detonation engine (10) is provided with an aerovalve (14) for controlling the pressure of injected propellants (Ox, Fuel) in an open-ended detonation chamber (26). The propellants are injected at such pressure and velocity, and in a direction generally toward a forward thrust wall end (16) of the detonation chamber (26), an aerovalve (14) is formed which effectively inhibits or prevents egress of the propellant from the detonation chamber (26). A shock wave (34) formed by the injected propellant acts, after reflection by the thrust wall end (16) and in combination with the aerovalve (14), to compress and conserve, or increase, the pressure of the injected propellant. Carefully timed ignition (28) effects a detonation pulse under desired conditions of maintained, or increased, pressure. Termination of the propellant injection serves to “open” the aerovalve (14), and exhaust of the combusted propellants occurs to produce thrust. Alternate embodiments of propellant injection mechanisms (12, 112) provide pulse valves (24, 122, 124) each having a fixed slotted disk (40, 140, 240) and a rotating slotted disk (42, 142, 242) to provide the desired high speed valving of discrete pulses of propellant for injection. | ||||||
| 234 | Rotary valve for pulse detonation engines | US09821274 | 2001-03-29 | US20020139106A1 | 2002-10-03 | Gregory Vincent Meholic |
| A rotary valve for pulse detonation engines includes a rotor rotatively mounted in the forward end of the pulse detonation tube and a plurality of transfer plenums for receiving fuel and air arranged around the rotor and partially disposed over the forward end of the tube. The rotor has a plurality of internal flow passages formed therein which periodically align with a plurality of inlet ports formed near the forward end of the tube as the rotor rotates. Each one of the transfer plenums is aligned with a corresponding one of the inlet ports so that the flow passages will establish fluid communication between the tube and the transfer plenums when aligned with the inlet ports. Additional features include axial injection of the fuel-air mixture into the pulse detonation tube, pre-compression of the inlet flow and a drive system located outside of the primary gas path. | ||||||
| 235 | Annular liquid fueled pulse detonation engine | US09593068 | 2000-06-13 | US06349538B1 | 2002-02-26 | Louis G. Hunter, Jr.; Kent W. Benner |
| A pulse detonation engine has an inner tubular housing rigidly and concentrically mounted within a cylindrical bore of an outer tubular housing. The inner housing has a plurality of inner housing ports, and the outer housing has a plurality of outer housing ports. A detonation chamber is formed in the annulus between the inner housing and the outer housing. In one embodiment, an outer valve sleeve is rotatably mounted to the outer housing for selectively allowing air to enter the detonation chamber through the outer housing ports. A movable, inner protective sleeve is mounted to the inner housing for protecting a plurality of fuel injectors that supply liquid fuel to the detonation chamber through the inner housing ports. The air and liquid fuel mixture is detonated by several igniters located in the detonation chamber. In a second embodiment, an inner valve sleeve is rotatably mounted to the inner housing for selectively allowing air to enter the detonation chamber through the inner housing ports. A movable, outer protective sleeve is mounted to the outer housing for protecting a plurality of fuel injectors that supply liquid fuel to the detonation chamber through the outer housing ports. The air and liquid fuel mixture is detonated by several igniters located in the detonation chamber. The detonation for both embodiments creates a detonation wave that travels through an open downstream end of the detonation chamber, thereby creating thrust for the engine. | ||||||
| 236 | PERFORMANCE IMPROVEMENTS FOR PULSE DETONATION ENGINES USING EJECTORS | PCT/US2006033080 | 2006-08-24 | WO2007025047A3 | 2007-10-11 | GUTMARK EPHRAIM J; ALLGOOD DANIEL C |
| A device and method for improving the performance of a pulse detonation engine (10) . The device includes at least one of an exhaust structure and an ejector (300) . The exhaust structure can be configured as a straight (70) , converging (100) or diverging (200) nozzle device, and connected to the engine to control the flow of a primary fluid (25) produced during a detonation reaction. The ejector is fluidly coupled to the engine, using the movement of the primary fluid to promote entrainment of a secondary fluid (95) that can be mixed with the primary fluid. The secondary fluid can be used to increase the mass flow of the primary fluid to increase thrust, as well as be used to cool engine components. Device positioning, sizing, shaping and integration with other engine operating parameters, such as fill fraction, choice of fuel and equivalence ratio, can be used to improve engine performance. In addition to thrust augmentation and enhanced cooling, the disclosed device can be used for engine noise reduction. | ||||||
| 237 | Pulse detonation engine operating with an air-fuel mixture | US12667486 | 2008-06-19 | US08516788B2 | 2013-08-27 | Emeric Daniau; François Falempin; Etienne Bobo; Jean-Pierre Minard |
| The invention relates to a pulse detonation engine operating with an air-fuel mixture. According to the invention, the engine (1) includes at least two predetonation tubes (4, 5) which operate under conditions close to thermal cutoff conditions and the shock waves from which are focused in the combustion chamber (19). | ||||||
| 238 | ENHANCED PULSE DETONATION ENGINE SYSTEM | US13591393 | 2012-08-22 | US20130047625A1 | 2013-02-28 | William Donald Eatwell |
| An enhanced pulse detonation engine (PDE) system for application in an aircraft capable of vertical takeoff and vertical landing (VTOVL) is described. The PDE system described herein may be installed onto a round vehicle platform whereby many PDE chamber and ejector tube assemblies are mounted with the ejector tubes facing towards a rotating bladed fan which, in certain embodiments, provides VTOVL flight and gyro stabilization. The angle and design of the fan blades are such that when the fan is rotated by exhaust force, the fan pulls fresh air through the aircraft's interior ducting, cooling the assemblies and adding more air mass for lift. Ignition rotation is adjustable (with or opposite fan rotation) to maximize the fan's thrust output. The design of the fan blade angle is optimized to provide low acoustical detection, low exhaust thrust temperature signature, and maximum air pull-through for lift. | ||||||
| 239 | MULTITUBE VALVELESS PULSE DETONATION ENGINE | US13160840 | 2011-06-15 | US20110302908A1 | 2011-12-15 | Soheil Farshchian; Alejandro Juan |
| Disclosed herein is a valveless multitube pulse detonation engine including: a plurality of detonation tubes, wherein each detonation tube comprises an independent discharge outlet, and the plurality of detonation tubes interconnected at a common air/fuel mixture intake port. In the disclosed engine, an air and fuel mixture is detonated in the detonation tubes simultaneously, and the common air/fuel mixture intake port minimizes back-pressure caused by detonating the air/fuel mixture by directing multiple reverse shock waves into one another and effectively using the back-pressures as reacting surfaces for one another and effectively reducing the effect of back flowing shock waves moving towards upstream. The detonation tubes may be non-linear, and may have independent discharges. The independent discharges may be coupled to an adapter nozzle terminating in a combined exhaust outlet. | ||||||
| 240 | Timing control system for pulse detonation engines | US11651188 | 2007-01-08 | US20100229529A1 | 2010-09-16 | Bernard J. Raver |
| An engine timing input system is described for pulse detonation engines that allows for accurate engine timing when rotary or cylindrical valves are used to distribute an air/fuel mixture for combustion. The invention uses a profile disk having a predetermined circumferential edge corresponding to valve position to provide for accurate engine timing. A frequency wheel is used in conjunction with the profile disk to provide a more accurate representation of valve position by partitioning the valve position into multiple pulses during each rotation of the rotary or cylindrical valve. The profile disk and frequency wheel when used with programmable timing circuitry signal fuel valve timing and ignition relative to the rotating valve. | ||||||
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