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1. 发明申请

US20140182264A1 AIRCRAFT ENGINE SYSTEMS AND METHODS FOR OPERATING SAME 审中-公开
标题翻译：飞机发动机系统及其操作方法
公开(公告)号：US20140182264A1
公开(公告)日：2014-07-03
申请号：US13876863
申请日：2011-09-30
申请人： Robert Harold Weisgerber , Kurt David Murrow , Michael Jay Epstein , Nicholas Dinsmore , Samuel Jacob Martin , Randy M. Vondrell , Christopher Thompson , Craig Gonyou
发明人： Robert Harold Weisgerber , Kurt David Murrow , Michael Jay Epstein , Nicholas Dinsmore , Samuel Jacob Martin , Randy M. Vondrell , Christopher Thompson , Craig Gonyou
IPC分类号： F02C7/22
CPC分类号： F02C7/22 , B64D37/30 , F01D11/24 , F01D25/18 , F02C7/143 , F02C7/16 , F02C7/224 , H05K7/20218 , Y02T50/44 , Y02T50/672 , Y02T50/675
摘要： A gas turbine propulsion system includes a system which utilizes a cryogenic liquid fuel for a non-combustion function.
摘要翻译：燃气轮机推进系统包括利用低温液体燃料用于非燃烧功能的系统。

2. 发明申请

US20130186059A1 DUAL FUEL AIRCRAFT SYSTEM AND METHOD FOR OPERATING SAME 审中-公开
标题翻译：双燃料飞机系统及其操作方法
公开(公告)号：US20130186059A1
公开(公告)日：2013-07-25
申请号：US13876738
申请日：2011-09-30
申请人： Michael Jay Epstein , Kurt David Murrow , Nicholas Rowe Dinsmore , Samuel Martin , Randy Vondrell , Robert Harold Weisgerber , Narendra Digamber Joshi
发明人： Michael Jay Epstein , Kurt David Murrow , Nicholas Rowe Dinsmore , Samuel Martin , Randy Vondrell , Robert Harold Weisgerber , Narendra Digamber Joshi
IPC分类号： F02K9/42
CPC分类号： F02K9/42 , F02C3/22 , F02C7/22 , F02C7/224 , F02C7/236 , F02C9/40 , F05D2260/85 , F05D2270/08 , F05D2270/082 , Y02T50/672 , Y02T50/677
摘要： A dual fuel propulsion system comprising a gas turbine engine configured to generate a propulsive thrust using a cryogenic liquid fuel.
摘要翻译：一种双燃料推进系统，包括配置为使用低温液体燃料产生推进推力的燃气涡轮发动机。

3. 发明授权

US07854111B2 Axial flow positive displacement turbine 有权
标题翻译：轴流式正排量涡轮机
公开(公告)号：US07854111B2
公开(公告)日：2010-12-21
申请号：US12044043
申请日：2008-03-07
申请人： Kurt David Murrow , Rollin George Giffin
发明人： Kurt David Murrow , Rollin George Giffin
IPC分类号： F02C3/02
CPC分类号： F04C2/1073
摘要： An axial flow positive displacement turbine includes inner and outer bodies having offset inner and outer axes respectively extending between a relatively high pressure inlet and a relatively low pressure outlet. At least one of the bodies is rotatable about its axis. The inner and outer bodies have intermeshed inner and outer helical blades wound about the inner and outer axes respectively. The inner and outer helical blades extend radially outwardly and inwardly respectively. Each of the bodies has at least two blades. There is one more or one less outer helical blades than inner helical blades. The inner and outer bodies may both be rotatable about inner and outer axes and geared together in a fixed gear ratio. The turbine may have first and second sections with a first twist slope greater than a second twist slope respectively of the inner and outer helical blades.
摘要翻译：轴流式正排量涡轮机包括内部和外部本体，其具有分别在相对高压入口和相对低压力出口之间延伸的偏移的内轴和外轴。至少一个主体可围绕其轴线旋转。内外体分别围绕内轴和外轴缠绕内螺旋叶片和外螺旋叶片。内螺旋叶片和外螺旋叶片分别径向向外和向内延伸。每个主体至少有两个刀片。外螺旋叶片比内螺旋叶片多一个或多一个。内部和外部主体可以围绕内部轴线和外部轴线都可旋转并且以固定的齿轮比啮合在一起。涡轮可以具有分别具有大于内螺旋叶片和外螺旋叶片的第二扭转斜率的第一扭曲斜面的第一和第二部分。

