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1. 发明授权

US08137054B2 Supersonic compressor 有权
标题翻译：超音速压缩机
公开(公告)号：US08137054B2
公开(公告)日：2012-03-20
申请号：US12342278
申请日：2008-12-23
申请人： Douglas Carl Hofer , Zachary William Nagel , David Graham Holmes
发明人： Douglas Carl Hofer , Zachary William Nagel , David Graham Holmes
IPC分类号： F01D1/24
CPC分类号： F04D21/00 , F04D19/024
摘要： A novel supersonic compressor is provided by the present invention. In one embodiment, the novel supersonic compressor comprises a fluid inlet, a fluid outlet, and at least two counter rotary supersonic compressor rotors, said supersonic compressor rotors being configured in series such that an output from a first supersonic compressor rotor having a first direction of rotation is directed to a second supersonic compressor rotor configured to counter-rotate with respect to the first supersonic compressor rotor.
摘要翻译：本发明提供了一种新型超音速压缩机。在一个实施例中，新型超音速压缩机包括流体入口，流体出口和至少两个反向旋转超音速压缩机转子，所述超音速压缩机转子被串联配置，使得来自第一超音速压缩机转子的输出具有第一方向旋转被引导到构造成相对于第一超音速压缩机转子反转的第二超音速压缩机转子。

2. 发明授权

US08668446B2 Supersonic compressor rotor and method of assembling same 有权
标题翻译：超音速压缩机转子及其组装方法
公开(公告)号：US08668446B2
公开(公告)日：2014-03-11
申请号：US12873228
申请日：2010-08-31
申请人： Douglas Carl Hofer , Zachary William Nagel , David Graham Holmes
发明人： Douglas Carl Hofer , Zachary William Nagel , David Graham Holmes
IPC分类号： F01D5/14
CPC分类号： F04D21/00 , F04D17/02 , F04D17/10 , F04D29/284
摘要： A supersonic compressor rotor. The supersonic compressor rotor includes a rotor disk that includes an upstream surface, a downstream surface, and a radially outer surface that extends generally axially between the upstream surface and the downstream surface. The radially outer surface includes an inlet surface, an outlet surface, and a transition surface that extends between the inlet surface and the outlet surface. A plurality of vanes are coupled to the radially outer surface. Adjacent vanes form a pair and are oriented such that a flow channel is defined between each pair of adjacent vanes. The flow channel extends between an inlet opening and an outlet opening. The inlet surface defines an inlet plane that extends between the inlet opening and the transition surface. The outlet surface defines an outlet plane that extends between the outlet opening and the transition surface that is not parallel to the inlet plane. At least one supersonic compression ramp is positioned within the flow channel to facilitate forming at least one compression wave within the flow channel.
摘要翻译：超音速压缩机转子。超音速压缩机转子包括转子盘，转子盘包括上游表面，下游表面和径向外表面，该外表面在上游表面和下游表面之间大致轴向地延伸。径向外表面包括入口表面，出口表面和在入口表面和出口表面之间延伸的过渡表面。多个叶片联接到径向外表面。相邻的叶片形成一对并且被定向成使得在每对相邻叶片之间限定流动通道。流动通道在入口和出口之间延伸。入口表面限定了在入口和过渡表面之间延伸的入口平面。出口表面限定出口平面，该出口平面在出口开口和不平行于入口平面的过渡表面之间延伸。至少一个超音速压缩斜坡位于流动通道内以便于在流动通道内形成至少一个压缩波。

3. 发明授权

US09097258B2 Supersonic compressor comprising radial flow path 有权
标题翻译：超音速压缩机包括径向流动路径
公开(公告)号：US09097258B2
公开(公告)日：2015-08-04
申请号：US12491602
申请日：2009-06-25
申请人： Douglas Carl Hofer , Zachary William Nagel , David Graham Holmes
发明人： Douglas Carl Hofer , Zachary William Nagel , David Graham Holmes
IPC分类号： F04D21/00 , F04D17/12 , F04D29/44 , F04D29/28
CPC分类号： F04D21/00 , F04D17/127 , F04D29/284 , F04D29/44 , F04D29/441
摘要： The present invention provides novel supersonic compressors comprising novel supersonic compressor rotors. The supersonic compressor rotors are designed to operate at very high rotational speed wherein the velocity of the gas entering the supersonic compressor rotor is greater than the local speed of sound in the gas, hence the descriptor “supersonic”. The new supersonic compressors comprise at least one supersonic compressor rotor defining an inner cylindrical cavity and an outer rotor rim and at least one radial flow channel allowing fluid communication between the inner cylindrical cavity and the outer rotor rim, said radial flow channel comprising a supersonic compression ramp. The novel supersonic compressor rotors are expected to enhance the performance of supersonic compressors comprising them, and to provide for greater design versatility in systems comprising such novel supersonic compressors.
摘要翻译：本发明提供了包含新型超音速压缩机转子的新型超音速压缩机。超音速压缩机转子设计成以非常高的转速工作，其中进入超音速压缩机转子的气体的速度大于气体中局部的声速，因此描述了“超音速”。新的超音速压缩机包括至少一个超音速压缩机转子，其限定内圆柱形空腔和外转子边缘以及至少一个径向流动通道，其允许内圆柱形空腔和外转子轮缘之间的流体连通，所述径向流动通道包括超音速压缩斜坡期望新颖的超音速压缩机转子增强包括它们的超音速压缩机的性能，并且在包括这种新型超音速压缩机的系统中提供更大的设计通用性。

