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公开(公告)号：WO2013103427A2
公开(公告)日：2013-07-11
申请号：PCT/US2012/060286
申请日：2012-10-15
Applicant: FIRESTAR ENGINEERING, LLC , MUNGAS, Gregory S. , PETERS, Gregory H. , BINGHAM, Andrew T.
Inventor： MUNGAS, Gregory S. , PETERS, Gregory H. , BINGHAM, Andrew T.
Abstract: The presently disclosed linear detonation wave diverter (600) provides a structure and method for quickly and controllably venting a detonation event out of the diverter without igniting working fluid upstream of a microporous barrier (626) within the linear detonation wave diverter. Further, the detonation wave is linearly vented out of the diverter upon the failure of a burst member (682), which provides a low resistance path for detonation waves to exit the detonation wave diverter.
Abstract translation: 目前公开的线性爆震波分流器（600）提供了一种结构和方法，用于快速并可控地将爆震事件排出分流器外而不会点燃线性内的微孔隔板（626）上游的工作流体 爆轰波分流器。 此外，当爆破构件（682）失效时，爆炸波线性地从分流器排出，这为爆震波离开爆轰波分流器提供了低阻力路径。
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公开(公告)号：WO2012149462A2
公开(公告)日：2012-11-01
申请号：PCT/US2012035641
申请日：2012-04-27
Applicant: FIRESTAR ENGINEERING LLC , MUNGAS GREGORY , BUCHANAN LARRY
Inventor： MUNGAS GREGORY , BUCHANAN LARRY
IPC: F01N13/08
CPC classification number: F01N13/082 , F01N13/20 , F01N2260/06 , F01N2270/08 , Y10T137/0329 , Y10T137/2599
Abstract: A throttleable exhaust venturi (700) is described herein that generates strong suction pressures at an exhaust outlet (718) by accelerating an incoming ambient fluid stream with the aid of a venturi to high gas velocities and injecting a combustion exhaust stream into the ambient fluid stream at an effective venturi throat (728). A mixing element (544) downstream of the venturi throat ensures that the mixed fluid stream recovers from a negative static pressure up to local atmospheric pressure. A physical (724) and the effective (728) throat of the venturi (700) are designed to promote mixing and stabilize the ambient fluid flow to ensure that high velocity is achieved and the effective venturi is operable over a variety of combustion exhaust stream mass flow rates.
Abstract translation: 本文描述了一种可节流的排气文丘里管（700），其通过在文氏管的帮助下将进入的环境流体流加速到高气体速度并将燃烧废气流注入到环境流体流中而在排气出口（718）处产生强吸入压力 在有效的文丘里喉咙（728）。 文丘里喉部下游的混合元件（544）确保混合流体流从负静压力恢复到局部大气压力。 文丘里管（700）的物理（724）和有效（728）喉部被设计成促进混合和稳定环境流体流动，以确保实现高速度，并且有效文丘里管可在多种燃烧废气流质量 流量。
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公开(公告)号：WO2014145794A1
公开(公告)日：2014-09-18
申请号：PCT/US2014/030620
申请日：2014-03-17
Applicant: FIRESTAR ENGINEERING, LLC
Inventor： MUNGAS, Gregory S.
Abstract: Implementations described herein provide a high efficiency steam cycle that includes a steam turbine cycle coupled to output of a high performance steam piston topping (HPSPT) cycle. The HPSPT cycle includes a piston-cylinder assembly that extracts work from an expanding fluid volume and operates in a thermal regime outside of thermal operational limits of a steam turbine. The steam turbine cycle utilizes heat, transferred at the output of the HPSPT cycle, to generate turbine work.
