公开(公告)号：US20230323774A1

公开(公告)日：2023-10-12

申请号：US17658608

申请日：2022-04-08

Applicant: Sapphire Technologies, Inc.

Inventor： Jeffrey Earl ,  Freddie Sarhan ,  Jeremy Liu

IPC: F01D1/04 ,  F01D1/32

CPC classification number: F01D1/04 ,  F01D1/32

Abstract: A first turboexpander generator is configured to decrease a temperature or pressure of a process stream flowing through the first turboexpander generator by generating electrical power from the process stream. A second turboexpander generator is configured to decrease a temperature or pressure of a process stream flowing through the second turboexpander generator by generating electrical power from the process stream. The second turboexpander generator is downstream of and receives a flow output from the first turboexpander generator. The first turboexpander generator and the second turboexpander generator each include the following features. An electric stator surrounds an electric rotor. An annulus defined by the electric rotor and the electric stator is configured to receive a process fluid flow. Magnetic bearings carry the rotor within the stator. A housing encloses the rotor and stator. The housing is hermetically sealed between an inlet and an outlet of each turboexpander generator.

公开(公告)号：US11021976B2

公开(公告)日：2021-06-01

申请号：US14862351

申请日：2015-09-23

Applicant: United Technologies Corporation

Inventor： Steven D. Porter ,  John T. Ols ,  Kyle C. Lana

IPC: F01D9/02 ,  F01D1/04 ,  F01D11/00 ,  F01D5/08

Abstract: A gas-turbine engine is provided. The gas-turbine engine comprises a high pressure turbine with an aft blade platform. A static structure may be disposed aft of the high pressure turbine and proximate a cavity defined by the aft blade platform. A vane of the static structure may have a vane platform with a shaped tip extending into the cavity.

公开(公告)号：US10784750B2

公开(公告)日：2020-09-22

申请号：US16006094

申请日：2018-06-12

Applicant: General Electric Company

Inventor： William Dwight Gerstler ,  Florian Stefan Hoefler ,  Mark Aaron Chan Chan

IPC: H02K9/20 ,  H02K5/20 ,  F04D29/58 ,  F01D25/26 ,  F01D25/12 ,  F01D9/02 ,  F01D1/04 ,  B64D27/24 ,  B64D27/02

Abstract: The present disclosure pertains to electric machines such as electric propulsion systems for aircraft that integrated cooling systems, and methods of cooling such an electric machine. Exemplary electric machines include an electric motor that has a stator, a rotor, and a drive shaft operably coupled to the rotor. Exemplary electric machines further include a motor cooling conduit that defines a pathway for conveying a cooling fluid through or around at least a portion of the electric motor, a casing assembly that circumferentially surrounds at least a portion of the electric motor, a casing assembly conduit integrally formed within at least a portion of the casing assembly which defines a pathway for conveying the cooling fluid through the at least a portion of the casing assembly, and a pump or compressor operably coupled to the drive shaft and configured to circulate the cooling fluid through the motor cooling conduit and the casing assembly conduit.

公开(公告)号：US20190218941A1

公开(公告)日：2019-07-18

申请号：US16306272

申请日：2017-07-18

Applicant: DRESSER-RAND COMPANY

Inventor： Randall W. Moll ,  Daniel Flurschutz ,  George M. Lucas

IPC: F01D25/32 ,  F01D9/04 ,  F01D1/04 ,  F01D11/00

Abstract: A drainage system for a stage of a turbine. The drainage system may include at least one annular recess defined in the inner surface of the casing of the turbine and configured to accumulate liquid therein. An axial slot and a radial slot may be formed in a diaphragm of the turbine, the axial slot extending between the upstream and downstream faces of the diaphragm. The drainage system may further include a tubular member including an axially extending tubular portion disposed in the axial slot and a radially extending tubular portion disposed in the radial slot. The radially extending tubular portion may be sized and configured to fluidly couple the at least one annular recess and the axially extending tubular portion, such that liquid in the at least one annular recess may be drained therefrom and discharged from the stage of the turbine via the axially extending tubular portion.

公开(公告)号：US10316588B1

公开(公告)日：2019-06-11

申请号：US15389787

申请日：2016-12-23

Applicant: Dandelion Energy, Inc.

