公开(公告)号：US12055057B2

公开(公告)日：2024-08-06

申请号：US18091517

申请日：2022-12-30

Applicant: Pratt & Whitney Canada Corp.

Inventor： Hien Duong ,  Vijay Kandasamy

IPC: F04D29/68 ,  B64C21/02 ,  F01D5/14 ,  F01D9/02 ,  F01D25/16 ,  F04D29/32

CPC classification number: F01D25/162 ,  B64C21/02 ,  B64C21/025 ,  F01D5/145 ,  F01D9/02 ,  F04D29/682 ,  F04D29/684 ,  B64C2230/06 ,  B64C2230/20 ,  F04D29/324

Abstract: A strut includes a strut body extending in a radial direction and defining an airfoil shape in cross-section perpendicular to the radial direction. The airfoil shape includes a leading edge and a trailing edge. An extraction inlet is defined through an exterior surface of the strut body, in fluid communication with an internal conduit of the strut body. An injection outlet is defined through the exterior surface of the strut body, in fluid communication with the internal conduit for fluid communication through the internal conduit from the extraction inlet to the injection outlet.

公开(公告)号：US11971051B2

公开(公告)日：2024-04-30

申请号：US18207805

申请日：2023-06-09

Applicant: RTX CORPORATION

Inventor： Lisa I. Brilliant ,  Becky E. Rose ,  Yuan Dong ,  Stanley J. Balamucki

IPC: F02K3/06 ,  F02K3/04 ,  F04D19/02 ,  F04D25/04 ,  F04D29/32 ,  F04D29/52 ,  F04D29/54 ,  F04D29/56 ,  F04D29/68

CPC classification number: F04D29/547 ,  F02K3/04 ,  F02K3/06 ,  F04D19/028 ,  F04D25/045 ,  F04D29/321 ,  F04D29/522 ,  F04D29/563 ,  F04D29/681 ,  F05D2220/3217 ,  F05D2220/36 ,  F05D2260/606

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor that delivers flow to a core flowpath and a compressor section including first and second compressors. The core flowpath passes through the first compressor. The core flowpath in the first compressor has an outer diameter relative to the engine longitudinal axis. The outer diameter has a slope angle relative to the axis.

公开(公告)号：US11946497B2

公开(公告)日：2024-04-02

申请号：US17461510

申请日：2021-08-30

Applicant: 13 Mari Ltd.

Inventor： Krassimir Fotev ,  Rumen Kishev ,  Grigor Plamenov Nikolov

IPC: F15D1/00 ,  B62D35/00 ,  B63B1/36 ,  B64C21/02 ,  F15D1/12 ,  F04D29/68

CPC classification number: F15D1/003 ,  B62D35/00 ,  B63B1/36 ,  B64C21/02 ,  F15D1/004 ,  F15D1/12 ,  F04D29/681 ,  F04D29/688 ,  F05D2240/127 ,  F05D2260/2212 ,  Y02T50/10 ,  Y02T50/60

Abstract: A novel mechanism for reducing boundary layer friction and inhibiting the effects of uncontrolled fluid turbulence and turbulent layer separation, thus reducing the body drag, kinetic energy losses and lowering engine and pump fuel consumption is proposed. It steps on the type of turbulence observed in the so-called in fluid dynamics “drag crisis”. Plurality of device shapes and plurality of devices producing the wanted pure form of even plurality of counter-rotating vortices extending into the flow, i.e. tubes, are presented and discussed in detail, contrasting with the prior art. Configurations of multiple devices for the purposes of drag and fuel reduction, including their simulations and experimental results are put forward. Additional embodiments of the resulting tubes disclose use on aircraft or vessel control surfaces as stall inhibitors, use in wind turbines as dynamic range extenders, as well as use in turbines in efficient cooling mechanisms.

