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公开(公告)号：US12129790B1
公开(公告)日：2024-10-29
申请号：US18433518
申请日：2024-02-06
摘要： A new power plant cycle that does not condense the vapor leaving the turbine facilitated by an innovative vapor compression apparatus to repressurize the vapor with heat input to the cycle from a new renewable energy or other heat source. The new cycle can be used in place of the conventional low efficiency Rankine cycle to provide economical production of electricity. Using the cycle with heat input from a fossil fuel would reduce air pollution from this source to a fraction of current emissions.
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公开(公告)号：US20170268527A1
公开(公告)日：2017-09-21
申请号：US15611654
申请日：2017-06-01
发明人： Shohei Naruoka , Hiroyuki Watanabe
CPC分类号： F04D29/284 , F02B33/40 , F02B39/04 , F02B61/02 , F04D17/10 , F04D21/00 , F04D25/028 , F04D25/08 , F04D29/30 , F05D2220/40
摘要： An impeller (60) for use in a supercharger (42), which is cable of increasing the efficiency while suppressing the increase in size of the impeller (60), is driven in driving connection with a crankshaft (26) of a combustion engine (E) mounted on a motorcycle to supply an intake air (I) towards the combustion engine (E). When the supercharger (42) is driven at a maximum permissible engine speed of an inlet diameter (Ii), the impeller (60) is so set that the peripheral velocity at an inlet side tip end portion (112) of the impeller (60) may exceed the sonic velocity, and may be smaller than 1.3 times the sonic velocity.
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公开(公告)号：US20140341706A1
公开(公告)日：2014-11-20
申请号：US14272667
申请日：2014-05-08
申请人： Pascal Lardy , James M. Sorokes , Mark J. Kuzdzal
发明人： Pascal Lardy , James M. Sorokes , Mark J. Kuzdzal
CPC分类号： F04D29/444 , F04D17/10 , F04D21/00 , F04D25/0686 , F04D29/422 , F04D29/462 , F05D2240/121 , F05D2250/52
摘要： A supersonic compressor provided may include an axial inlet and a centrifugal impeller fluidly coupled to the axial inlet. The centrifugal impeller may have a periphery and may be configured to impart energy to process fluid received via the axial inlet and discharge the process fluid from the periphery in at least a partially radial direction. The supersonic compressor may further include a static diffuser circumferentially disposed about the periphery of the centrifugal impeller and configured to receive the process fluid from the centrifugal impeller and convert the energy imparted. The static diffuser may include a plurality of diffuser vanes defining diffuser passageways therebetween. A supersonic ramp may be formed at an end of the at least one diffuser vane proximate the periphery of the centrifugal impeller. The supersonic ramp may be configured to generate a shock wave from the process fluid.
摘要翻译： 提供的超音速压缩机可以包括流体耦合到轴向入口的轴向入口和离心式叶轮。 离心式叶轮可以具有周边并且可以被配置成赋予能量以处理经由轴向入口接收的流体并且在至少部分径向方向上从周边排出过程流体。 超音速压缩机还可以包括围绕离心式叶轮的周边周向设置的静态扩散器，并且构造成从离心式叶轮接收工艺流体并转换所赋予的能量。 静态扩散器可以包括限定其间的扩散器通道的多个扩散器叶片。 超音速斜坡可以形成在靠近离心式叶轮的周边的至少一个扩散器叶片的端部。 超音速斜坡可以被配置为从过程流体产生冲击波。
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4.发明授权System and methods of assembling a supersonic compressor rotor including a radial flow channel 有权组装包括径向流动通道的超音速压缩机转子的系统和方法公开(公告)号：US08827640B2
公开(公告)日：2014-09-09
申请号：US13037675
申请日：2011-03-01
CPC分类号： F04D21/00 , B23P15/006 , F04D17/02 , F04D29/053 , F04D29/282 , F04D29/284 , F04D29/624 , Y10T29/49243 , Y10T29/49245 , Y10T29/49325
摘要： A supersonic compressor rotor that includes a rotor disk that includes a substantially cylindrical endwall, a radially inner surface, and a radially outer surface. The endwall extends between the radially inner surface and the radially outer surface. A plurality of vanes are coupled to the endwall. The vanes extend outwardly from the endwall. Adjacent vanes form a pair and are spaced a circumferential distance apart such that a flow channel is defined between each pair of circumferentially-adjacent vanes. The flow channel extends generally radially between an inlet opening and an outlet opening. A first supersonic compression ramp is coupled to the endwall. The first 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： 一种超音速压缩机转子，其包括转子盘，转子盘包括基本上圆柱形的端壁，径向内表面和径向外表面。 端壁在径向内表面和径向外表面之间延伸。 多个叶片联接到端壁。 叶片从端壁向外延伸。 相邻的叶片形成一对并且隔开间隔开的周向距离，使得在每对周向相邻的叶片之间限定流动通道。 流动通道在入口开口和出口之间大致径向延伸。 第一超音速压缩斜坡连接到端壁。 第一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。
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公开(公告)号：US08657571B2
公开(公告)日：2014-02-25
申请号：US12974566
申请日：2010-12-21
IPC分类号： F04D21/00
CPC分类号： F04D21/00 , F04D29/284 , F04D29/321 , Y10T29/49236
摘要： A supersonic compressor rotor that includes a rotor disk that includes a body that extends between a radially inner surface and a radially outer surface. A plurality of vanes are coupled to the body. The vanes extend outwardly from the rotor disk. 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. At least one supersonic compression ramp is positioned within the flow channel. The supersonic compression ramp is configured to condition a fluid being channeled through the flow channel such that the fluid includes a first velocity at the inlet opening and a second velocity at the outlet opening. Each of the first velocity and the second velocity being supersonic with respect to said rotor disk surfaces.
