公开(公告)号：WO2021211345A1

公开(公告)日：2021-10-21

申请号：PCT/US2021/026274

申请日：2021-04-07

Applicant: CHIU, Kin-Chung Ray

Inventor： CHIU, Kin-Chung Ray

IPC: F04D17/16 ,  F04D19/04 ,  F01D1/34 ,  F01D1/36 ,  F04D17/161 ,  F04D17/168 ,  F04D21/00 ,  F05B2240/20 ,  F05B2260/60 ,  F05D2240/20

Abstract: A vacuum pump generally comprises a low pressure portion and a high pressure portion separated by a gas impermeable partition. Gas molecules exit the low pressure portion through an opening in the partition and passively impinge on a featureless rotatable surface in the high pressure portion. A drive rotates the rotatable surface with tangential velocity in the supersonic range at multiple times the most probable velocity of the impinging gas molecules. Impinging gas molecules are ejected outwardly from the periphery of the rotatable surface generating a substantial net outward flow of gas and reducing the pressure in the low pressure portion. The vacuum pump is effective to reduce the pressure in the low pressure portion to a target minimum pressure without using seals to prevent gas molecules from leaking back to the low pressure portion and without using blades or vanes to actively impact the gas molecules.

公开(公告)号：WO2021170819A1

公开(公告)日：2021-09-02

申请号：PCT/EP2021/054872

申请日：2021-02-26

Applicant: SAFRAN AERO BOOSTERS SA

Inventor： PRINCIVALLE, Rémy, Henri, Pierre

IPC: F04D19/02 ,  F04D21/00 ,  F04D29/54

Abstract: L'invention a trait à un compresseur transsonique (24) de turbomachine (2) comprenant exactement deux ou exactement trois rangées annulaires d'aubes rotoriques (40, 44) et respectivement exactement une ou exactement deux rangée(s) annulaire(s) d'aubes statoriques intermédiaire(s) (41), intercalée(s) entre deux rangées d'aubes rotoriques (40, 44) respectives, compresseur dans lequel la vitesse du flux relative au rotor (44) en aval des aubes statoriques intermédiaires (41) est inférieure ou égale à un nombre de Mach de 0.9 sur une portion radiale des aubes (44) s'étendant sur les 40% radialement internes des aubes (44), et inférieure ou égale à un nombre de Mach de 1 sur une portion radiale s'étendant sur les 80% radialement internes des aubes (44), et inférieure ou égale à un nombre de Mach de 1.05 sur une portion radiale s'étendant sur les 20% radialement externes des aubes (44).

公开(公告)号：WO2020040774A1

公开(公告)日：2020-02-27

申请号：PCT/US2018/047745

申请日：2018-08-23

Applicant: DRESSER-RAND COMPANY

Inventor： SRINIVASAN, Ravichandra ,  SARETTO, Silvano R. ,  ALLES, Katherine ,  BROWN, Paul Morrison

IPC: F04D29/28 ,  F04D29/44 ,  F04D29/66 ,  F04D21/00

Abstract: Process fluid flow in the primary flow passage (70) of a compressor (20) is altered by selective inclusion of one or more tooth-like, annular circumferential flanges (48) in its secondary flow passage (72). The compressor's secondary flow passage is defined between opposing surfaces of a hub (40) of the impeller (26) and the opposing hub side (64) of the housing (21). The annular circumferential flange is coupled to the hub of the impeller and/or the hub side of the compressor housing within the secondary flow passage. A compressor incorporating one or more of the annular circumferential flanges in its secondary flow passage achieves more uniform flow velocity flow within the primary flow passage.

