公开(公告)号：US11255343B2

公开(公告)日：2022-02-22

申请号：US15887340

申请日：2018-02-02

Applicant: General Electric Company

Inventor： Trevor Wood ,  Kishore Ramakrishnan

IPC: F04D29/54 ,  F01D9/04 ,  F04D29/66 ,  F02C3/04

Abstract: A system includes an airfoil disposed inside an engine assembly that includes a pressure side and a suction side that are coupled together at a leading edge and a trailing edge. The airfoil extends a radial length away from a central axis of the engine assembly between a hub end and a tip end. The airfoil includes a sweep feature disposed at the leading edge that is shaped to alter the air inside the engine assembly. Altering the air inside the engine assembly reduces a surface unsteady pressure level on the airfoil. The system includes a fan frame assembly comprising an inner and outer surface. The hub end is coupled with the inner surface and the tip end is coupled with the outer surface. The airfoil is integrated with the fan frame assembly such that the airfoil increases a structural load supporting capability of the fan frame assembly.

公开(公告)号：US11649834B2

公开(公告)日：2023-05-16

申请号：US17582931

申请日：2022-01-24

Applicant: General Electric Company

Inventor： Trevor Wood ,  Kishore Ramakrishnan

IPC: F04D29/54 ,  F04D29/66 ,  F01D9/04 ,  F02C3/04

CPC classification number: F04D29/544 ,  F01D9/042 ,  F04D29/667 ,  F02C3/04 ,  F05D2220/323 ,  F05D2230/80 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2260/96

Abstract: Disclosed examples include a retrofit fan frame assembly, comprising: a leading edge adjustment component coupleable to an airfoil, the leading edge adjustment component of variable chord length, the variable chord length to increase and then decrease along a radial length from a hub end of the airfoil to an opposite tip end of the airfoil; and an attachment mechanism configured to couple the leading edge adjustment component to a leading edge of the airfoil.

公开(公告)号：US10290562B2

公开(公告)日：2019-05-14

申请号：US14060262

申请日：2013-10-22

Applicant: General Electric Company

Inventor： Fei Han ,  Mehmet Arik ,  Trevor Wood ,  Charles Franklin Wolfe, Jr.

IPC: H01L23/467 ,  F21V29/63 ,  F21K9/23 ,  F21Y105/10 ,  F21Y115/10

Abstract: Apparatus and method are provided for reducing acoustical noise when cooling a device, such as a lamp system. The apparatus includes at least a set of a first synthetic jet and a second synthetic jet. The first and second synthetic jets are responsive to respective actuating signals having a phase difference (e.g., 180°) between one another chosen to reduce acoustic noise produced by the first and second synthetic jets when cooling the device.

公开(公告)号：US20140124589A1

公开(公告)日：2014-05-08

申请号：US14060262

申请日：2013-10-22

Applicant: General Electric Company

Inventor： Fei Han ,  Mehmet Arik ,  Trevor Wood ,  Charles Franklin Wolfe, JR.

IPC: H01L23/467

CPC classification number: H01L23/467 ,  F21K9/23 ,  F21V29/63 ,  F21Y2105/10 ,  F21Y2115/10 ,  H01L2924/0002 ,  H01L2924/00

Abstract: Apparatus and method are provided for reducing acoustical noise when cooling a device, such as a lamp system. The apparatus includes at least a set of a first synthetic jet and a second synthetic jet. The first and second synthetic jets are responsive to respective actuating signals having a phase difference (e.g., 180°) between one another chosen to reduce acoustic noise produced by the first and second synthetic jets when cooling the device.

Abstract translation: 提供了用于在冷却诸如灯系统的装置时降低声学噪声的装置和方法。 该装置至少包括一组第一合成射流和第二合成射流。 第一和第二合成射流响应于相应的致动信号，其具有彼此之间的相位差（例如，180°），其被选择为在冷却装置时减少由第一和第二合成射流产生的声音噪声。

公开(公告)号：US12117019B2

公开(公告)日：2024-10-15

申请号：US18301692

申请日：2023-04-17

Applicant: General Electric Company

Inventor： Trevor Wood ,  Kishore Ramakrishnan

IPC: F04D29/54 ,  F01D9/04 ,  F04D29/66 ,  F02C3/04

CPC classification number: F04D29/544 ,  F01D9/042 ,  F04D29/667 ,  F02C3/04 ,  F05D2220/323 ,  F05D2230/80 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2260/96

Abstract: Disclosed examples include an airfoil comprising: a pressure side and a suction side that are coupled together at a substantially radial trailing edge of the airfoil, wherein the substantially radial trailing edge is downstream from a leading edge, the leading edge including a sweep feature of a variable chord length, the variable chord length to include: a first increase in chord length and a decrease in chord length along a radial length from a hub end of the airfoil to an opposite tip end of the airfoil; and a second increase in chord length along the radial length from the hub end to the opposite tip end, the second increase different than the first increase.