摘要翻译： 一种超音速压缩机转子，其包括转子盘，该转子盘包括在径向内表面和径向外表面之间延伸的主体。 多个叶片联接到主体。 叶片从转子盘向外延伸。 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。 至少一个超音速压缩斜坡位于流动通道内。 超音速压缩斜坡被配置为调节通过流动通道引导的流体，使得流体包括在入口开口处的第一速度和在出口开口处的第二速度。 第一速度和第二速度中的每一个相对于所述转子盘表面是超音速的。
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公开(公告)号：US08550770B2
公开(公告)日：2013-10-08
申请号：US13117871
申请日：2011-05-27
IPC分类号： F04D21/00
CPC分类号： F04D17/127 , F04D21/00
摘要： A supersonic compressor includes a fluid inlet, fluid outlet, and a fluid conduit extending therebetween with a supersonic compressor rotor disposed therein. The supersonic compressor rotor includes a first endwall and a plurality of vanes coupled thereto. Each pair of the vanes defines a fluid flow channel. The fluid flow channel defines a flow channel inlet opening and a flow channel outlet opening and includes a throat portion. The supersonic compressor rotor also includes a second endwall and at least one axially translatable fluid control device positioned adjacent to the rotor. The axially translatable fluid control device is configured to obstruct the throat portion and includes at least one axially translatable protrusion insertable into at least a portion of the throat portion.
摘要翻译： 超音速压缩机包括流体入口，流体出口和在其间延伸的流体导管，其中设置有超音速压缩机转子。 超音速压缩机转子包括第一端壁和与其连接的多个叶片。 每对叶片限定了流体流动通道。 流体流动通道限定流动通道入口开口和流动通道出口开口，并且包括喉部分。 超音速压缩机转子还包括第二端壁和邻近转子定位的至少一个可轴向平移的流体控制装置。 可轴向平移的流体控制装置构造成阻塞喉部并且包括可插入喉部的至少一部分中的至少一个可轴向平移的突出部。
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公开(公告)号：US20130223975A1
公开(公告)日：2013-08-29
申请号：US13441833
申请日：2012-04-06
申请人： Shawn P. Lawlor
发明人： Shawn P. Lawlor
IPC分类号： F04D21/00
CPC分类号： F04D21/00 , F04D27/0215
摘要： A supersonic gas compressor with bleed gas collectors, and a method of starting the compressor. The compressor includes aerodynamic duct(s) situated for rotary movement in a casing. The aerodynamic duct(s) generate a plurality of oblique shock waves for efficiently compressing a gas at supersonic conditions. A convergent inlet is provided adjacent to a bleed gas collector, and during startup of the compressor, bypass gas is removed from the convergent inlet via the bleed gas collector, to enable supersonic shock stabilization. Once the oblique shocks are stabilized at a selected inlet relative Mach number and pressure ratio, the bleed of bypass gas from the convergent inlet via the bypass gas collectors is effectively eliminated.
摘要翻译： 具有排放气体收集器的超音速气体压缩机和启动压缩机的方法。 压缩机包括用于在壳体中旋转运动的空气动力学管道。 空气动力学管道产生多个倾斜冲击波，用于在超音速条件下有效地压缩气体。 收集入口邻近排放气体收集器设置，并且在压缩机启动期间，旁路气体经由排放气体收集器从会聚入口移除，以实现超音速冲击稳定。 一旦倾斜冲击稳定在所选择的入口相对马赫数和压力比，则有效地消除了从收敛入口经由旁路气体收集器的旁路气体的泄放。
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公开(公告)号：US20130149100A1
公开(公告)日：2013-06-13
申请号：US13542674
申请日：2012-07-06
IPC分类号： F01D9/00
CPC分类号： F01D9/00 , F01D1/026 , F01D1/10 , F01D1/16 , F01D5/02 , F01D9/047 , F02C3/00 , F02C3/04 , F02C3/06 , F02C3/14 , F02C7/00 , F02C7/22 , F02C9/16 , F02C9/18 , F04D21/00 , F05D2220/3216 , F05D2220/3218 , F05D2220/3219 , F05D2240/128 , F05D2240/30 , F05D2240/301 , F05D2240/302 , F05D2240/35 , Y02E20/14
摘要： A gas turbine engine with a compressor rotor having compressor impulse blades that delivers gas at supersonic conditions to a stator. The stator includes a one or more aerodynamic ducts that each have a converging portion and a diverging portion for deceleration of the selected gas to subsonic conditions and to deliver a high pressure oxidant containing gas to flameholders. The flameholders may be provided as trapped vortex combustors, for combustion of a fuel to produce hot pressurized combustion gases. The hot pressurized combustion gases are choked before passing out of an aerodynamic duct to a turbine. Work is recovered in a turbine by expanding the combustion gases through impulse blades. By balancing the axial loading on compressor impulse blades and turbine impulse blades, asymmetrical thrust is minimized or avoided.
