| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 241 | SEAL FOR PULSE DETONATION ENGINE | US11560600 | 2006-11-16 | US20090120059A1 | 2009-05-14 | Bobby W. Sanders; Charlotte A. Sanders; Lois J. Weir |
| A system of controlling airflow into a pulse detonation engine includes a rotary airflow controller valve receiving air from a high-speed inlet. An engine frame includes a plurality of detonation chambers. A sealing mechanism is between the rotary airflow controller valve and the engine frame. The sealing mechanism is associated with the engine frame and limits leakage of a gas from a first of the detonation chambers to a second of the detonation chambers. | ||||||
| 242 | Pulse detonation engines and components thereof | US11262652 | 2005-10-31 | US07526912B2 | 2009-05-05 | Venkat Eswarlu Tangirala; Adam Rasheed; Christian Lee Vandervort; Anthony John Dean |
| A pulse detonation engine comprises a primary air inlet; a primary air plenum located in fluid communication with the primary air inlet; a secondary air inlet; a secondary air plenum located in fluid communication with the secondary air inlet, wherein the secondary air plenum is substantially isolated from the primary air plenum; a pulse detonation combustor comprising a pulse detonation chamber, wherein the pulse detonation chamber is located downstream of and in fluid communication with the primary air plenum; a coaxial liner surrounding the pulse detonation combustor defining a cooling plenum, wherein the cooling plenum is in fluid communication with the secondary air plenum; an axial turbine assembly located downstream of and in fluid communication with the pulse detonation combustor and the cooling plenum; and a housing encasing the primary air plenum, the secondary air plenum, the pulse detonation combustor, the coaxial liner, and the axial turbine assembly. | ||||||
| 243 | Pulse detonation engine system for driving turbine | US10511906 | 2004-02-10 | US07367194B2 | 2008-05-06 | 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). | ||||||
| 244 | Pulse detonation engines and components thereof | US11262652 | 2005-10-31 | US20080006019A1 | 2008-01-10 | Venkat Tangirala; Adam Rasheed; Christian Vandervort; Anthony Dean |
| A pulse detonation engine comprises a primary air inlet; a primary air plenum located in fluid communication with the primary air inlet; a secondary air inlet; a secondary air plenum located in fluid communication with the secondary air inlet, wherein the secondary air plenum is substantially isolated from the primary air plenum; a pulse detonation combustor comprising a pulse detonation chamber, wherein the pulse detonation chamber is located downstream of and in fluid communication with the primary air plenum; a coaxial liner surrounding the pulse detonation combustor defining a cooling plenum, wherein the cooling plenum is in fluid communication with the secondary air plenum; an axial turbine assembly located downstream of and in fluid communication with the pulse detonation combustor and the cooling plenum; and a housing encasing the primary air plenum, the secondary air plenum, the pulse detonation combustor, the coaxial liner, and the axial turbine assembly. | ||||||
| 245 | Detonation damper for pulse detonation engines | US10452422 | 2003-05-30 | US20040237504A1 | 2004-12-02 | Pierre Francois Pinard; Anthony John Dean; Adam Rasheed |
| An engine includes at least one pulse detonation chamber configured to receive and detonate a fuel and an oxidizer. The pulse detonation chamber has an outlet end and includes a porous liner adapted to fit within an inner surface of the pulse detonation chamber within a vicinity of the outlet end. The engine also includes a casing housing the pulse detonation chamber. | ||||||
| 246 | Plenum air preheat for cold startup of liquid-fueled pulse detonation engine | JP2009235261 | 2009-10-09 | JP2011080448A | 2011-04-21 | JOSHI NARENDRA DIGAMBER; TANGIRALA VENKAT ESWARLU; HINCKLEY KEVIN MICHAEL |
| PROBLEM TO BE SOLVED: To solve such a problem that startup of operation of a combustor may be difficult, particularly, in a low temperature environment, in use of a pulse detonation engine/combustor. SOLUTION: A power generation system includes: a compressor stage; a pre-burner stage; a combustor stage; and a turbine stage. The pre-burner stage heats a part of a fluid flow from the compressor stage to give the inside of the fluid flow a higher temperature. The heated fluid flow is guided to the combustor stage including at least one pulse detonation combustor. The turbine stage is disposed downstream of the burner stage. In another embodiment of the power generation system, fuel is heated before combustion in the combuster stage. COPYRIGHT: (C)2011,JPO&INPIT | ||||||
| 247 | Multi-hole fine tube plate for supplying fuel oxidizing agent for pulse detonation engine | JP2000258181 | 2000-07-24 | JP2002039012A | 2002-02-06 | KASAHARA JIRO; ARAI TAKAKAGE; NAGATA HARUNORI; MATSUO AKIKO |
