公开(公告)号：US20240358205A1

公开(公告)日：2024-10-31

申请号：US18680262

申请日：2024-05-31

Applicant: Samsung Electronics Co., Ltd.

Inventor： Masayuki TAKADA ,  Minoru YOSHIDA

IPC: A47L5/28 ,  F04D29/30 ,  F04D29/38

CPC classification number: A47L5/28 ,  F04D29/30 ,  F04D29/384 ,  F05D2240/303

Abstract: A cleaner includes an impeller generating a suction force within the cleaner, in an airflow direction, a base portion having an increasing diameter in the airflow direction, and blades each protruding from the base portion, in a direction opposite to the airflow direction, and tilted backward in a direction opposite to the rotational direction. A wind-cutting edge of the blades faces the airflow direction and includes a proximal end closest to the boss portion along the radial direction and meeting the base portion, a protruding end furthest from the boss portion along the radial direction and spaced apart from the base portion along the airflow direction, a protruding curved portion convexly curved in the rotational direction, and a recessed curved portion concavely curved in the direction opposite to the rotational direction, the recessed curved portion being closer to the protruding end than the protruding curved portion.

公开(公告)号：US12121969B2

公开(公告)日：2024-10-22

申请号：US17770238

申请日：2020-10-13

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Christian Suchel ,  Sébastien Gouet ,  Sophie Martine Jobez ,  Christine Macheret

IPC: B22F10/80 ,  B29C65/00 ,  B29C65/48 ,  B29L31/08 ,  B33Y50/00 ,  F01D5/14 ,  F01D5/28

CPC classification number: B22F10/80 ,  B29C65/48 ,  B29C66/721 ,  B29C66/742 ,  B33Y50/00 ,  B29L2031/082 ,  F01D5/147 ,  F01D5/282 ,  F05D2230/23 ,  F05D2240/303 ,  F05D2300/603

Abstract: A method for manufacturing a blade in composite material with added metal leading edge for gas turbine aeroengine, the method including producing a batch of plurality of blade bodies in composite material; creating a digital model of a blade body from a blade in the batch of plurality of blade bodies; creating a digital model of a theoretical final blade including a leading edge; generating a digital model of a leading edge from the digital model of a blade body and final blade model; manufacturing at least one leading edge via additive manufacturing from the generated leading edge digital model; bonding each manufactured leading edge onto a blade body from the batch of plurality of blade bodies.

公开(公告)号：US20240307639A1

公开(公告)日：2024-09-19

申请号：US18676662

申请日：2024-05-29

Applicant: ResMed Pty Ltd

Inventor： Barton John KENYON ,  Emily Claire SHRUBB ,  Liam HOLLEY

IPC: A61M16/00 ,  A61M16/06 ,  A61M16/10 ,  A61M16/20 ,  F04D13/06 ,  F04D15/00 ,  F04D17/16 ,  F04D29/28 ,  F04D29/30 ,  F04D29/42 ,  F04D29/44

CPC classification number: A61M16/0069 ,  A61M16/00 ,  A61M16/024 ,  A61M16/0616 ,  A61M16/0666 ,  A61M16/0683 ,  A61M16/1045 ,  A61M16/208 ,  F04D13/068 ,  F04D15/00 ,  F04D17/162 ,  F04D17/164 ,  F04D29/281 ,  F04D29/30 ,  F04D29/424 ,  F04D29/444 ,  A61M2016/0027 ,  A61M2016/0033 ,  A61M2205/3341 ,  A61M2205/8206 ,  A61M2209/088 ,  A61M2210/06 ,  F05D2240/303 ,  F05D2240/304

Abstract: The present technology is directed to a respiratory pressure therapy system, that includes a plenum chamber pressurisable to a therapeutic pressure above ambient air pressure, a seal-forming structure to form a seal with an entrance to the patient's airways to maintain said therapeutic pressure in the plenum chamber throughout the patient's respiratory cycle in use, a positioning and stabilising structure constructed and arranged to provide an elastic force to hold the seal-forming structure in a therapeutically effective position on the patient's head, a blower configured to generate the flow of air and pressurise the plenum chamber to the therapeutic pressure, the blower having a motor, the blower being connected to the plenum chamber such that the blower is suspended from the patient's head and the axis of rotation of the motor is perpendicular to the patient's sagittal plane, and a power supply configured to provide electrical power to the blower.

公开(公告)号：US20240280024A1

公开(公告)日：2024-08-22

申请号：US18171533

申请日：2023-02-20

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nicholas Joseph Kray ,  Arthur William Sibbach

IPC: F01D5/14 ,  F01D5/28

CPC classification number: F01D5/147 ,  F01D5/282 ,  F05D2220/36 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2300/603

Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.