摘要翻译： 具有压缩机转子的燃气涡轮发动机具有压缩机脉冲叶片，其将超声波条件下的气体输送到定子。 定子包括一个或多个空气动力学管道，每个空气动力学管道具有会聚部分和发散部分，用于将选定气体减速至亚音速条件并将含有气体的高压氧化剂输送到火焰持有器。 火焰保持器可以被设置为被捕获的涡流燃烧器，用于燃烧燃料以产生热的加压燃烧气体。 热的加压燃烧气体在从空气动力学管道流出到涡轮机之前被阻塞。 通过将燃烧气体膨胀通过脉冲叶片在涡轮机中恢复工作。 通过平衡压缩机脉冲叶片和涡轮脉冲叶片上的轴向载荷，可以最小化或避免非对称推力。
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公开(公告)号：US20130142632A1
公开(公告)日：2013-06-06
申请号：US13542678
申请日：2012-07-06
IPC分类号： F04D21/00
CPC分类号： F04D21/00 , F03D1/0633 , F04D27/0207 , F04D27/0215 , F04D29/522 , F04D29/547 , F04D29/563 , F04D29/682 , F05B2240/30 , F05D2240/127 , Y02E10/721 , Y10T137/85938
摘要： A supersonic compressor including a rotor to deliver a gas at supersonic conditions to a diffuser. The diffuser includes a plurality of aerodynamic ducts that have converging and diverging portions, for deceleration of gas to subsonic conditions and then for expansion of subsonic gas, to change kinetic energy of the gas to static pressure. The aerodynamic ducts include vortex generating structures for controlling boundary layer, and structures for changing the effective contraction ratio to enable starting even when the aerodynamic ducts are designed for high pressure ratios, and structures for boundary layer control. In an embodiment, aerodynamic ducts are provided having an aspect ratio of in excess of two to one, when viewed in cross-section orthogonal to flow direction at an entrance to the aerodynamic duct.
摘要翻译： 一种超音速压缩机，其包括用于在超音速条件下将气体输送到扩散器的转子。 扩散器包括具有会聚和发散部分的多个空气动力学管道，用于将气体减速到亚音速条件，然后用于膨胀亚音速气体，以将气体的动能改变为静态压力。 空气动力学管道包括用于控制边界层的涡流产生结构，以及用于改变有效收缩比以使得即使当空气动力学管道被设计用于高压比时也能够启动的结构，以及用于边界层控制的结构。 在一个实施例中，当在与空气动力学管道的入口处垂直于流动方向的横截面中观察时，提供具有超过2比1的纵横比的空气动力学管道。
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公开(公告)号：US20130037657A1
公开(公告)日：2013-02-14
申请号：US13542673
申请日：2012-07-06
CPC分类号： F04D21/00 , F03D1/0633 , F04D27/0207 , F04D27/0215 , F04D29/522 , F04D29/547 , F04D29/563 , F04D29/682 , F05B2240/30 , F05D2240/127 , Y02E10/721 , Y10T137/85938
摘要： A vortex generator, or an array of vortex generators, for attenuating flow separation during flow of fluid over a surface. Vortex generators include a base with a forward end and a leading edge extending outward and rearward from the forward end to an outward end. The leading edge includes a first angular discontinuity at a height H1 above the base, and a second angular discontinuity at a height H2 above the base. The vortex generator(s) are configured for generating, adjacent a surface, at least two (2) vortices V1 and V2 in a fluid, and turning the outermost generated vortice toward the surface over which the fluid is passing.
摘要翻译： 涡流发生器或涡流发生器阵列，用于在流体流过表面时减弱流动分离。 涡街发生器包括具有前端和从前端到外端向外和向后延伸的前缘的底座。 前缘包括位于基座上方的高度H1处的第一角度不连续部，以及在基座之上的高度H2处的第二角度不连续部。 涡流发生器被配置用于在流体中产生邻近表面的至少两个（2）涡流V1和V2，并将最外面产生的涡流朝向流体所在的表面转动。
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