4. 发明授权

US07624565B2 Hybrid worm gas turbine engine 有权
标题翻译：混合式蜗轮燃气轮机
公开(公告)号：US07624565B2
公开(公告)日：2009-12-01
申请号：US11742789
申请日：2007-05-01
申请人： Kurt David Murrow , Rollin George Giffin , Oladapo Fakunle
发明人： Kurt David Murrow , Rollin George Giffin , Oladapo Fakunle
IPC分类号： F02C3/02
CPC分类号： F01C1/107 , F01C11/008 , F02C3/055 , F02K3/06 , F05D2250/25
摘要： A gas turbine engine has components including a compressor, a combustor, and a turbine. At least one component is radially bladed having at least one row of radially extending rotatable blades and at least another is a worm component having an inner body disposed within an outer body. The inner and outer bodies have offset inner and outer axes, intermeshed inner and outer helical blades wound about the inner and outer axes respectively, and at least one of the inner and outer bodies being rotatable about a corresponding one of the inner and outer axes. An aircraft gas turbine engine has components in serial downstream flow relationship including a fan, a low pressure compressor, a high pressure compressor, a combustor, a high pressure turbine, and a low pressure turbine. At least one of the components is radially bladed and at least one of the components is a worm component.
摘要翻译：燃气涡轮发动机具有包括压缩机，燃烧器和涡轮机的部件。至少一个部件是径向叶片的，具有至少一排径向延伸的可旋转叶片，并且至少另一个部件是具有设置在外部主体内部的内部主体的蜗杆部件。内部和外部主体具有偏移的内部和外部轴线，分别围绕内部轴线和外部轴线缠绕的相互啮合的内部和外部螺旋叶片，并且内部主体和外部主体中的至少一个可围绕内部轴线和外部轴线中的相应一个旋转。飞机燃气涡轮发动机具有串联下游流量关系的部件，包括风扇，低压压缩机，高压压缩机，燃烧器，高压涡轮机和低压涡轮机。至少一个部件是径向叶片的，并且组件中的至少一个是蜗杆部件。

5. 发明授权

US07530217B2 Axial flow positive displacement gas generator with combustion extending into an expansion section 有权
标题翻译：轴向流量正位移气体发生器，其燃烧延伸到膨胀段
公开(公告)号：US07530217B2
公开(公告)日：2009-05-12
申请号：US11303143
申请日：2005-12-16
申请人： Kurt David Murrow , Brandon Flowers Powell
发明人： Kurt David Murrow , Brandon Flowers Powell
IPC分类号： F02C3/02
CPC分类号： F23R3/56 , F01C1/107 , F01C11/008 , F02C3/055 , F02C5/06 , F02K5/00 , F05D2220/326 , F05D2220/327 , F05D2250/25 , F05D2260/40311 , Y02T50/671
摘要： An axial flow positive displacement engine has an inlet axially spaced apart and upstream from an outlet. Inner and outer bodies have offset inner and outer axes extend from the inlet to the outlet through first, second, and third sections of a core assembly in serial downstream flow relationship. At least one of the bodies is rotatable about its axis. The inner and outer bodies have intermeshed inner and outer helical blades wound about the inner and outer axes respectively. The inner and outer helical blades extend radially outwardly and inwardly respectively and have first, second, and third twist slopes in the first, second, and third sections respectively. The first twist slopes are less than the second twist slopes and the third twist slopes are less than the second twist slopes. A combustion section extends axially downstream from the second section through at least a portion of the third section.
摘要翻译：轴流容积式发动机具有在出口处轴向间隔开和上游的入口。内部和外部主体具有偏移的内部和外部轴线从入口到出口通过串联下游流动关系的芯组件的第一，第二和第三部分延伸。至少一个主体可围绕其轴线旋转。内外体分别围绕内轴和外轴缠绕内螺旋叶片和外螺旋叶片。内螺旋叶片和外螺旋叶片分别径向向外和向内延伸，并且分别在第一，第二和第三部分中具有第一，第二和第三扭曲斜面。第一扭转斜面小于第二扭转斜面，第三扭转斜面小于第二扭转斜面。燃烧部分从第二部分轴向延伸穿过第三部分的至少一部分。

