公开(公告)号：US20240360835A1

公开(公告)日：2024-10-31

申请号：US18766133

申请日：2024-07-08

申请人： Hunter Fan Company

发明人： Charles William Botkin ,  Bobby Neal Norwood ,  Jason Matthew McPherson

IPC分类号： F04D25/08 ,  F04D29/30 ,  F04D29/56

CPC分类号： F04D25/088 ,  F04D29/30 ,  F04D29/563

摘要： A ceiling fan or ceiling fan includes a body defining an interior passage having an inlet and an outlet provided on the body. The inlet, outlet, and interior passage can be annular. An impeller is mounted within the interior passage and driven by a motor mounted within the body to draw a volume of air through the interior passage from the inlet to the outlet. A movable deflector including an inner angled surface and a lower angled surface is provided at the outlet to direct the airflow in a generally outward or generally downward direction, respectively.

公开(公告)号：US12066035B1

公开(公告)日：2024-08-20

申请号：US18234663

申请日：2023-08-16

申请人： Rolls-Royce North American Technologies Inc. ,  Rolls-Royce Corporation

发明人： Robert W. Heeter ,  Daniel E. Molnar, Jr. ,  Michael S. Krautheim

IPC分类号： F02K3/06 ,  F04D29/52 ,  F04D29/54 ,  F04D29/56 ,  F04D29/68

CPC分类号： F04D29/563 ,  F02K3/06 ,  F04D29/526 ,  F04D29/542 ,  F04D29/68 ,  F05D2220/36 ,  F05D2240/12 ,  F05D2240/14

摘要： A fan case assembly adapted for use with a gas turbine engine includes a case at extends circumferentially at least partway about an axis of the gas turbine engine and a plurality of vanes. The case is formed to define a channel that that extends circumferentially at least partway about the axis. The plurality of vanes are arranged in the channel and spaced apart circumferentially about the axis.

公开(公告)号：US12044133B2

公开(公告)日：2024-07-23

申请号：US18251755

申请日：2021-10-22

申请人： AECC SHANGHAI COMMERCIAL AIRCRAFT ENGINE MANUFACTURING CO., LTD. ,  AECC COMMERCIAL AIRCRAFT ENGINE CO., LTD.

发明人： Jiaguang Wang ,  Bin Zhu ,  Miaomiao Zhang ,  Haomai Gao ,  Chuanjun Cao

IPC分类号： F01D17/16 ,  F04D29/56

CPC分类号： F01D17/16 ,  F01D17/162 ,  F04D29/563 ,  F05D2220/323 ,  F05D2240/128 ,  F05D2260/60

摘要： An adjustable stator blade position maintaining structure for an aero-engine compressor, which keeps an adjustable stator blade at a preset position when a compressor works. The adjustable stator blade position maintaining structure includes a positioning section, a limiting section and a force transmission section The positioning section is mounted in a mounting hole in a casing; the limiting section is cone-shaped and thus fits into a conical hole in the top of a journal of the adjustable stator blade; and the force transmission section is connected between the positioning section and the limiting section so as to transmit a load from the limiting section to the positioning section.

公开(公告)号：US11767853B2

公开(公告)日：2023-09-26

申请号：US17287918

申请日：2019-10-08

申请人： Dyson Technology Limited

发明人： Lucy Horton ,  Timothy Neil Jukes ,  Charles Edward Pouget ,  Joseph Robert Carling ,  Ryan Alexander Hughes ,  Steven Eduard Peet ,  Peter Harley

IPC分类号： F04D25/08 ,  F04F5/46 ,  F24F13/10 ,  F04D25/10 ,  F04D25/12 ,  F04D29/40 ,  F04D29/52 ,  F04D29/56 ,  F24F13/065

CPC分类号： F04D25/10 ,  F04D25/12 ,  F04D29/403 ,  F04D29/524 ,  F04D29/563 ,  F24F13/065 ,  F24F13/10

摘要： There is provided a nozzle for a fan assembly. The nozzle comprises an air inlet, a first air outlet and a second air outlet that are oriented in convergent directions, and a valve for controlling the first and second air outlets. The valve comprises one or more valve members that are moveable to simultaneously adjust the size of the first air outlet and inversely adjust the size of the second air outlet. The nozzle further comprises a third air outlet and a fourth air outlet, the third air outlet being opposite the fourth air outlet, the third and fourth air outlets being oriented in convergent directions, and the third air outlet and the fourth air outlet each being substantially perpendicular to each of the first and second air outlets.

公开(公告)号：US20230265766A1

公开(公告)日：2023-08-24

申请号：US18018073

申请日：2021-07-29

申请人： MTU AERO ENGINES AG

发明人： Alexander Halcoussis ,  Harsimar Sahota

IPC分类号： F01D17/16 ,  F01D5/14 ,  F04D29/56

CPC分类号： F01D17/162 ,  F01D5/143 ,  F04D29/563 ,  F05D2250/713

摘要： A guide vane for arrangement in a gas duct of a turbomachine, including a guide vane blade and an outer platform which, relative to a longitudinal axis of the turbomachine, is arranged radially on an outside on the guide vane blade. The outer platform delimits the gas duct with an inner wall surface radially to the outside. The inner wall surface has a curved profile with an inflection point when viewed in an axial section, the inner wall surface having a concave curvature in a first axial section which is upstream from the inflection point with respect to a flow through the gas duct, and a convex curvature in a second axial section which is arranged downstream from the inflection point with respect to the flow through the gas duct.