| PROBLEM TO BE SOLVED: To solve the following problems: An operating frequency of a fuel oxidizing agent supply valve in a pulse detonation engine limits performance of the engine. When the detonation wave is ignited without using a bulb, because the detonation wave propagates in the flow direction of the fuel and the oxidizing agent, efficiency is lowered and fuel and oxidizing agent are discharged in the exhaust period of the burnt fuel. Because mixing of the fuel and oxidizing agent having ultrasonic relative velocity is easy to become insufficient, detonation waves are not generated. SOLUTION: The oxidization agent supply plate separately injects fuel and oxidizing agent from a number of fuel holes having a complicated shape for promoting the mixing of the fuel and oxidizing agent, and serves as a plate for receiving rearward pressure of the detonation wave. COPYRIGHT: (C)2002,JPO | ||||||
| 248 | INTEGRATED PULSE DETONATION ENGINE IN A LIFTING SURFACE WITH SUPERCIRCULATION | PCT/US2006032057 | 2006-08-17 | WO2007022315A3 | 2007-06-14 | GUTMARK EPHRAIM JEFF; ALLGOOD DANIEL CLAY |
| An integrated aircraft propulsion system includes a pulse detonation engine integrated with a lifting surface to achieve supercirculation. The exhaust from the pulse detonation engine is expelled in a rearward direction tangentially to the lifting surface and is deflected at least partially around the trailing edge of the lifting surface. The circulation-controlled lifting surface provides augmented lift, reduced drag, and an efficient propulsion system through supercirculation and thrust vector control capability, hi a delta wing, a pulse detonation engine can be used to power one or more control jets, located near the apex or the trailing edge of the wing, for controlling vortex breakdown of the vortices created by the leading edge of the delta wing. | ||||||
| 249 | IMPROVED ROTARY VALVE MULTIPLE COMBUSTOR PULSE DETONATION ENGINE | PCT/US1994004101 | 1994-04-14 | WO1994024427A1 | 1994-10-27 | ADROIT SYSTEMS, INC.; BUSSING, Thomas, R., A. |
| A pulse detonation engine is provided with several detonation combustors (10) selectively coupled to an air inlet (20) and fuel source (31) by a rotary valve (50). The rotary valve (50) isolates the steady operation of the air inlet (20) and fuel system (30) from the unsteady nature of the detonation process, and allows the fueling of some of the detonation chambers (10) while detonation occurs in the other detonation chambers (10). The fuel system (30) can use a solid fueled gas generator. | ||||||
| 250 | INTERNAL DETONATION ENGINE, HYBRID ENGINES INCLUDING THE SAME, AND METHODS OF MAKING AND USING THE SAME | EP13823051 | 2013-07-19 | EP2877716A4 | 2015-08-12 | LEE BRENT WEI-TEH |
| 251 | Pulse Detonation Engine with Variable Control Piezoelectric Fuel Injector | US14691255 | 2015-04-20 | US20150316001A1 | 2015-11-05 | Paul Reynolds; Robert Andrew Banks |
| A pulse detonation engine including one or more fuel injectors comprising one or more piezoelectric driving stacks wherein a flow control member of each injector is driven directly by the one or more piezoelectric stacks without additional amplification means or interposing elements while a flow area of the nozzle is variably adjustable to deliver controlled flow rates in a desired flow profile to improve engine performance and reduce emissions. The pulse detonation engine configured to support variable mission and operational requirements including delivery of required thrust using specific fuel types and with power and performance of the pulse detonation engine variably adaptable. The fuel injectors associated with the pulse detonation engine configure to deliver specified flow rates with minimal linear movement of the flow control member. The injector and drive electronics configured to deliver higher frequency operation and response with increased operational stability. | ||||||
| 252 | Methods and apparatus for controlling air flow within a pulse detonation engine | US11348869 | 2006-02-07 | US07980056B2 | 2011-07-19 | Adam Rasheed; Anthony John Dean |
| A flow control device for use with a pulse detonation chamber including an inlet coupled in flow communication with a source of compressed air. The inlet extends at least partially into the chamber to facilitate controlling air flow into the chamber. The device also includes a body portion extending downstream from and circumferentially around the inlet, wherein the body portion is positioned in flow communication with the inlet. | ||||||
| 253 | Swirling flows and swirler to enhance pulse detonation engine operation | US11304411 | 2005-12-15 | US20070137171A1 | 2007-06-21 | David Chapin; Anthony Dean; Christian Vandervort; Venkat Tangirala; Edward Furlong |
| A swirler having cross-sectional area comparable to the area of a detonation chamber is placed upstream of the detonation chamber to enhance the fuel-air mixing. The swirler has a first region and a second region, each of which induces swirl in the flow through the swirler. Each region induces a different direction of swirl in the flow. The residual net swirl present in the flow downstream of the swirler is controlled by the relative properties of each region of the swirler. The swirler also provides high optical blockage to inhibit the upstream propagation of flow due to the detonation shockwave. | ||||||
| 254 | Pulse detonation engine having a scroll ejector attenuator | US13650523 | 2012-10-12 | US09021783B2 | 2015-05-05 | James D. Hill; Michael J. Cuozzo |