6. 发明授权

US08328542B2 Positive displacement rotary components having main and gate rotors with axial flow inlets and outlets 有权
标题翻译：具有具有轴向流入口和出口的主转子和闸转子的正位移旋转部件
公开(公告)号：US08328542B2
公开(公告)日：2012-12-11
申请号：US12347617
申请日：2008-12-31
申请人： Kurt David Murrow , Rollin George Giffin
发明人： Kurt David Murrow , Rollin George Giffin
IPC分类号： F03C2/00 , F03C4/00 , F04C18/00 , F04C2/00
CPC分类号： F01C1/165 , F01C1/20 , F01C11/002 , F01C11/006 , F04C29/12 , F04C2240/20 , F04C2250/101 , F04C2250/102
摘要： An axial flow positive displacement gas turbine engine component such as a compressor or a turbine or an expander includes a rotor assembly extending from a fully axial flow inlet to a downstream axially spaced apart axial flow outlet. The rotor assembly includes a main rotor and one or more gate rotors rotatable about parallel main and gate axes of the main and gate rotors respectively. The main and gate rotors having intermeshed main and gate helical blades extending radially outwardly from annular main and gate hubs, circumscribed about, and wound about the main and gate axes respectively. Intersecting main and gate annular openings in the axial flow inlet extend radially between a casing surrounding the rotor assembly and the main and gate hubs. The main helical blades transition from 0 to a full radial height in a downstream direction in an inlet transition section.
摘要翻译：诸如压缩机或涡轮机或膨胀机的轴向流量正位移燃气涡轮发动机部件包括从完全轴向流入口延伸到下游轴向间隔开的轴向流出口的转子组件。转子组件包括主转子和分别围绕主转子和转子的主轴和闸门轴线旋转的一个或多个转子。主和门转子具有相互啮合的主螺旋叶片和门螺旋叶片，其从环形主浇道和浇口轮毂径向向外延伸，分别围绕并围绕主轴和闸轴缠绕。在轴向流入口中相交的主和门环形开口径向地在围绕转子组件的壳体和主和浇口毂之间延伸。主螺旋叶片在入口过渡部分中沿下游方向从0转变为完全径向高度。

7. 发明申请

US20100166591A1 POSITIVE DISPLACEMENT ROTARY COMPONENTS HAVING MAIN AND GATE ROTORS WITH AXIAL FLOW INLETS AND OUTLETS 有权
标题翻译：具有轴向流入口和出口的主门和门旋转器的正位移旋转部件
公开(公告)号：US20100166591A1
公开(公告)日：2010-07-01
申请号：US12347617
申请日：2008-12-31
申请人： Kurt David Murrow , Rollin George Giffin
发明人： Kurt David Murrow , Rollin George Giffin
IPC分类号： F04C18/16
CPC分类号： F01C1/165 , F01C1/20 , F01C11/002 , F01C11/006 , F04C29/12 , F04C2240/20 , F04C2250/101 , F04C2250/102
摘要： An axial flow positive displacement gas turbine engine component such as a compressor or a turbine or an expander includes a rotor assembly extending from a fully axial flow inlet to a downstream axially spaced apart axial flow outlet. The rotor assembly includes a main rotor and one or more gate rotors rotatable about parallel main and gate axes of the main and gate rotors respectively. The main and gate rotors having intermeshed main and gate helical blades extending radially outwardly from annular main and gate hubs, circumscribed about, and wound about the main and gate axes respectively. Intersecting main and gate annular openings in the axial flow inlet extend radially between a casing surrounding the rotor assembly and the main and gate hubs. The main helical blades transition from 0 to a full radial height in a downstream direction in an inlet transition section.
摘要翻译：诸如压缩机或涡轮机或膨胀机的轴向流量正位移燃气涡轮发动机部件包括从完全轴向流入口延伸到下游轴向间隔开的轴向流出口的转子组件。转子组件包括主转子和分别围绕主转子和转子的主轴和闸门轴线旋转的一个或多个转子。主和门转子具有相互啮合的主螺旋叶片和门螺旋叶片，其从环形主浇道和浇口轮毂径向向外延伸，分别围绕并围绕主轴和闸轴缠绕。在轴向流入口中相交的主和门环形开口径向地在围绕转子组件的壳体和主和浇口毂之间延伸。主螺旋叶片在入口过渡部分中沿下游方向从0转变为完全径向高度。