公开(公告)号：US12065945B2

公开(公告)日：2024-08-20

申请号：US18545535

申请日：2023-12-19

Applicant: RTX Corporation

Inventor： Carlos Calixtro ,  Alex D. Wong ,  Yanhu Guo

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F05D2220/323 ,  F05D2240/30 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/22141

Abstract: An internally cooled turbine blade for use in a gas turbine engine includes a serpentine channel extending within the turbine blade for flowing cooling air through the interior of the blade. The turbine blade includes turbulators positioned within the serpentine channel to cause or increase turbulence of the cooling air flowing through the serpentine channel, increasing the heat transfer between the turbine blade and the cooling air before exiting a plurality of air outlets within the turbine blade.

公开(公告)号：US20240271593A1

公开(公告)日：2024-08-15

申请号：US18440364

申请日：2024-02-13

Applicant: Vincent Loccisano

Inventor： Vincent Loccisano

IPC: F01D5/14

CPC classification number: F01D5/141 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2260/22141 ,  F05D2300/612

Abstract: A shrouded fluid turbine comprises annular airfoils (called shrouds) that are coaxial with and surround a rotor of a fluid turbine. A Mixer Ejector Wind Turbine consists of a turbine shroud that is engaged with a rotor. The rotor is rotationally engaged with a nacelle that houses electrical-generation equipment. The turbine shroud is engaged with support members that are engaged with an ejector shroud. At least one inflated annular tube is surrounded by an annular array of support members, which in turn is covered by a membrane, forming the annular airfoils that make up the turbine shroud and ejector shroud.

公开(公告)号：US20240209738A1

公开(公告)日：2024-06-27

申请号：US18418909

申请日：2024-01-22

Applicant: General Electric Company

Inventor： Daniel Endecott Osgood ,  Zachary Daniel Webster ,  Gregory Terrence Garay ,  Kevin Robert Feldmann

IPC: F01D5/18 ,  F01D1/12 ,  F01D5/14 ,  F01D5/28 ,  F01D11/12 ,  F01D11/14

CPC classification number: F01D5/186 ,  F01D1/12 ,  F01D5/147 ,  F01D5/284 ,  F01D11/12 ,  F01D11/122 ,  F01D11/14 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2230/311 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2300/514

Abstract: A component for a turbine engine includes a body with an exterior surface abutting a combustion flowpath for a combustion gas flow through the turbine engine, a cooling passage defined within the body, and a trench on the exterior surface. The trench includes a plurality of outlets, and a plurality of cooling holes extending from the cooling passage to the corresponding plurality of outlets.

公开(公告)号：US12000303B2

公开(公告)日：2024-06-04

申请号：US18039611

申请日：2021-11-29

Applicant: Safran Aircraft Engines

Inventor： Carole Onja Rakotoarisoa ,  Teddy Fixy ,  Guillaume Pascal Jean-Charles Gondre ,  Julien Paul Schneider-Die-Gross

IPC: F01D5/14 ,  F01D5/28

CPC classification number: F01D5/147 ,  F01D5/141 ,  F01D5/282 ,  F05D2240/303 ,  F05D2300/6034

Abstract: The invention relates to a fan blade (3) made of composite material the fibrous reinforcement of which comprises first strands (12) having a first stiffness, second strands (13) having a second stiffness and third strands (14) having a third stiffness lower than the first stiffness and greater than the second stiffness, the blade comprising a first portion (15) comprising only first strands (12), a second portion (16) comprising only second strands (13) and a third portion (17) which is located between the first and second portions (15, 16) and which comprises both first, second and third strands (12, 13, 14); there is a gradual transition of properties at the interface between the different portions (15, 16, 17).

公开(公告)号：US11988221B2

公开(公告)日：2024-05-21

申请号：US17994453

申请日：2022-11-28

Applicant: Danfoss A/S

Inventor： Jin Yan ,  Tadeu Mendonca Fagundes ,  Ryan Dingman

IPC: F04D29/28

CPC classification number: F04D29/284 ,  F05D2240/303 ,  F05D2240/304

Abstract: This disclosure relates to a refrigerant compressor including an impeller. The impeller has a blade with a wavy contour. The wavy contour reduces flow separation relative to smooth, non-wavy blades. In particular, the disclosed wavy contour creates smaller trailing edge vortexes adjacent the blades. In turn, the wavy contour of the blades improves overall compressor efficiency.

公开(公告)号：US20240125237A1

公开(公告)日：2024-04-18

申请号：US17967361

申请日：2022-10-17

Applicant: Raytheon Technologies Corporation

Inventor： David A. Knaul

IPC: F01D5/14 ,  F01D5/34

CPC classification number: F01D5/147 ,  F01D5/34 ,  F05D2230/23 ,  F05D2240/303

Abstract: An integrally bladed rotor for a gas turbine engine, including: a plurality of blades integrally formed with a hub as a single component, each of the plurality of blades having a blade body extending from the hub to an opposing blade tip surface along a longitudinal axis, each blade body having a pressure side and a suction side each extending between a leading edge and a trailing edge of the blade body; and each of the plurality of blades including a leading edge shield secured to the leading edge of the blade body.