公开(公告)号：WO2015050645A1

公开(公告)日：2015-04-09

申请号：PCT/US2014/052591

申请日：2014-08-26

Applicant: GENERAL ELECTRIC COMPANY

Inventor： GADAMSETTY, Rajesh, Kumar Venkata ,  ONGOLE, Chaitanya Venkata Rama, Krishna ,  HOFER, Douglas, Carl ,  MICHELASSI, Vittorio

IPC: F04D17/02 ,  F04D17/10 ,  F04D21/00 ,  F04D29/28

CPC classification number: F04D21/00 ,  F04D17/02 ,  F04D17/08 ,  F04D29/284

Abstract: A supersonic compressor rotor and method of compressing a fluid is disclosed. The rotor includes a first and a second rotor disk, a first set and a second set of rotor vanes. The first set and second set of rotor vanes are coupled to and disposed between the first and second rotor disks. Further, the first set of rotor vanes are offset from the second set of rotor vanes. The rotor includes a first set of flow channels defined by the first set of rotor vanes disposed between the first and second rotor disks. Similarly, the rotor includes a second set of flow channels defined by the second set of rotor vanes disposed between the first and second rotor disks. Further, the rotor includes a compression ramp disposed on a rotor vane surface opposite to an adjacent rotor vane surface.

Abstract translation: 公开了一种超音速压缩机转子和压缩流体的方法。 转子包括第一和第二转子盘，第一组和第二组转子叶片。 第一组和第二组转子叶片联接到第一和第二转子盘之间并设置在第一和第二转子盘之间。 此外，第一组转子叶片偏离第二组转子叶片。 转子包括由设置在第一和第二转子盘之间的第一组转子叶片限定的第一组流动通道。 类似地，转子包括由设置在第一和第二转子盘之间的第二组转子叶片限定的第二组流动通道。 此外，转子包括设置在与相邻的转子叶片表面相对的转子叶片表面上的压缩斜坡。

公开(公告)号：WO2013009642A3

公开(公告)日：2013-03-21

申请号：PCT/US2012045817

申请日：2012-07-06

Applicant: RAMGEN POWER SYSTEMS LLC ,  LAWLOR SHAWN P

Inventor： LAWLOR SHAWN P

IPC: F04D21/00 ,  F04D27/02 ,  F04D29/56 ,  F04D29/68

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 stator. The stator may be used in a supersonic compressor that utilizes a rotor to deliver a gas at supersonic conditions to the stator. The stator 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.

Abstract translation: 定子。 该定子可用于超音速压缩机中，该超音速压缩机利用转子将气体以超音速状态输送至定子。 定子包括多个具有会聚和发散部分的空气动力管道，用于使气体减速到亚音速条件，然后使亚音速气体膨胀，从而将气体的动能改变成静压。 空气动力管道包括改变有效收缩率的结构，即使在空气动力管道设计用于高压比时也能启动，并且还可用于边界层控制结构。

公开(公告)号：WO2020242788A1

公开(公告)日：2020-12-03

申请号：PCT/US2020/033105

申请日：2020-05-15

Applicant: CARRIER CORPORATION

Inventor： JOLY, Michael, M. ,  SISHTLA, Vishnu, M.

IPC: F04D1/04 ,  F04D21/00 ,  F04D29/44 ,  F04D17/06 ,  F04D17/02 ,  F04D29/28

Abstract: A centrifugal compressor includes a casing. An impeller is arranged within the casing. The impeller is rotatable about an axis. A diffuser section is arranged within the casing. The diffuser section is positioned axially downstream from an outlet of the impeller and includes a forward portion fixed relative to the impeller and an aft portion distinct from the forward portion.

