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公开(公告)号：US20120204531A1
公开(公告)日：2012-08-16
申请号：US13454246
申请日：2012-04-24
IPC分类号： F02C7/22
CPC分类号： C06D5/00 , F23C13/06 , F23R3/36 , F23R3/40 , Y02E20/344
摘要： A combustion system for performing stable combustion and flame stabilization at high altitudes is described. A primary liquid hydrocarbon fuel is atomized and vaporized within the main combustor chamber to produce a primary fuel vapor. When the combustion system operates at a high altitude, a secondary gaseous fuel is fed into the inlet air port such that the secondary fuel mixes with air, thereby enabling the mixture of the air and the secondary fuel to combust in a catalytic reactor to produce high temperature, oxygen-rich gases that flow into the main combustor chamber. Proper proportional amounts of the two fuels are determined as a function of altitude.
摘要翻译： 描述了一种用于在高海拔地区进行稳定燃烧和火焰稳定的燃烧系统。 主要的液体烃燃料在主燃烧器室内被雾化和蒸发以产生主燃料蒸气。 当燃烧系统在高空作业时，二次气体燃料被供给到入口空气口中，使得二次燃料与空气混合，从而使空气和二次燃料的混合物在催化反应器中燃烧以产生高 温度，富氧气体流入主燃烧室。 确定两种燃料的适当比例量作为高度的函数。
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公开(公告)号：US20110056184A1
公开(公告)日：2011-03-10
申请号：US12556202
申请日：2009-09-09
IPC分类号： C06D5/04
CPC分类号： C06D5/00 , F23C13/06 , F23R3/36 , F23R3/40 , Y02E20/344
摘要： A combustion system for performing stable combustion and flame stabilization at high altitudes is described. A primary liquid hydrocarbon fuel is atomized and vaporized within the main combustor chamber to produce a primary fuel vapor. When the combustion system operates at a high altitude, a secondary gaseous fuel is fed into the inlet air port such that the secondary fuel mixes with air, thereby enabling the mixture of the air and the secondary fuel to combust in a catalytic reactor to produce high temperature, oxygen-rich gases that flow into the main combustor chamber. Proper proportional amounts of the two fuels are determined as a function of altitude.
摘要翻译： 描述了一种用于在高海拔地区进行稳定燃烧和火焰稳定的燃烧系统。 主要的液体烃燃料在主燃烧器室内被雾化和蒸发以产生主燃料蒸气。 当燃烧系统在高空作业时，二次气体燃料被供给到入口空气口中，使得二次燃料与空气混合，从而使空气和二次燃料的混合物在催化反应器中燃烧以产生高 温度，富氧气体流入主燃烧室。 确定两种燃料的适当比例量作为高度的函数。
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公开(公告)号：US08225613B2
公开(公告)日：2012-07-24
申请号：US12556202
申请日：2009-09-09
CPC分类号： C06D5/00 , F23C13/06 , F23R3/36 , F23R3/40 , Y02E20/344
摘要： A combustion system for performing stable combustion and flame stabilization at high altitudes is described. A primary liquid hydrocarbon fuel is atomized and vaporized within the main combustor chamber to produce a primary fuel vapor. When the combustion system operates at a high altitude, a secondary gaseous fuel is fed into the inlet air port such that the secondary fuel mixes with air, thereby enabling the mixture of the air and the secondary fuel to combust in a catalytic reactor to produce high temperature, oxygen-rich gases that flow into the main combustor chamber. Proper proportional amounts of the two fuels are determined as a function of altitude.
摘要翻译： 描述了一种用于在高海拔地区进行稳定燃烧和火焰稳定的燃烧系统。 主要的液体烃燃料在主燃烧器室内被雾化和蒸发以产生主燃料蒸气。 当燃烧系统在高空作业时，二次气体燃料被供给到入口空气口中，使得二次燃料与空气混合，从而使空气和二次燃料的混合物在催化反应器中燃烧以产生高 温度，富氧气体流入主燃烧室。 确定两种燃料的适当比例量作为高度的函数。
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公开(公告)号：US20090184195A1
公开(公告)日：2009-07-23
申请号：US12323820
申请日：2008-11-26
摘要： An engine for use in operating an aircraft is disclosed, the engine comprising a decomposition chamber configured to decompose into at least one combustible constituent element a first chemically unstable substance in the presence of a catalyst, wherein the decomposition of the first chemically unstable substance releases a first amount of heat; a first turbine configured to accept the constituent elements and the first amount of heat from the decomposition chamber and thereby rotate; a compressor rotationally connected to the first turbine, and configured to compress air when the first turbine rotates; and a combustion chamber configured to accept the compressed air and constituent elements and combust the combination, substantially regardless of an altitude above sea level and ambient air pressure, and output the combustion products into a power turbine, causing it to rotate, whereby the rotation of the first turbine and/or the power turbine rotate a propeller rotationally coupled to the first and power turbines. Alternately, a nozzle can be used in place of the power turbine, thereby creating a jet engine.