8. 发明申请

US20090193786A1 System And Method Of Continuous Detonation In A Gas Turbine Engine 有权
标题翻译：燃气轮机发动机连续爆震的系统和方法
公开(公告)号：US20090193786A1
公开(公告)日：2009-08-06
申请号：US12024592
申请日：2008-02-01
申请人： Kurt David Murrow , Lawrence Butler
发明人： Kurt David Murrow , Lawrence Butler
IPC分类号： F02C3/16 , F02C3/14
CPC分类号： F02C3/16 , F02C3/14 , F05D2250/232 , F05D2250/25 , F05D2250/314 , F23R7/00
摘要： A continuous detonation system, including: a rotatable member including a forward end, an aft end, a circumferential wall and a longitudinal centerline axis extending therethrough; an outer circumferential wall, wherein the rotatable member is positioned therein so that the circumferential wall of the rotatable member is spaced radially inwardly from the outer circumferential wall; at least one helical channel formed by a plurality of helical sidewalls extending between the circumferential wall of the rotatable member and the outer circumferential wall, each helical channel being open at the forward end and the aft end of the rotatable member so as to provide flow communication therethrough; an air supply for providing air to each helical channel; and, a fuel supply for providing fuel to each helical channel. In this way, a mixture of the fuel and air is continuously detonated within each helical channel in a manner such that combustion gases exit therefrom with an increased pressure and temperature.
摘要翻译：一种连续爆炸系统，包括：可旋转构件，包括前端，后端，周向壁和延伸穿过其的纵向中心轴线; 外周壁，其中可旋转构件定位在其中，使得可旋转构件的周壁与外周壁径向向内间隔开; 至少一个由可旋转构件的圆周壁和外周壁之间延伸的多个螺旋侧壁形成的螺旋通道，每个螺旋通道在可旋转构件的前端和后端开口，以便提供流动连通通过用于向每个螺旋通道提供空气的空气供应装置; 以及用于向每个螺旋通道提供燃料的燃料供应。以这种方式，燃料和空气的混合物在每个螺旋通道内以使得燃烧气体以增加的压力和温度从其中排出的方式连续地引爆。