公开(公告)号：US11661183B2

公开(公告)日：2023-05-30

申请号：US17203413

申请日：2021-03-16

申请人： D. Anthony Windisch

发明人： D. Anthony Windisch

IPC分类号： F04D19/00 ,  B64C29/00 ,  B64C13/50 ,  F04D29/56

CPC分类号： B64C29/0066 ,  B64C13/503 ,  F04D19/007 ,  F04D29/563

摘要： An aircraft having a frame assembly that supports a compressor having an outer shell that defines front and rear nozzle ports with rotatable nozzles for selectable vertical or horizontal thrust. The inner shell and the outer shell define an intake gap therebetween such as an annulus. A first fan unit within the inner shell and is configured to exhaust air through the front nozzle ports. A second fan unit within the outer shell intakes air through the intake gap and exhausts air through the rear nozzle ports. The fan units are preferably connected to one another via a drive shaft that is surrounded by a streamlining tube. The fan units each include a plurality of fans having stators therebetween. The stators have a plurality of stator arms with a wing structure pivotally attached to the trailing edge for angling air flow from a front to a rear fan.

公开(公告)号：US20190249572A1

公开(公告)日：2019-08-15

申请号：US16266612

申请日：2019-02-04

申请人： MTU Aero Engines AG

发明人： Werner HUMHAUSER

IPC分类号： F01D25/28 ,  F01D17/16 ,  F01D25/24

CPC分类号： F01D17/162 ,  F04D29/563 ,  F05D2260/36 ,  F05D2260/37

摘要： Described is a connecting device (50) for a variable vane (51) of a gas turbine (10), in particular of an aircraft gas turbine, the connecting device including a trunnion element (52) connected to a respective vane (51); a lever element (54) connected to the trunnion element (52), the lever element (54) and the trunnion element (52) being movable together about a trunnion axis of rotation (ZD). It is provided that the lever element (54) and the trunnion element (52) be aligned with each other by a positioning element (68), the positioning element (68) being received in a trunnion receptacle (60) and a lever receptacle (66, 66a, 66b).

公开(公告)号：US20190195239A1

公开(公告)日：2019-06-27

申请号：US16326866

申请日：2017-08-22

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Olivier BAZOT ,  Jérémy Philippe Pierre EDYNAK

IPC分类号： F04D29/56 ,  F04D29/64 ,  F01D17/16

CPC分类号： F04D29/563 ,  F01D17/16 ,  F01D17/162 ,  F04D29/644 ,  F05D2230/80 ,  F05D2240/128

摘要： An interface member equips a control ring of a high-pressure compressor of an engine. This control ring has at least one housing intended to partially house a guide shoe. This interface member includes a central wall to which two holding tabs are secured, delimiting a through-housing having dimensions substantially identical to the initial dimensions of the housing, and suitable for being inserted into the housing, after it has been machined to receive same following a deformation, until the holding tabs keep it stationary relative to the control ring.

公开(公告)号：US20190120250A1

公开(公告)日：2019-04-25

申请号：US15789456

申请日：2017-10-20

申请人： Rolls-Royce Corporation ,  Rolls-Royce North American Techologies Inc.

发明人： Christopher Hall ,  Russell White ,  Jonathan Acker ,  Lyle Helvie

IPC分类号： F04D29/56 ,  F04D29/64

CPC分类号： F04D29/563 ,  F04D29/644

摘要： An apparatus and method of controlling the position of a variable vane in a compressor and a kit for adding such apparatus to the compressor are disclosed. The vane is coupled to a unison ring, a cam is secured to a torque tube, a cam follower is secured to the unison ring. The cam follower is secured such that a wall of the cam follower is in contact with the cam. Rotation of the torque tube causes movement of the cam, and movement of the cam moves the cam follower, thereby moving the unison ring and the variable vane coupled thereto.

公开(公告)号：US20190078460A1

公开(公告)日：2019-03-14

申请号：US15698905

申请日：2017-09-08

申请人： PRATT & WHITNEY CANADA CORP.

发明人： David MENHEERE ,  Andrew MARSHALL ,  Richard A. KOSTKA

IPC分类号： F01D17/16 ,  F01D9/04

CPC分类号： F01D17/162 ,  F01D9/041 ,  F04D29/563 ,  F05D2240/12 ,  F05D2260/38 ,  F05D2260/53

摘要： A variable stator guide vane system for a gas turbine engine comprises a set of vanes circumferentially distributed around a central axis and rotatably mounted for rotation about respective spanwise axes. A ring gear is rotatably mounted about the central axis. Pinion gears are operatively coupled to respective ones of the vanes and in driving engagement with the ring gear. Biasing members individually bias the pinion gears in meshing engagement with the ring gear.