摘要翻译： 公开了一种用于操作飞行器的发动机，所述发动机包括分解室，其被配置为在催化剂存在下分解为至少一种可燃组成元素的第一化学不稳定物质，其中所述第一化学不稳定物质的分解释放 第一热量; 第一涡轮机，其构造成接受来自分解室的构成元件和第一量的热量，从而旋转; 压缩机，其旋转地连接到所述第一涡轮机，并且构造成当所述第一涡轮机旋转时压缩空气; 以及燃烧室，其构造成接受压缩空气和组成元件并且燃烧组合，基本上与海拔高度和环境空气压力无关，并且将燃烧产物输出到动力涡轮机中，使得其转动， 第一涡轮机和/或动力涡轮机旋转地旋转地联接到第一和动力涡轮机的螺旋桨。 或者，可以使用喷嘴来代替动力涡轮机，从而形成喷气发动机。
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公开(公告)号：US08500067B2
公开(公告)日：2013-08-06
申请号：US13567015
申请日：2012-08-04
IPC分类号： B64C1/32
CPC分类号： B64C1/30 , A63H27/001 , A63H27/02 , B64C15/00 , B64C19/00 , B64C39/028 , B64C2201/028 , B64C2201/042 , B64C2201/104 , B64C2201/127 , B64C2201/165 , B64C2201/18 , B64C2201/187 , B64C2201/201 , B64D1/14 , B64D9/00 , B64D27/26
摘要： An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.
摘要翻译： 描述了一种无人驾驶飞机。 飞行器包括机身，连接到机身的后部的一对翼片，连接到机身的底部的一对二面支架，第一推力矢量（“T / V”）模块和第二T / V模块，以及电子模块。 电子模块向两个T / V模块提供命令。 两个T / V模块被配置为通过直接控制飞行器的俯仰，滚动和偏航中的每一个的推力矢量来向飞行器提供侧向和纵向控制。 使用直接连接的电动机作为T / V模块，使飞机能够在大范围的空速下执行紧半径的转弯。
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公开(公告)号：US08516818B2
公开(公告)日：2013-08-27
申请号：US13454246
申请日：2012-04-24
IPC分类号： F02C1/00
CPC分类号： C06D5/00 , F23C13/06 , F23R3/36 , F23R3/40 , Y02E20/344
摘要： A combustion system for performing stable combustion and flame stabilization at high altitudes is described. A primary liquid hydrocarbon fuel is atomized and vaporized within the main combustor chamber to produce a primary fuel vapor. When the combustion system operates at a high altitude, a secondary gaseous fuel is fed into the inlet air port such that the secondary fuel mixes with air, thereby enabling the mixture of the air and the secondary fuel to combust in a catalytic reactor to produce high temperature, oxygen-rich gases that flow into the main combustor chamber. Proper proportional amounts of the two fuels are determined as a function of altitude.
摘要翻译： 描述了一种用于在高海拔地区进行稳定燃烧和火焰稳定的燃烧系统。 主要的液体烃燃料在主燃烧器室内被雾化和蒸发以产生主燃料蒸气。 当燃烧系统在高空作业时，二次气体燃料被供给到入口空气口中，使得二次燃料与空气混合，从而使空气和二次燃料的混合物在催化反应器中燃烧以产生高 温度，富氧气体流入主燃烧室。 确定两种燃料的适当比例量作为高度的函数。
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公开(公告)号：US08205827B2
公开(公告)日：2012-06-26
申请号：US12323820
申请日：2008-11-26
IPC分类号： B64D27/00
摘要： An engine for use in operating an aircraft is disclosed, the engine comprising a decomposition chamber configured to decompose into at least one combustible constituent element a first chemically unstable substance in the presence of a catalyst, wherein the decomposition of the first chemically unstable substance releases a first amount of heat; a first turbine configured to accept the constituent elements and the first amount of heat from the decomposition chamber and thereby rotate; a compressor rotationally connected to the first turbine, and configured to compress air when the first turbine rotates; and a combustion chamber configured to accept the compressed air and constituent elements and combust the combination, substantially regardless of an altitude above sea level and ambient air pressure, and output the combustion products into a power turbine, causing it to rotate, whereby the rotation of the first turbine and/or the power turbine rotate a propeller rotationally coupled to the first and power turbines. Alternately, a nozzle can be used in place of the power turbine, thereby creating a jet engine.
摘要翻译： 公开了一种用于操作飞行器的发动机，所述发动机包括分解室，其被配置为在催化剂存在下分解为至少一种可燃组成元素的第一化学不稳定物质，其中所述第一化学不稳定物质的分解释放 第一热量; 第一涡轮机，其构造成接受来自分解室的构成元件和第一量的热量，从而旋转; 压缩机，其旋转地连接到所述第一涡轮机，并且构造成当所述第一涡轮机旋转时压缩空气; 以及燃烧室，其构造成接受压缩空气和组成元件并且燃烧组合，基本上与海拔高度和环境空气压力无关，并且将燃烧产物输出到动力涡轮机中，使得其转动， 第一涡轮机和/或动力涡轮机旋转地旋转地联接到第一和动力涡轮机的螺旋桨。 或者，可以使用喷嘴来代替动力涡轮机，从而形成喷气发动机。
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