Abstract translation: 本文所述的实施方案提供了高效蒸汽循环，其包括耦合到高性能蒸汽活塞顶部（HPSPT）循环的输出的蒸汽轮机循环。 HPSPT循环包括活塞 - 气缸组件，其从膨胀的流体体积中提取工作并且在蒸汽轮机的热操作极限之外的热状态下操作。 蒸汽轮机循环利用在HPSPT循环的输出处传递的热量来产生涡轮机工作。
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公开(公告)号：WO2013105988A3
公开(公告)日：2013-09-26
申请号：PCT/US2012025308
申请日：2012-02-15
Applicant: FIRESTAR ENGINEERING LLC , FISHER DAVID , MUNGAS GREGORY
Inventor： FISHER DAVID , MUNGAS GREGORY
CPC classification number: F02K9/00 , F02K9/58 , F02K9/82 , F02K9/88 , F05D2240/40 , F05D2250/314
Abstract: A clustered, fixed cant, throttleable rocket assembly (102) is used to propel and a steer a vessel (100) in terrestrial or extraterrestrial applications. The fixed cant of each of at least three individual rocket engines (104, 106, 108) in the cluster provides the steering input to the overall assembly (102). More specifically, by changing the propellant flow rate to the individual rocket engines (104, 106, 108) relative to one another, the overall thrust vector of the rocket assembly (102) may be selected to provide a desired steering input to the vessel (100). A measured vessel orientation may be compared with a desired vessel orientation to determine what steering input is required to achieve the desired vessel orientation.
Abstract translation: 聚集的，固定的可倾斜的可节流的火箭组件（102）用于推进和操纵船只（100）在地面或外星应用中。 组中的至少三个单独的火箭发动机（104,106,108）中的每一个的固定倾斜向整个组件（102）提供转向输入。 更具体地，通过改变相对于彼此的各个火箭发动机（104,106,108）的推进剂流量，可以选择火箭组件（102）的总推力矢量以向船只提供期望的转向输入 100）。 测量的血管取向可以与期望的血管取向比较以确定实现期望的血管取向需要什么操纵输入。
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公开(公告)号：WO2013116390A1
公开(公告)日：2013-08-08
申请号：PCT/US2013/023927
申请日：2013-01-30
Applicant: FIRESTAR ENGINEERING, LLC
Inventor： MUNGAS, Gregory
IPC: F02K9/50
Abstract: The presently disclosed technology relates to using a combustion / decomposition heater (214) fed by a working fluid (234) stored within a storage tank (202) to thermally pressurize the storage tank. The thermal pressurization may be used to maintain a desired pressure within the storage tank, even as the working fluid (232) within the storage tank is drawn down. Further, a feedback mechanism may also be incorporated that varies the thermal energy added to the working fluid within the storage tank to maintain the desired pressure within the storage tank.
Abstract translation: 本公开的技术涉及使用由存储在储罐（202）内的工作流体（234）供给的燃烧/分解加热器（214）来对储罐进行热加压。 即使当储存罐内的工作流体（232）被拉下时，也可以使用热加压来保持储罐内的所需压力。 此外，还可以引入反馈机构，其改变添加到储罐内的工作流体的热能，以保持储存罐内所需的压力。
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Patent Agency Ranking
公开(公告)号：WO2013033437A3
公开(公告)日：2013-05-10
申请号：PCT/US2012053196
申请日：2012-08-30
Applicant: FIRESTAR ENGINEERING LLC , MUNGAS GREGORY
Inventor： MUNGAS GREGORY
CPC classification number: F02K9/44 , B64G1/402 , F05D2260/20 , Y10T137/0391 , Y10T137/6416
Abstract: A thermal variation source (318) (e.g., a heater or a heat sink) is used to induce a temperature gradient across an interior surface of a storage tank (302). The storage tank stores a working fluid (e.g., a fuel, and oxidizer, or a monopropellant) that may have pockets of gaseous-phase working fluid interspersed within liquid-phase working fluid, or vice versa. In the absence of gravity or other significant forces on the working fluid, the temperature gradient is sufficient to cause phase-separation of the working fluid and allow either the liquid-phase or the gaseous-phase working fluid to be withdrawn from the storage tank, as desired.
