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公开(公告)号：US07854111B2
公开(公告)日：2010-12-21
申请号：US12044043
申请日：2008-03-07
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。
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公开(公告)号：US07624565B2
公开(公告)日：2009-12-01
申请号：US11742789
申请日：2007-05-01
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。
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3.发明授权Axial flow positive displacement gas generator with combustion extending into an expansion section 有权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
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。
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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。
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5.发明授权Counter-rotatable fan gas turbine engine with axial flow positive displacement worm gas generator 有权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
IPC分类号： F01C1/107
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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6.发明申请COUNTER-ROTATABLE FAN GAS TURBINE ENGINE WITH AXIAL FLOW POSITIVE DISPLACEMENT WORM GAS GENERATOR 有权具有轴向流动的逆转风扇涡轮发动机积极位移WORM气体发生器公开(公告)号：US20130081374A1
公开(公告)日：2013-04-04
申请号：US11838379
申请日：2007-08-14
IPC分类号： F02C3/067
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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公开(公告)号：US07905084B2
公开(公告)日：2011-03-15
申请号：US12024528
申请日：2008-02-01
CPC分类号： F02K3/06 , F02C3/165 , F05D2250/25
摘要： A gas generator for providing continuous pressure rise combustion, 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. Each helical channel includes an inlet portion having a first cross-sectional area for receiving a flow having a designated shape and orientation, a throat portion downstream of the inlet portion having a second cross-section less than the first cross-section of the inlet portion, and a diffusion portion downstream of the throat portion having a third cross-section greater than the second cross-section of the throat portion. A device is also positioned downstream from the diffusion portion of each helical channel for holding flame therein. A mixture of the fuel and air is continuously combusted downstream of the diffusion portion of each helical channel in a manner such that combustion gases exit therefrom with an increased pressure and temperature.
摘要翻译： 一种用于提供连续升压燃烧的气体发生器，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线轴线; 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源; 以及用于向每个螺旋通道提供燃料的燃料供应。 每个螺旋通道包括具有用于接收具有指定形状和取向的流的第一横截面区域的入口部分，入口部分下游的喉部部分具有小于入口部分的第一横截面的第二横截面 并且所述喉部的下游的扩散部分具有大于所述喉部的所述第二横截面的第三横截面。 装置也位于每个螺旋通道的扩散部分的下游，用于在其中保持火焰。 燃料和空气的混合物以每个螺旋通道的扩散部分的下游连续燃烧，使得燃烧气体以增加的压力和温度从其中离开。
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公开(公告)号：US07726115B2
公开(公告)日：2010-06-01
申请号：US11345760
申请日：2006-02-02
IPC分类号： F02C3/055
CPC分类号： F01C1/084 , F01C1/107 , F01C11/008 , F02B53/00 , F02C5/06 , F02K5/00 , F03C2/08 , Y02T50/671
摘要： An axial flow positive displacement compressor 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 and second sections of a compressor 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. The helical blades have first and second twist slopes in the first and second sections respectively. The first twist slopes are less than the second twist slopes. An engine including the compressor has in downstream serial flow relationship from the compressor a combustor and a high pressure turbine drivingly connected to the compressor by a high pressure shaft.
摘要翻译： 轴流容积式压缩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压缩机组件的第一和第二部分延伸。 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。 螺旋叶片分别在第一和第二部分具有第一和第二扭曲斜面。 第一个扭转斜率小于第二个扭曲斜率。 包括压缩机的发动机与来自压缩机的下游串联流动关系是通过高压轴驱动地连接到压缩机的燃烧器和高压涡轮机。
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公开(公告)号：US06889505B2
公开(公告)日：2005-05-10
申请号：US10405561
申请日：2003-04-02
申请人： Lawrence Butler , Kattalaicheri Srinivasan Venkataramani , Kurt David Murrow , Ivett Alejandra Leyva
发明人： Lawrence Butler , Kattalaicheri Srinivasan Venkataramani , Kurt David Murrow , Ivett Alejandra Leyva
摘要： A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where at least one stage of circumferentially spaced detonation chambers is disposed therein. The pulse detonation system further includes a shaft rotatably connected to the cylindrical member and a stator configured in spaced arrangement around the forward surface, the aft surface, and the outer circumferential surface of the cylindrical member and a portion of the shaft. The stator has at least one group of ports formed therein which sequentially align with the detonation chambers as the cylindrical member rotates. In this way, detonation cycles are performed in the detonation chambers of each detonation stage so that reaction forces induced by the detonation cycles create a torque which causes the cylindrical member to rotate. Each detonation chamber includes a first open end located adjacent the outer circumferential surface of the cylindrical member and a second closed end located within a middle portion of the cylindrical member.
摘要翻译： 用于具有延伸穿过其中的纵向中心线轴的燃气涡轮发动机的脉冲爆震系统包括具有前表面，后表面和外周表面的可旋转圆柱形构件，其中在其中设置至少一个周向间隔开的爆震腔室。 脉冲爆震系统还包括可旋转地连接到圆柱形构件的轴和定子，其围绕圆筒构件的前表面，后表面和外圆周表面以及轴的一部分间隔开地布置。 定子具有形成在其中的至少一组端口，随着圆柱形构件的旋转，它们与引爆室顺序对准。 以这种方式，在每个爆震阶段的引爆室中进行爆震循环，使得由引爆循环引起的反作用力产生使圆柱形构件旋转的扭矩。 每个爆震室包括位于圆柱形构件的外周表面附近的第一开口端和位于圆柱形构件的中间部分内的第二封闭端。
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公开(公告)号：US20080273969A1
公开(公告)日：2008-11-06
申请号：US11742789
申请日：2007-05-01
IPC分类号： F03B3/00
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。
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