公开(公告)号：US20180003064A1

公开(公告)日：2018-01-04

申请号：US15197254

申请日：2016-06-29

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Thomas Lee Becker ,  Daniel Alan Niergarth ,  Bugra Han Ertas

IPC: F01D9/04 ,  F02C7/18 ,  F01D25/16 ,  F02C3/04

CPC classification number: F01D9/04 ,  F01D25/16 ,  F02C3/04 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2240/50 ,  F05D2240/60 ,  F16C27/02 ,  F16C32/0622 ,  F16C2360/23

Abstract: A system includes a gas delivery disk coupled to a second shaft, wherein the second shaft and the gas delivery disk are disposed about an axis. The gas delivery disk includes an inner axial opening configured to facilitate a first axial flow through a first passage within the second shaft, a duct configured to supply a bearing flow in a radial direction toward the axis, and a bearing face disposed within the first passage and radially interior to the inner axial opening. The bearing face is configured to receive the bearing flow, and the bearing face is configured to form a gas bearing between the bearing face and a first shaft disposed about the axis.

公开(公告)号：US20170297728A1

公开(公告)日：2017-10-19

申请号：US15132304

申请日：2016-04-19

Applicant: General Electric Company

Inventor： Daniel Alan Niergarth ,  Randy M. Vondrell ,  Brandon Wayne Miller ,  Patrick Michael Marrinan

IPC: B64D27/24 ,  B64D27/12 ,  B64D27/02 ,  F02C7/36 ,  F02C3/04 ,  F01D25/24

CPC classification number: B64D27/24 ,  B64D27/02 ,  B64D27/12 ,  B64D2027/026 ,  F01D25/24 ,  F02C3/04 ,  F02C7/36 ,  Y02T50/44 ,  Y02T50/62 ,  Y10S903/905 ,  Y10S903/906 ,  Y10S903/907

Abstract: A propulsion system for an aircraft is provided having a propulsion engine configured to be mounted to the aircraft. The propulsion engine includes an electric machine defining an electric machine tip speed during operation. The propulsion system additionally includes a fan rotatable about a central axis of the electric propulsion engine with the electric machine. The fan defines a fan pressure ratio, RFP, and includes a plurality of fan blades, each fan blade defining a fan blade tip speed. The electric propulsion engine defines a ratio of the fan blade tip speed to electric machine tip speed that is within twenty percent of the equation, 1.01×RFP−0.311, such that the propulsion engine may operate at a desired efficiency.

公开(公告)号：US20170234324A1

公开(公告)日：2017-08-17

申请号：US15043036

申请日：2016-02-12

Applicant: General Electric Company

Inventor： Daniel Alan Niergarth ,  Darek Tomasz Zatorski ,  Christopher James Kroger

IPC: F04D29/36 ,  F04D29/32

CPC classification number: F04D29/36 ,  B64C11/38 ,  F04D29/325 ,  F04D29/362 ,  Y02T50/66

Abstract: The variable pitch propeller assembly includes a hub. The variable pitch propeller assembly also includes a plurality of propeller blade assemblies spaced circumferentially about the hub. Each of the plurality of propeller blade assemblies configured to rotate a respective propeller blade. The variable pitch propeller assembly also includes a hydraulic fluid port assembly integrally formed and including at least three hydraulic fluid ports configured to receive respective flows of hydraulic fluid from a stationary hydraulic fluid transfer sleeve. The variable pitch propeller assembly also includes a pitch actuator assembly coupled in flow communication with at least three hydraulic fluid ports through respective hydraulic fluid transfer tubes. The pitch actuator coupled to the plurality of propeller blade assemblies to selectively control a pitch of the propeller blades. The pitch actuator assembly includes a travel stop configured to limit a rotation of at least one of the pitch actuator assemblies.

公开(公告)号：US20160290228A1

公开(公告)日：2016-10-06

申请号：US14679096

申请日：2015-04-06

Applicant: General Electric Company

Inventor： Gert J. van der Merwe ,  Brandon Wayne Miller ,  Daniel Alan Niergarth

IPC: F02C7/06 ,  F01D5/14 ,  F02K3/06 ,  F16C19/36 ,  F16C19/54

CPC classification number: F02K3/06 ,  B64C11/06 ,  F01D7/00 ,  F02C3/107 ,  F02C9/58 ,  F04D29/0566 ,  F04D29/059 ,  F04D29/323 ,  F05D2220/36 ,  F05D2240/54 ,  F05D2260/74 ,  F05D2260/79 ,  F16C19/364 ,  F16C19/545 ,  F16C19/547 ,  F16C33/62 ,  F16C2204/52 ,  F16C2206/40 ,  F16C2360/23 ,  Y02T50/671 ,  Y02T50/673

Abstract: A gas turbine engine including a core engine and a variable pitch fan arranged in flow communication with the core engine is provided. The variable pitch fan includes a plurality of blades coupled to a disk, the blades and disk configured to rotate together about an axial direction of the engine. A rotatable front hub may be provided over a front end of the variable pitch fan, including the disk. The gas turbine engine additionally includes a plurality of trunnion mechanisms coupling each of the plurality of fan blades to the disk. Each trunnion mechanism includes a bearing having one or more components formed of a non-ferrous material, decreasing a weight of the respective trunnion mechanism and allowing for, e.g., a smaller front hub.

Abstract translation: 提供了一种燃气涡轮发动机，其包括与所述核心发动机流体连通地布置的核心发动机和变桨距风扇。 可变间距风扇包括耦合到盘的多个叶片，叶片和盘构造成围绕发动机的轴向方向一起旋转。 可旋转的前轮毂可以设置在可变桨距风扇的前端上，包括盘。 燃气涡轮发动机还包括将多个风扇叶片中的每一个联接到盘的多个耳轴机构。 每个耳轴机构包括具有由有色金属材料形成的一个或多个部件的轴承，减小相应的耳轴机构的重量并允许例如较小的前轮毂。