公开(公告)号：WO2012166563A8

公开(公告)日：2013-11-28

申请号：PCT/US2012039490

申请日：2012-05-25

Applicant: GEN ELECTRIC ,  HOFER DOUGLAS CARL ,  GOTTAPU DHANANJAYARAO

Inventor： HOFER DOUGLAS CARL ,  GOTTAPU DHANANJAYARAO

IPC: F04D17/12 ,  F04D21/00

CPC classification number: F04D17/127 ,  F04D21/00

Abstract: A supersonic compressor (10) includes a fluid inlet (26), a fluid outlet (28), and a fluid conduit extending there between with a supersonic compressor rotor (40) disposed therein. The supersonic compressor rotor includes a first end wall (60) and a plurality of vanes (46) coupled thereto. Each pair of the vanes defines a fluid flow channel (80). The fluid flow channel defines a flow channel inlet opening (76) and a flow channel outlet opening (78) and includes a throat portion (124). The supersonic compressor rotor also includes a second end wall (90) and at least one axially translatable fluid control device (172) 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 (178) insertable into at least a portion of the throat portion.

Abstract translation: 超音速压缩机（10）包括流体入口（26），流体出口（28）和在其间延伸的超声波压缩机转子（40）之间的流体导管。 超音速压缩机转子包括第一端壁（60）和与其连接的多个叶片（46）。 每对叶片限定了流体流动通道（80）。 流体流动通道限定流动通道入口开口（76）和流动通道出口开口（78）并且包括喉部（124）。 超音速压缩机转子还包括邻近转子定位的第二端壁（90）和至少一个可轴向平移的流体控制装置（172）。 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（178）。

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.

IPC: F04D21/00 ,  F04D27/02 ,  F04D29/56 ,  F04D29/68

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.

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。

公开(公告)号：WO2012053024A1

公开(公告)日：2012-04-26

申请号：PCT/JP2010/006152

申请日：2010-10-18

Applicant: 株式会社 日立製作所 ,  明連 千尋 ,  高橋 康雄 ,  圓島 信也

Inventor： 明連　千尋 ,  高橋　康雄 ,  圓島　信也

IPC: F04D29/38 ,  F01D5/14 ,  F01D9/02 ,  F04D21/00

CPC classification number: F01D5/147 ,  F01D5/141 ,  F04D21/00 ,  F04D29/324 ,  F04D29/384 ,  F05D2210/30 ,  F05D2240/301 ,  F05D2240/302 ,  Y02T50/673

Abstract: 　本発明の目的は、軸流回転機械中の遷音速以上の流れ場で作動する翼において、設計点における衝撃波損失の低減とストールマージンの向上を同時に達成する遷音速翼を提供する。　上記目的を達成するために、本発明では、通過する流れの全体もしくは一部が遷音速以上の流れ場に用いられる遷音速翼において、翼の各高さ位置における断面を翼の前縁３４と後縁３５を結ぶスタッガ線３８と平行に移動させ、回転機械の回転軸もしくは外周側ケーシングと接続しているハブ断面３１から、翼高さ方向で前記ハブ断面から最も離れた位置にあるチップ断面３３にかけて、各高さ位置での翼断面の重心位置を結ぶスタッキングライン３６が作動流体の上流側に移動するとともに、各高さ位置における翼断面の最大厚み位置を、前記ハブ断面３１からチップ断面３３にかけて翼の後縁側に移動するように形成する。

Abstract translation: 本发明的目的是提供一种用于轴流式旋转机器中的跨音速或超音速流场的跨音速叶片，所述跨音速叶片能够同时减小设计点处的冲击波损耗并增加失速 保证金。 为了实现上述目的，在这种用于流场中的跨音速叶片中，其中一些或全部流过的空气以跨音速或更大的速度移动，沿叶片高度的每个点处的横截面为 平行于连接叶片的前缘（34）和后缘（35）的交错线（38）移动。 此外，沿着叶片的高度的每个点处的横截面形成为使得沿着高度的每个点处连接叶片横截面的重心的位置的堆叠线（36）在上游穿过 所述工作流体，所述堆叠线从连接到所述旋转机械的轴的外周的轮毂横截面（31）或外壳延伸到位于距离所述轮毂横截面最远的点的尖端横截面（33） 叶片高度方向的截面; 并且沿着从轮毂横截面（31）到尖端横截面（33）的高度的每个点处的叶片横截面的最大厚度点在叶片的后缘的方向上移动。