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公开(公告)号：WO2013009643A3
公开(公告)日：2013-01-17
申请号：PCT/US2012/045823
申请日：2012-07-06
Applicant: RAMGEN POWER SYSTEMS, LLC , ROBERTS, William, Byron , LAWLOR, Shawn, P.
Inventor： ROBERTS, William, Byron , LAWLOR, Shawn, P.
Abstract: 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 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. In an embodiment, the number of leading edges are minimized, and may be less than half, compared to the number of blades in the accompanying rotor.
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公开(公告)号：WO2013009643A2
公开(公告)日：2013-01-17
申请号：PCT/US2012045823
申请日：2012-07-06
Applicant: RAMGEN POWER SYSTEMS LLC , ROBERTS WILLIAM BYRON , LAWLOR SHAWN P
Inventor： ROBERTS WILLIAM BYRON , LAWLOR SHAWN P
IPC: F04D21/00
CPC classification number: F04D21/00 , F04D27/0207 , F04D27/0215 , F04D29/522 , F04D29/547 , F04D29/563 , F04D29/682 , F05D2240/127 , Y02E10/721 , Y10T137/85938
Abstract: 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 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. In an embodiment, the number of leading edges are minimized, and may be less than half, compared to the number of blades in the accompanying rotor.
Abstract translation: 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改变有效收缩比的结构，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，并且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。 在一个实施例中，前缘的数量最小化，并且可以小于伴随转子中的叶片数量的一半。
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公开(公告)号：WO2013009636A2
公开(公告)日：2013-01-17
申请号：PCT/US2012/045803
申请日：2012-07-06
Applicant: RAMGEN POWER SYSTEMS, LLC , ROBERTS, William, Byron , LAWLOR, Shawn, P.
Inventor： ROBERTS, William, Byron , LAWLOR, Shawn, P.
IPC: F02C3/06
CPC classification number: 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
Abstract: A gas turbine engine having a compressor section using blades on a rotor to deliver a gas at supersonic conditions to a stator. The stator includes one or more of aerodynamic ducts that have converging and diverging portions for deceleration of the gas to subsonic conditions and to deliver a high pressure gas to combustors. The aerodynamic ducts include structures for changing the effective contraction ratio to enable starting even when designed for high pressure ratios, and structures for boundary layer control. In an embodiment, aerodynamic ducts are provided having an aspect ratio of two to one (2:1) or more, when viewed in cross-section orthogonal to flow direction at an entrance to the aerodynamic duct.
Abstract translation: 具有压缩机部分的燃气涡轮发动机，所述压缩机部分使用转子上的叶片将超音速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，其具有用于使气体减速到亚音速条件并将高压气体输送到燃烧器的会聚和发散部分。 空气动力管道包括改变有效收缩率的结构，即使设计用于高压比时也可以启动，还可用于边界层控制结构。 在一个实施例中，当在与空气动力管道的入口处的流动方向正交的横截面上观察时，提供具有二比一（2:1）或更大的纵横比的空气动力学管道。
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公开(公告)号：WO2013009636A3
公开(公告)日：2013-05-10
申请号：PCT/US2012045803
申请日：2012-07-06
Applicant: RAMGEN POWER SYSTEMS LLC , ROBERTS WILLIAM BYRON , LAWLOR SHAWN P
Inventor： ROBERTS WILLIAM BYRON , LAWLOR SHAWN P
CPC classification number: 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
Abstract: A gas turbine engine having a compressor section using blades on a rotor to deliver a gas at supersonic conditions to a stator. The stator includes one or more of aerodynamic ducts that have converging and diverging portions for deceleration of the gas to subsonic conditions and to deliver a high pressure gas to combustors. The aerodynamic ducts include structures for changing the effective contraction ratio to enable starting even when designed for high pressure ratios, and structures for boundary layer control. In an embodiment, aerodynamic ducts are provided having an aspect ratio of two to one (2:1) or more, when viewed in cross-section orthogonal to flow direction at an entrance to the aerodynamic duct.
Abstract translation: 一种具有压缩机部分的燃气涡轮发动机，该压缩机部分使用转子上的叶片将超声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，其具有用于将气体减速到亚音速条件并且将高压气体输送到燃烧器的会聚和发散部分。 空气动力学管道包括用于改变有效收缩比以便即使设计用于高压比也能起动的结构，以及用于边界层控制的结构。 在一个实施例中，当在空气动力学管道的入口处垂直于流动方向的横截面观察时，提供具有两比一（2:1）或更大的纵横比的空气动力学管道。
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