4. 发明申请

US20100329856A1 SUPERSONIC COMPRESSOR COMPRISING RADIAL FLOW PATH 有权
标题翻译：包括径向流动路径的超级压缩机
公开(公告)号：US20100329856A1
公开(公告)日：2010-12-30
申请号：US12491602
申请日：2009-06-25
申请人： Douglas Carl Hofer , Zachary William Nagel , David Graham Holmes
发明人： Douglas Carl Hofer , Zachary William Nagel , David Graham Holmes
IPC分类号： F04D21/00 , F04D29/28 , F04D29/44
CPC分类号： F04D21/00 , F04D17/127 , F04D29/284 , F04D29/44 , F04D29/441
摘要： The present invention provides novel supersonic compressors comprising novel supersonic compressor rotors. The supersonic compressor rotors are designed to operate at very high rotational speed wherein the velocity of the gas entering the supersonic compressor rotor is greater than the local speed of sound in the gas, hence the descriptor “supersonic”. The new supersonic compressors comprise at least one supersonic compressor rotor defining an inner cylindrical cavity and an outer rotor rim and at least one radial flow channel allowing fluid communication between the inner cylindrical cavity and the outer rotor rim, said radial flow channel comprising a supersonic compression ramp. The novel supersonic compressor rotors are expected to enhance the performance of supersonic compressors comprising them, and to provide for greater design versatility in systems comprising such novel supersonic compressors.
摘要翻译：本发明提供了包含新型超音速压缩机转子的新型超音速压缩机。超音速压缩机转子设计成以非常高的转速工作，其中进入超音速压缩机转子的气体的速度大于气体中局部的声速，因此描述了“超音速”。新的超音速压缩机包括至少一个超音速压缩机转子，其限定内圆柱形空腔和外转子边缘以及至少一个径向流动通道，其允许内圆柱形空腔和外转子轮缘之间的流体连通，所述径向流动通道包括超音速压缩斜坡期望新颖的超音速压缩机转子增强包括它们的超音速压缩机的性能，并且在包括这种新型超音速压缩机的系统中提供更大的设计通用性。

5. 发明申请

US20100158665A1 SUPERSONIC COMPRESSOR 有权
标题翻译：超级压缩机
公开(公告)号：US20100158665A1
公开(公告)日：2010-06-24
申请号：US12342278
申请日：2008-12-23
申请人： Douglas Carl Hofer , Zachary William Nagel , David Graham Holmes
发明人： Douglas Carl Hofer , Zachary William Nagel , David Graham Holmes
IPC分类号： F04D19/02 , F04D29/32
CPC分类号： F04D21/00 , F04D19/024
摘要： A novel supersonic compressor is provided by the present invention. In one embodiment, the novel supersonic compressor comprises a fluid inlet, a fluid outlet, and at least two counter rotary supersonic compressor rotors, said supersonic compressor rotors being configured in series such that an output from a first supersonic compressor rotor having a first direction of rotation is directed to a second supersonic compressor rotor configured to counter-rotate with respect to the first supersonic compressor rotor.
摘要翻译：本发明提供了一种新型超音速压缩机。在一个实施例中，新型超音速压缩机包括流体入口，流体出口和至少两个反向旋转超音速压缩机转子，所述超音速压缩机转子被串联配置，使得来自第一超音速压缩机转子的输出具有第一方向旋转被引导到构造成相对于第一超音速压缩机转子反转的第二超音速压缩机转子。

6. 发明申请

US20120156015A1 SUPERSONIC COMPRESSOR AND METHOD OF ASSEMBLING SAME 审中-公开
标题翻译：超级压缩机及其组装方法
公开(公告)号：US20120156015A1
公开(公告)日：2012-06-21
申请号：US12971521
申请日：2010-12-17
申请人： Ravindra Gopaldas Devi , Douglas Carl Hofer , Zachary William Nagel , David Graham Holmes
发明人： Ravindra Gopaldas Devi , Douglas Carl Hofer , Zachary William Nagel , David Graham Holmes
IPC分类号： F04D21/00 , B23P15/00
CPC分类号： F04D21/00 , F04D29/284 , F04D29/321 , F04D29/624 , F04D29/644 , Y10T29/49236
摘要： A supersonic compressor includes a fluid inlet and a fluid outlet, a fluid conduit extending therebetween, and a supersonic compressor rotor disposed within the fluid conduit. The rotor includes at least one rotor disk that includes a substantially cylindrical body extending between a radially inner and outer surface and a plurality of vanes coupled to the body that extend radially outward from the rotor disk and adjacent vanes form a pair of vanes. The rotor disk further includes a shroud extending about at least a portion of the rotor disk. The shroud is coupled to at least a portion of each of the plurality of vanes. The radially outer surface, the pair of adjacent vanes, and the shroud are oriented such that a fluid flow channel is defined therebetween. The rotor disk also includes a plurality of adjacent supersonic compression ramps positioned within the fluid flow channel.
摘要翻译：超音速压缩机包括流体入口和流体出口，在其间延伸的流体导管和设置在流体导管内的超音速压缩机转子。转子包括至少一个转子盘，该转子盘包括在径向内表面和外表面之间延伸的基本上圆柱形的主体，以及耦合到主体的多个叶片，其从转子盘径向向外延伸，并且相邻叶片形成一对叶片。转子盘还包括围绕转子盘的至少一部分延伸的护罩。护罩耦合到多个叶片中的每一个的至少一部分。径向外表面，一对相邻叶片和护罩被定向成使得在其间限定流体流动通道。转子盘还包括位于流体流动通道内的多个相邻的超音速压缩斜面。