Abstract translation: 使用热变化源（318）（例如，加热器或散热器）以引起横跨储罐（302）的内表面的温度梯度。 储罐储存可能具有散布在液相工作流体内的气相工作流体的小袋的工作流体（例如，燃料和氧化剂，或单一推进剂），反之亦然。 在工作流体上不存在重力或其他显着力的情况下，温度梯度足以引起工作流体的相分离并且允许液相或气相工作流体从储罐中排出， 如预期的。
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公开(公告)号：WO2012149461A3
公开(公告)日：2013-01-24
申请号：PCT/US2012035640
申请日：2012-04-27
Applicant: FIRESTAR ENGINEERING LLC , MUNGAS GREGORY , BUCHANAN LARRY
Inventor： MUNGAS GREGORY , BUCHANAN LARRY
CPC classification number: F01N13/082 , F01N13/20 , F01N2260/06 , F01N2270/08 , Y10T137/0329 , Y10T137/2599
Abstract: A throttleable exhaust venturi (700) is described herein that generates strong suction pressures at an exhaust outlet (718) by accelerating an incoming ambient fluid stream with the aid of a venturi to high gas velocities and injecting a combustion exhaust stream into the ambient fluid stream at an effective venturi throat (728). A mixing element (544) downstream of the venturi throat ensures that the mixed fluid stream recovers from a negative static pressure up to local atmospheric pressure. A physical (724) and the effective (728) throat of the venturi (700) are designed to promote mixing and stabilize the ambient fluid flow to ensure that high velocity is achieved and the effective venturi is operable over a variety of combustion exhaust stream mass flow rates.
Abstract translation: 本文描述了一种可节流的排气文丘里管（700），其通过在文氏管的帮助下将进入的环境流体流加速到高气体速度并将燃烧废气流注入到环境流体流中而在排气出口（718）处产生强吸入压力 在有效的文丘里喉咙（728）。 文丘里喉部下游的混合元件（544）确保混合流体流从负静压力恢复到局部大气压力。 文丘里管（700）的物理（724）和有效（728）喉部被设计成促进混合和稳定环境流体流动，以确保实现高速度，并且有效文丘里管可在多种燃烧废气流质量 流量。
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公开(公告)号：WO2011005891A8
公开(公告)日：2011-12-29
申请号：PCT/US2010041255
申请日：2010-07-07
Applicant: FIRESTAR ENGINEERING LLC , DOYLE KENNETH , FISHER DAVID J , MUNGAS GREGORY S
Inventor： DOYLE KENNETH , FISHER DAVID J , MUNGAS GREGORY S
IPC: A62C4/02
CPC classification number: F02K9/566 , F16K17/366 , F16K17/40 , F23D14/82 , Y10T29/49 , Y10T156/10
Abstract: A flashback-arresting shut-off valve is disclosed herein. Propellant is moved from a propellant reservoir, through the shut-off valve in an open configuration to a point of combustion in a normal propellant flow direction. During a flashback, the propellant is ignited within the propellant line and substantial physical/thermal energy caused by the flashback travels in the direction opposite to the normal propellant flow direction back to the shut-off valve. A burst member within the shut-off valve fails because of the flashback. Failure of the burst member causes compression on a spring-loaded portion of the shut-off valve to be released, thereby closing the shut-off valve and sealing the propellant reservoir from the flashback. Failure of the burst member also causes one or more pressure relief outlets to open that direct the physical/thermal energy and/or un-combusted/combusted propellant out and away from the shut-off valve.
Abstract translation: 本文公开了一种防回流截止阀。 推进剂从推进剂储存器移动，通过截止阀处于打开状态，以正常推进剂流动方向的燃烧点移动。 在闪回期间，推进剂在推进剂管线内点燃，并且由闪回引起的大量物理/热能在与正常推进剂流动方向相反的方向上返回到截止阀。 截止阀内的爆裂构件由于闪回而失效。 突发构件的故障导致截止阀的弹簧加载部分的压缩被释放，从而关闭截止阀并将推进剂储存器从闪回中密封。 爆裂构件的故障还导致一个或多个压力释放出口打开，其将物理/热能和/或未燃烧/燃烧的推进剂引出并远离截止阀。
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公开(公告)号：WO2011005891A1
公开(公告)日：2011-01-13
申请号：PCT/US2010/041255
申请日：2010-07-07
Applicant: FIRESTAR ENGINEERING LLC , DOYLE, Kenneth , FISHER, David, J. , MUNGAS, Gregory, S.