公开(公告)号：US11933323B2

公开(公告)日：2024-03-19

申请号：US15927117

申请日：2018-03-21

Applicant: OneSubsea IP UK Limited

Inventor： Bernt-Helge Torkildsen

IPC: F04D29/68 ,  E21B43/01 ,  E21B43/12 ,  F04D1/06 ,  F04D13/08 ,  F04D29/18 ,  F04D29/32

CPC classification number: F04D29/68 ,  E21B43/01 ,  E21B43/121 ,  F04D1/06 ,  F04D13/086 ,  F04D29/185 ,  F04D29/321 ,  F04D29/324 ,  F04D29/682 ,  F04D29/684 ,  F04D29/688

Abstract: A subsea fluid pressure-increasing machine includes an elongated member that is rotatable about a longitudinal axis. The machine also may include a plurality of impellers each having a leading edge, a trailing edge, a suction side, and a chord line defined by a line between the leading and trailing edges. Each impeller is fixedly mounted to the member such that a chord angle defined by an angle between the chord line and the rotation direction is less than or equal to a stall angle at which a maximum force is exerted on a fluid in a direction primarily parallel to the longitudinal axis when the member is rotated in the rotation direction. At least some of the impellers comprise one or more features that effectively reduce a pressure peak or specific loading of the suction side such that the axial length of the impeller is configured to be reduced without exceeding a desired specific load.

公开(公告)号：US20230349570A1

公开(公告)日：2023-11-02

申请号：US18173440

申请日：2023-02-23

Applicant: AIRIUS IP HOLDINGS, LLC

Inventor： Raymond B. Avedon

IPC: F24F7/007 ,  F04D25/08 ,  F24F7/06 ,  F04D29/54 ,  F04D29/68 ,  F04F5/16 ,  F04D19/00 ,  F04D27/00 ,  F04D27/02

CPC classification number: F24F7/007 ,  F04D19/002 ,  F04D25/088 ,  F04D27/007 ,  F04D27/0215 ,  F04D29/541 ,  F04D29/542 ,  F04D29/544 ,  F04D29/547 ,  F04D29/684 ,  F04F5/16 ,  F24F7/065 ,  F05B2240/12 ,  F05B2250/501

Abstract: An air moving device has a housing with a primary flow path and a secondary flow path that extends from a secondary inlet of the housing and empties into an inner outlet adjacent the primary flow path. An impeller assembly rotates a blade to cause air to enter the housing and flow along the primary flow path. The flow of air through the primary flow path creates a low pressure region at the inner outlet of the secondary flow path, causing air to flow through the secondary flow path and mix with the air in the primary flow path. The mixture of air flows through a downstream portion of the primary flow path having an expanded width compared to an upstream portion of the primary flow path and exits the housing. Stator vanes may extend longitudinally within the housing to cause columnar air flow. The device may be used for destratification of thermal gradients of air within an enclosure, such as a home or warehouse.

公开(公告)号：US11732612B2

公开(公告)日：2023-08-22

申请号：US17560225

申请日：2021-12-22

Applicant: Rolls-Royce North American Technologies Inc.

Inventor： Daniel E. Molnar, Jr. ,  Robert W. Heeter

IPC: F04D29/52 ,  F01D25/26 ,  F01D9/06 ,  F01D25/24 ,  F04D29/68 ,  F01D21/04

CPC classification number: F01D25/26 ,  F01D9/065 ,  F01D21/045 ,  F01D25/24 ,  F04D29/526 ,  F04D29/685 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/14 ,  F05D2260/60

Abstract: A fan case assembly adapted for use with a gas turbine engine includes a fan track liner and an annular case. The fan track liner extends circumferentially at least partway about a central axis of the gas turbine engine. The annular case is configured to support the fan track liner at a radial position relative to the central axis. The fan case assembly further includes an air recirculation duct configured to redirect air around the fan track liner.