Inventor： Kenneth Robertson ,  Bruce Allen Eisenhauer, Jr. ,  Luuk Sasse

IPC: E21B7/24 ,  F01D1/04 ,  F01D15/00 ,  E21B7/20 ,  E21B1/00

Abstract: A pipe shaker apparatus is configured to shake within a pipe and cause the pipe to vibrate. The pipe shaker apparatus includes a rotor having an offset mass. The offset mass is offset from a longitudinal axis through a first end piece of the rotor at a first end of the rotor and a second end piece of the rotor at a second end of the rotor. The pipe shaker apparatus also includes a tubular body having first and second ends. First and second end caps are arranged at first and second ends of the tubular body such that air is able to pass through the first end cap, enter the tubular body, cause the rotor to rotate, and exit the tubular body through the second end cap. The rotor is arranged such that rotation of the rotor by the air cases the offset mass to shake the pipe shaker apparatus.

公开(公告)号：US20180291761A1

公开(公告)日：2018-10-11

申请号：US15575724

申请日：2016-05-26

Applicant: HYDROSPIN MONITORING SOLUTIONS LTD.

Inventor： Dani Peleg

IPC: F01D17/14 ,  F01D17/10 ,  F01D15/10 ,  F01D1/04

Abstract: An energy generating system for transforming energy of fluid flow into electric energy, the system, at least in operation, comprising: a flow-changing member having a peripheral rim and mounted in a fluid path having a path surface, so as to be at least partially surrounded by said path surface, said flow-changing member being displaceable between a first position, in which at least a portion of the rim is spaced from a corresponding portion of the path surface to a first extent and a second position, in which said portion of the rim is spaced from said portion of the fluid path surface to a second extent greater than said first extent, so that increase of total volumetric flow rate of said fluid above a predetermined threshold to an increased volumetric flow rate is configured to induce displacement of said flow-changing member from said first position toward said second position, thereby causing the volumetric flow rate of said fluid at said spacing to be above said increased volumetric flow rate; and a turbine mounted in fluid communication with said fluid path at a location other than said spacing, whereby said displacement causes the volumetric flow rate of said fluid at said turbine to be below said increased volumetric flow rate.

公开(公告)号：US09909506B2

公开(公告)日：2018-03-06

申请号：US14759979

申请日：2013-01-28

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis

IPC: F02C9/18 ,  F02K3/10 ,  F02K3/077 ,  F01D1/04 ,  F02K1/78 ,  F02K3/075 ,  F02C3/04 ,  F02C3/14 ,  F02C7/08 ,  F02K3/02

CPC classification number: F02C9/18 ,  F01D1/04 ,  F02C3/04 ,  F02C3/145 ,  F02C7/08 ,  F02K1/78 ,  F02K3/025 ,  F02K3/075 ,  F02K3/077 ,  F02K3/10 ,  F05D2220/32 ,  F05D2250/31

Abstract: A gas turbine engine has a fan rotor for delivering air axially downstream into a core engine duct, which sequentially passes a turbine, a combustor, and a compressor. The core engine duct extends to a turning supply duct configured to turn the core air flow axially upstream so that the core air sequentially passes through the compressor, combustor and turbine, and into an exhaust conduit which turns the core airflow radially outwardly and axially downstream into an exhaust duct. A door is selectively opened to communicate a portion of the core airflow in the core engine duct to an augmentor with the exhaust duct isolated from the augmentor. The door is at a location prior to the core airflow reaching the compressor. A method is also disclosed.

公开(公告)号：US09797267B2

公开(公告)日：2017-10-24

申请号：US14949991

申请日：2015-11-24

Applicant: Siemens Energy, Inc.

Inventor： Andrew S. Lohaus ,  Anthony J. Malandra ,  Carmen Andrew Scribner ,  Farzad Taremi ,  Horia Flitan ,  Ching-Pang Lee ,  Gm Salam Azad ,  Tobias Buchal

IPC: F01D1/04 ,  F01D9/04 ,  F01D5/14

CPC classification number: F01D9/041 ,  F01D5/141 ,  F05D2250/74

Abstract: A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall. The airfoil includes pressure and suction sidewalls defining chordally spaced apart leading and trailing edges of the airfoil. An airfoil mean line is defined located centrally between the pressure and suction sidewalls. An angle between the mean line and a line parallel to the engine axis at the leading and trailing edges defines gas flow entry angles, α, and exit angles, β. Airfoil inlet and exit angles are substantially in accordance with inlet angle values, α, and exit angle values, β, set forth in one of Tables 1, 2, 3, and 4.