Inventor： DOYLE, Kenneth , FISHER, David, J. , MUNGAS, Gregory, S.
IPC: A62C4/02
CPC classification number: F02K9/566 , F16K17/366 , F16K17/40 , F23D14/82 , Y10T29/49 , Y10T156/10
Abstract: A flashback-arresting shut-off valve is disclosed herein. Propellant is moved from a propellant reservoir, through the shut-off valve in an open configuration to a point of combustion in a normal propellant flow direction. During a flashback, the propellant is ignited within the propellant line and substantial physical/thermal energy caused by the flashback travels in the direction opposite to the normal propellant flow direction back to the shut-off valve. A burst member within the shut-off valve fails because of the flashback. Failure of the burst member causes compression on a spring-loaded portion of the shut-off valve to be released, thereby closing the shut-off valve and sealing the propellant reservoir from the flashback. Failure of the burst member also causes one or more pressure relief outlets to open that direct the physical/thermal energy and/or un- combusted/combusted propellant out and away from the shut-off valve.
Abstract translation: 本文公开了一种防回流截止阀。 推进剂从推进剂储存器移动，通过截止阀处于打开状态，以正常推进剂流动方向的燃烧点移动。 在回火期间，推进剂在推进剂管线内点燃，并且由闪回引起的大量物理/热能在与正常推进剂流动方向相反的方向上返回到截止阀。 截止阀内的爆裂构件由于闪回而失败。 爆裂构件的故障导致截止阀的弹簧加载部分的压缩被释放，从而关闭截止阀并将推进剂储存器从回火中密封。 爆裂构件的故障还导致一个或多个压力释放出口打开，其将物理/热能和/或未燃烧/燃烧的推进剂引出并远离截止阀。
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10.发明申请TIERED POROSITY FLASHBACK SUPPRESSING ELEMENTS FOR MONOPROPELLANT OR PRE-MIXED BIPROPELLANT SYSTEMS 审中-公开用于单面或双组分平板印刷系统的均匀耐压闪光元件
公开(公告)号：WO2011005885A1
公开(公告)日：2011-01-13
申请号：PCT/US2010/041249
申请日：2010-07-07
Applicant: FIRESTAR ENGINEERING LLC , MUNGAS, Gregory, S. , FISHER, David, J. , PETERS, Gregory H. , SMITH, Jon Anthony
Inventor： MUNGAS, Gregory, S. , FISHER, David, J. , PETERS, Gregory H. , SMITH, Jon Anthony
IPC: F02K9/95
CPC classification number: F02K9/566 , F16K17/366 , F16K17/40 , F23D14/82 , Y10T29/49 , Y10T156/10
Abstract: Monopropellant and pre-mixed bipropellant storage and supply systems for rocket engines and other work producing systems are subject to damage when detonation progresses upstream from a combustion chamber to and through supply lines. Interposing one or more micro porous or micro fluidic elements into the supply conduit can limit the flame front that accompanies such unintended detonation, but inevitably restrict the flow of the propellant to the combustion chamber. A tiered micro fluidic element where a bulk of the element has relatively large pores but forms a structurally robust supports a second, relatively thin region having appropriately small mean pore diameter provides an effective flashback barrier that can resist catastrophic failure during such detonations. Such elements can be used in isolation, or they can be incorporated into detonation wave arrestors or pressure wave-triggered cut-off valves or the like to decrease the incidence of unintended detonations.
Abstract translation: 火箭发动机和其他工作生产系统的单组分推进剂和预混合双组分推进剂储存和供应系统在爆炸从燃烧室上游进入和通过供应管路时受到损害。 将一个或多个微孔或微流体元件插入供应管道可以限制伴随这种非预期爆炸的火焰前沿，但是不可避免地限制推进剂到燃烧室的流动。 一种分层的微流体元件，其中大部分元件具有相对较大的孔但形成结构坚固的支撑具有适当小的平均孔径的第二相对较薄的区域提供了可以抵抗在这种爆震期间的灾难性故障的有效回流屏障。 这些元件可以隔离使用，也可以并入爆轰波抑制器或压力波触发截止阀等中，以减少非预期的爆震的发生。
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