7. 发明申请

US20120051933A1 SUPERSONIC COMPRESSOR ROTOR AND METHOD OF ASSEMBLING SAME 有权
标题翻译：超级压缩机转子及其组装方法
公开(公告)号：US20120051933A1
公开(公告)日：2012-03-01
申请号：US12873228
申请日：2010-08-31
申请人： Douglas Carl Hofer , Zachary William Nagel , David Graham Holmes
发明人： Douglas Carl Hofer , Zachary William Nagel , David Graham Holmes
IPC分类号： F04D29/38
CPC分类号： F04D21/00 , F04D17/02 , F04D17/10 , F04D29/284
摘要： A supersonic compressor rotor. The supersonic compressor rotor includes a rotor disk that includes an upstream surface, a downstream surface, and a radially outer surface that extends generally axially between the upstream surface and the downstream surface. The radially outer surface includes an inlet surface, an outlet surface, and a transition surface that extends between the inlet surface and the outlet surface. A plurality of vanes are coupled to the radially outer surface. Adjacent vanes form a pair and are oriented such that a flow channel is defined between each pair of adjacent vanes. The flow channel extends between an inlet opening and an outlet opening. The inlet surface defines an inlet plane that extends between the inlet opening and the transition surface. The outlet surface defines an outlet plane that extends between the outlet opening and the transition surface that is not parallel to the inlet plane. At least one supersonic compression ramp is positioned within the flow channel to facilitate forming at least one compression wave within the flow channel.
摘要翻译：超音速压缩机转子。超音速压缩机转子包括转子盘，转子盘包括上游表面，下游表面和径向外表面，该外表面在上游表面和下游表面之间大致轴向地延伸。径向外表面包括入口表面，出口表面和在入口表面和出口表面之间延伸的过渡表面。多个叶片联接到径向外表面。相邻的叶片形成一对并且被定向成使得在每对相邻叶片之间限定流动通道。流动通道在入口和出口之间延伸。入口表面限定了在入口和过渡表面之间延伸的入口平面。出口表面限定出口平面，该出口平面在出口开口和不平行于入口平面的过渡表面之间延伸。至少一个超音速压缩斜坡位于流动通道内以便于在流动通道内形成至少一个压缩波。

8. 发明授权

US5644918A Dynamics free low emissions gas turbine combustor 失效
标题翻译：无动力低排放燃气轮机燃烧器
公开(公告)号：US5644918A
公开(公告)日：1997-07-08
申请号：US337704
申请日：1994-11-14
申请人： Anil Gulati , Anthony John Dean , David Graham Holmes , Eayre Bruce Voorhees
发明人： Anil Gulati , Anthony John Dean , David Graham Holmes , Eayre Bruce Voorhees
IPC分类号： F23M99/00 , F23R3/00 , F23R3/02 , F23R3/18 , F02C7/045
CPC分类号： F23R3/18 , F23M20/005 , F23R3/002 , F23R3/02 , F05B2260/96 , F23R2900/00014
摘要： Combustion-induced instabilities are minimized in gas turbine combustors by incorporating one or more Helmholtz resonators into the combustor. First and second plates located in the head end of the combustor casing define one cavity, and a sleeve located between the casing and the liner defines another cavity. Each of the two cavities is connected to the combustion chamber by one or more throats, thus forming Helmholtz resonators. The throats of each resonator can be tubes of different lengths and/or different cross-sectional areas to provide dynamics suppression over a broad band of frequencies. The throats can also be arranged such that each throat is associated with a different portion of its respective cavity, each cavity portion having a different volume.
摘要翻译：通过将一个或多个亥姆霍兹共振器并入到燃烧器中，在燃气轮机燃烧器中燃烧诱发的不稳定性被最小化。位于燃烧器壳体头部的第一和第二板限定一个空腔，并且位于壳体和衬套之间的套筒限定另一腔。两个腔中的每一个通过一个或多个喉部连接到燃烧室，从而形成亥姆霍兹共振器。每个谐振器的喉部可以是具有不同长度和/或不同横截面面积的管，以在宽频带上提供动态抑制。喉部也可以布置成使得每个喉部与其相应空腔的不同部分相关联，每个空腔部分具有不同的体积。

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