公开(公告)号：US20160281507A1

公开(公告)日：2016-09-29

申请号：US15035832

申请日：2013-12-31

Applicant: Hung Fai Henry TSO

Inventor： Hung Fai Henry TSO

IPC: F01D1/04

CPC classification number: F01D1/04 ,  F03B17/065 ,  F03D3/067 ,  F05B2210/16 ,  Y02E10/28 ,  Y02E10/38 ,  Y02E10/74 ,  Y02P70/523 ,  Y02P70/527

Abstract: Disclosed is a multi-vane-type flow kinetic energy device placed in the atmosphere with an air current or in a body of water with a water current, and comprising: a wheel shaft (2); and multiple wheel vanes (1) fixed on the wheel shaft (2) along an axial direction of the wheel shaft (2), the multiple wheel vanes (1) being uniformly distributed on the wheel shaft (2) and in a radiating arrangement, and the wheel vanes (1) driving the wheel shaft (2) to rotate unidirectionally under the effect of fluid power of the water current or air current, wherein the wheel vanes (1) comprise a wheel vane frame (7) and multiple windows (4) formed in the wheel vane frame (7), window vanes (3) are provided on the windows (4) to cover the windows (4) in a forward flow region (11) and to automatically open the windows (4) in a counter-flow region, and all the window vanes (3) are placed on the same side of the wheel vanes (1). The multi-vane-type flow kinetic energy device has the advantages of having a simple structure, being convenient to manufacture, and being low in costs, and can be popularized and applied to rivers and seas in various places globally and places with wind.

Abstract translation: 公开了一种多叶片型流动动能装置，其具有气流或大气中的水流，并且包括：轮轴（2）; 以及沿轮轴（2）的轴向固定在轮轴（2）上的多个叶轮（1），多个叶轮（1）均匀地分布在轮轴（2）上并且以辐射装置， 并且在所述水流或气流的流体动力的作用下，驱动所述轮轴（2）的所述轮叶（1）单向旋转，其中所述轮叶（1）包括轮叶架（7）和多个窗 4）形成在车轮叶片框架（7）中，窗口（3）设置在窗（4）上以覆盖前向流动区域（11）中的窗口（4）并且自动打开窗口 逆流区域，并且所有的窗叶片（3）被放置在轮叶（1）的同一侧。 多叶片式流动动能装置具有结构简单，制造方便，成本低的优点，可广泛应用于全球各地和风场的河流和海洋。

公开(公告)号：US20160215623A1

公开(公告)日：2016-07-28

申请号：US14915229

申请日：2014-08-12

Applicant: SIEMENS AKTIENGESELLSCHAFT

Inventor： Ingo Assmann ,  Thilo Müller ,  Tim Neuberg ,  Michael Stöbe

IPC: F01D1/04 ,  F01D5/14 ,  F01K13/00 ,  F01D25/24

CPC classification number: F01D1/04 ,  F01D5/147 ,  F01D25/24 ,  F01K13/006 ,  F05D2220/31

Abstract: A steam turbine has a single-shell turbine casing and specific inner casings arranged inside the turbine casing. The steam turbine has a turbine casing with an outer wall, a turbine shaft mounted rotatably about a turbine axis in the turbine casing, a first turbine part, and at least one second turbine part which is arranged downstream of the first turbine part in the axial direction of the turbine shaft, wherein the expansion direction for steam conducted through the steam turbine runs from the first turbine part to the second turbine part, wherein between the first turbine part and the second turbine part, a sealing shell is arranged on the turbine casing, in particular on the inner side of the outer wall for rotation therewith, the sealing shell being formed in a sealing manner with respect to the turbine shaft via sealing elements.

Abstract translation: 蒸汽轮机具有单壳涡轮机壳体和布置在涡轮机壳体内部的特定内壳体。 蒸汽轮机具有涡轮壳体，其具有外壁，涡轮轴可围绕涡轮机壳体中的涡轮机轴线可旋转地安装，第一涡轮部分和至少一个第二涡轮部分，其布置在轴向的第一涡轮部分的下游 涡轮轴的方向，其中通过蒸汽轮机传导的蒸汽的膨胀方向从第一涡轮机部分运行到第二涡轮部分，其中在第一涡轮机部分和第二涡轮部分之间，密封壳体布置在涡轮机壳体 特别是在外壁的内侧用于与其一起旋转，密封壳通过密封元件相对于涡轮轴以密封方式形成。