| The engine (10) includes at least one firing tube (12) wherein an exhaust stream (32) from the firing tube (12) drives a turbine (30). A scroll ejector attenuator (40) is secured between and in fluid communication with an outlet end (28) of the firing tube (12) and an inlet (76) of the turbine (30). The attenuator (40) defines a turning, narrowing passageway (72) that extends a distance the exhaust stream (32) travels before entering the turbine (30) to attenuate shockwaves and mix the pulsed exhaust stream (32) into an even stream with minimal temperature differences to thereby enhance efficient operation of the turbine (30) without any significant pressure decline of exhaust stream (32) pressure and without any backpressure from the attenuator (40) on the firing tube (12). | ||||||
| 255 | PULSE DETONATION ENGINE HAVING A SCROLL EJECTOR ATTENUATOR | US13650523 | 2012-10-12 | US20140311121A1 | 2014-10-23 | James D. HILL; Michael J. CUOZZO |
| The engine (10) includes at least one firing tube (12) wherein an exhaust stream (32) from the firing tube (12) drives a turbine (30). A scroll ejector attenuator (40) is secured between and in fluid communication with an outlet end (28) of the firing tube (12) and an inlet (76) of the turbine (30). The attenuator (40) defines a turning, narrowing passageway (72) that extends a distance the exhaust stream (32) travels before entering the turbine (30) to attenuate shockwaves and mix the pulsed exhaust stream (32) into an even stream with minimal temperature differences to thereby enhance efficient operation of the turbine (30) without any significant pressure decline of exhaust stream (32) pressure and without any backpressure from the attenuator (40) on the firing tube (12). | ||||||
| 256 | Pulse detonation engine bypass and cooling flow with downstream mixing volume | US11561155 | 2006-11-17 | US07841167B2 | 2010-11-30 | Adam Rasheed; Anthony John Dean; Peirre Francois Pinard; Christian Lee Vandervort; Venkat Eswarlu Tangirala |
| An engine contains at least one pulse detonation combustor which is surrounded by a bypass flow air duct, through which bypass air flow is directed. The bypass air duct contains at least one converging-diverging structure to dampen or choke the upstream propagation of shock waves from the pulse detonation combustor through the bypass flow air duct. The bypass air also serves to cool the outer surfaces of the pulse detonation combustor. The bypass air flow is controlled in tandem with the heat release from the PDC to provide the appropriate amount of thermal energy to a downstream energy conversion device, such as a turbine. A mixing plenum is positioned downstream of the pulse detonation combustor and bypass flow air duct. | ||||||
| 257 | Method of magnetohydrodynamic flow control for pulse detonation engines | US10266434 | 2002-10-08 | US06751943B2 | 2004-06-22 | Gregory Vincent Meholic; William Randolph Stowell |
| Flow control in pulse detonation engines is accomplished using magnetohydrodynamic principles. The pulse detonation engine includes a tube having an open forward end and an open aft end and a fuel-air inlet formed in the tube at the forward end. An igniter is disposed in the tube at a location intermediate the forward end and the aft end. A magnetohydrodynamic flow control system is located between the igniter and the fuel-air inlet for controlling detonation in the tube forward of the igniter. The magnetohydrodynamic flow control system utilizes magnetic and electric fields forward of the igniter to dissipate or at least reduce the ignition potential of the forward traveling detonation flame front. | ||||||
| 258 | Magnetohydrodynamic flow control for pulse detonation engines | US09756895 | 2001-01-09 | US06484492B2 | 2002-11-26 | Gregory Vincent Meholic; William Randolph Stowell |
| Flow control in pulse detonation engines is accomplished using magnetohydrodynamic principles. The pulse detonation engine includes a tube having an open forward end and an open aft end and a fuel-air inlet formed in the tube at the forward end. An igniter is disposed in the tube at a location intermediate the forward end and the aft end. A magnetohydrodynamic flow control system is located between the igniter and the fuel-air inlet for controlling detonation in the tube forward of the igniter. The magnetohydrodynamic flow control system utilizes magnetic and electric fields forward of the igniter to dissipate or at least reduce the ignition potential of the forward traveling detonation flame front. | ||||||
| 259 | Rotary valve multiple combustor pulse detonation engine | US206162 | 1994-03-07 | US5353588A | 1994-10-11 | Bussing T. Richard |
| 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. | ||||||
| 260 | SYSTEM AND METHOD FOR CONTROLLING A PULSE DETONATION ENGINE | US12956868 | 2010-11-30 | US20120131901A1 | 2012-05-31 | Eric Richard Westervelt; Narendra Digamber Joshi; Adam Rasheed; Venkat Eswarlu Tangirala |
| In one embodiment, a pulse detonation engine (PDE) includes a controller configured to receive signals indicative of at least one of a desired operating parameter of the PDE and a measured internal parameter of the PDE, and to adjust at least one of a first fluid flow through the PDE and a second fluid flow through at least one of multiple pulse detonation tubes disposed within the PDE based on the signals. The PDE does not include a turbine or a mechanical compressor. | ||||||
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