公开(公告)号：US11725670B2

公开(公告)日：2023-08-15

申请号：US17892529

申请日：2022-08-22

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Lisa I. Brilliant ,  Becky E. Rose ,  Yuan Dong ,  Stanley J. Balamucki

IPC: F02K3/06 ,  F04D29/54 ,  F04D29/68 ,  F02K3/04 ,  F04D29/52 ,  F04D19/02 ,  F04D25/04 ,  F04D29/32 ,  F04D29/56

CPC classification number: F04D29/547 ,  F02K3/04 ,  F02K3/06 ,  F04D19/028 ,  F04D25/045 ,  F04D29/321 ,  F04D29/522 ,  F04D29/563 ,  F04D29/681 ,  F05D2220/3217 ,  F05D2220/36 ,  F05D2260/606

Abstract: A compressor section for a gas turbine engine according to an example of the present disclosure includes, among other things, a low pressure compressor including a plurality of rotor blades arranged about an axis, a high pressure compressor, and a core flowpath passing through the low pressure compressor. The core flowpath at the low pressure compressor defines an inner diameter and an outer diameter relative to the axis. The outer diameter has a slope angle relative to the axis.

公开(公告)号：US11619240B2

公开(公告)日：2023-04-04

申请号：US17407525

申请日：2021-08-20

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Martin Drolet

IPC: F04D27/02 ,  F04D29/44 ,  F01D17/16 ,  F02C3/04 ,  F04D17/10 ,  F04D29/68 ,  F01D17/12

Abstract: There is disclosed a centrifugal compressor including an impeller rotatable about an axis and a diffuser downstream of the impeller. The diffuser has walls delimiting flow passages. Plasma actuators are positioned adjacent the walls and are operatively connectable to a source of electricity. The plasma actuators have a first electrode, a second electrode, and a dielectric layer therebetween. The first electrode is upstream of the second electrode. The first electrode is exposed to the flow passage. The second electrode is shielded from the flow passage by the dielectric layer. The plasma actuators are operable to generate an electric field through the dielectric layer. The plasma actuators are located closer to inlets of the flow passage than to outlets of the flow passages. A method of operating the compressor is disclosed.

公开(公告)号：US11603852B2

公开(公告)日：2023-03-14

申请号：US15875167

申请日：2018-01-19

Applicant: General Electric Company

Inventor： Jonathan Atef Tawfik ,  Jeffrey Miles McMillen Prescott

IPC: F04D27/00 ,  F04D29/44 ,  F04D29/42 ,  F04D29/54 ,  F04D29/68 ,  F04D29/32 ,  F02C9/18 ,  F04D29/28

Abstract: A compressor bleed port apparatus includes: a compressor shroud which defines a boundary between a primary flowpath and a plenum; a bleed port including one or more apertures passing through the compressor shroud, each of the one or more apertures having an inlet communicating with the primary flowpath and an outlet communicating with the plenum, and extending along a respective centerline. Each of the one or more apertures is bounded by sidewalls, and includes a diffuser section in which the sidewalls diverge from each other in a downstream direction; A diffusing angle between the sidewalls varies over the length of the diffuser section.

公开(公告)号：US20230071034A1

公开(公告)日：2023-03-09

申请号：US17797908

申请日：2021-02-02

Applicant: TURBO SYSTEMS SWITZERLAND LTD.

Inventor： Daniel RUSCH

IPC: F04D29/42 ,  F04D29/68

Abstract: The invention relates to a stabilizer channel, in particular of a radial compressor or diagonal compressor, having an annular stabilizer chamber which encloses a main flow channel in the intake region of a compressor wheel and is delimited from the main flow channel by an annular bridge. The annular stabilizer chamber is bladeless and is connected to the main flow channel via a downstream inlet channel and an upstream outlet channel. A plurality of flow directing elements are arranged in the downstream inlet channel. The downstream inlet channel is arranged between an upstream part of the annular bridge and a downstream part of the annular bridge. The invention furthermore relates to a compressor, in particular a radial compressor or diagonal compressor, comprising the stabilizer channel according to the invention and to a turbocharger comprising the compressor.