9. 发明授权

US07096674B2 High thrust gas turbine engine with improved core system 有权
标题翻译：具有改进的核心系统的高推力燃气轮机
公开(公告)号：US07096674B2
公开(公告)日：2006-08-29
申请号：US10941546
申请日：2004-09-15
申请人： Robert Joseph Orlando , Kattalaicheri Srinivasan Venkataramani , Ching-Pang Lee , Thomas Ory Moniz , Kurt David Murrow
发明人： Robert Joseph Orlando , Kattalaicheri Srinivasan Venkataramani , Ching-Pang Lee , Thomas Ory Moniz , Kurt David Murrow
IPC分类号： F02C6/08
CPC分类号： F02C7/18 , F02C5/00 , F05D2260/20 , F05D2260/96 , F23R3/005 , F23R3/04 , F23R7/00 , F23R2900/03044 , F23R2900/03281 , Y02T50/676
摘要： A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a first drive shaft; a booster compressor positioned downstream of and in at least partial flow communication with the fan section including a plurality of stages, each stage including a stationary compressor blade row and a rotating compressor blade row connected to a drive shaft and interdigitated with the stationary compressor blade row; a core system positioned downstream of the compressor, where the core system further includes an intermediate compressor positioned downstream of and in flow communication with the booster compressor, the intermediate compressor being connected to a second drive shaft, and a combustion system for producing pulses of gas having increased pressure and temperature from a fluid flow provided to an inlet thereof so as to produce a working fluid at an outlet; and, a low pressure turbine positioned downstream of and in flow communication with the core system, the low pressure turbine being utilized to power the first drive shaft. The core system may also include an intermediate turbine positioned downstream of the combustion system in flow communication with the working fluid, where the intermediate turbine is utilized to power the second drive shaft. A first source of compressed air having a predetermined pressure is provided to the combustion system inlet and a second source of compressed air having a pressure greater than the first source of compressed air is provided to cool the combustion system.
摘要翻译：一种燃气涡轮发动机，其具有穿过其的纵向中心线轴线，包括：在所述燃气涡轮发动机的前端处的风扇部分，至少包括连接到第一驱动轴的第一风扇叶片排; 位于与包括多个级的风扇部分的下游并且至少部分流动连通的增压压缩机，每个级包括固定压缩机叶片排和连接到驱动轴的旋转压缩机叶片排，并与固定压缩机叶片排相互指向 ; 位于压缩机下游的核心系统，其中所述核心系统还包括位于所述增压压缩机下游并与所述增压压缩机流动连通的中间压缩机，所述中间压缩机连接到第二驱动轴，以及用于产生气体脉冲的燃烧系统从提供给其入口的流体流增加压力和温度，以便在出口处产生工作流体; 以及低压涡轮机，其位于所述核心系统的下游并与所述核心系统流动连通，所述低压涡轮机用于为所述第一驱动轴提供动力。核心系统还可以包括位于燃烧系统下游的中间涡轮机，其与工作流体流动连通，其中中间涡轮机用于为第二驱动轴提供动力。具有预定压力的第一压缩空气源被提供给燃烧系统入口，并且提供具有大于第一压缩空气源的压力的第二压缩空气源以冷却燃烧系统。

10. 发明授权

US08708643B2 Counter-rotatable fan gas turbine engine with axial flow positive displacement worm gas generator 有权
标题翻译：具有轴向流量正位移蜗轮气发生器的可逆转风机燃气轮机
公开(公告)号：US08708643B2
公开(公告)日：2014-04-29
申请号：US11838379
申请日：2007-08-14
申请人： Rollin George Giffin , Kurt David Murrow , Oladapo Fakunle
发明人： Rollin George Giffin , Kurt David Murrow , Oladapo Fakunle
IPC分类号： F01C1/107
CPC分类号： F02C3/067 , F01C1/107 , F01C11/008 , F01D1/38 , F02K3/072 , F02K5/00
摘要： A counter-rotatable fan turbine engine includes a counter-rotatable fan section, a worm gas generator, and a low pressure turbine to power the counter-rotatable fan section. The low pressure turbine maybe counter-rotatable or have a single direction of rotation in which case it powers the counter-rotatable fan section through a gearbox. The gas generator has inner and outer bodies having offset inner and outer axes extending through first, second, and third sections of a core assembly. At least one of the bodies is rotatable about its axis. The inner and outer bodies have intermeshed inner and outer helical blades wound about the inner and outer axes and extending radially outwardly and inwardly respectively. The helical blades have first, second, and third twist slopes in the first, second, and third sections respectively. A combustor section extends through at least a portion of the second section.
摘要翻译：一种可逆转风扇涡轮发动机包括一个可逆转的风扇部分，一个蜗杆气体发生器和一个低压涡轮机，为反向旋转的风扇部分提供动力。低压涡轮机可以是反向旋转的或具有单个旋转方向，在这种情况下，它通过齿轮箱为反向旋转的风扇部分供电。气体发生器具有内和外主体，其具有穿过芯组件的第一，第二和第三部分的偏移的内轴线和外轴线。至少一个主体可围绕其轴线旋转。内部和外部主体具有围绕内部轴线和外部轴线缠绕的内部和外部螺旋叶片，并且分别径向向外和向内延伸。螺旋叶片分别在第一，第二和第三部分具有第一，第二和第三扭曲斜面。燃烧器部分延伸穿过第二部分的至少一部分。

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