公开(公告)号：US20160097290A1

公开(公告)日：2016-04-07

申请号：US14839315

申请日：2015-08-28

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies, Inc.

Inventor： Roy D. Fulayter ,  Crawford F. Smith

IPC: F01D9/00 ,  F01D25/24 ,  B64D29/06

CPC classification number: F01D9/00 ,  B64C23/06 ,  B64D29/06 ,  B64D33/02 ,  B64D2033/0226 ,  F01D25/24 ,  F05D2220/323 ,  F05D2240/127 ,  Y02T50/162

Abstract: A nacelle for a gas turbine jet engine for an aircraft includes flow disruptors to provide boundary layer turbulence when the engine is exposed to air flow that is obtuse to direction of travel of the engine.

Abstract translation: 用于飞行器的燃气涡轮喷气发动机的机舱包括流动干扰器，以在发动机暴露于与发动机的行进方向无关的空气流时提供边界层湍流。

公开(公告)号：US20140294581A1

公开(公告)日：2014-10-02

申请号：US14145488

申请日：2013-12-31

Applicant: Rolls-Royce Corporation

Inventor： Jonathan M. Rivers ,  Roy D. Fulayter

IPC: F01D25/24 ,  B23P15/04

CPC classification number: F01D25/24 ,  B23P15/04 ,  B64D29/08 ,  B64D33/02 ,  B64D2033/0273 ,  F02C7/04 ,  F02K3/06 ,  Y10T29/49238

Abstract: An integrated access panel is disclosed that can be used to assist in adjusting a component like a fan blade of a turbofan engine. in one form the integrated access panel is hinged at one end such that the panel remains attached during adjustment of the fan blade. The access panel can be positioned in an angled flow surface of a nacelle such that the fan blade cannot be removed from a wheel without removal of the nacelle or opening of the access panel. The integrated access panel can be spring-loaded and positioned to allow the fan blade to be removed from a wheel by moving the access panel out of the way. Subsequent blade removal can occur by rotation of the wheel to locate another blade in proximity to the access panel.

Abstract translation: 公开了一种集成检修面板，其可用于帮助调整诸如涡扇风扇发动机的风扇叶片的部件。 在一种形式中，集成检修面板在一端铰接，使得在调节风扇叶片期间板保持固定。 检修面板可以定位在机舱的倾斜的流动表面中，使得风扇叶片不能从车轮上移除，而不需要移除机舱或打开检修面板。 集成的检修面板可以是弹簧加载和定位的，以允许通过将检修面板移开的方式将风扇叶片从轮子上移除。 随后的叶片移除可以通过轮的旋转而发生，以将另一个叶片定位在接近面板附近。

公开(公告)号：US20140255188A1

公开(公告)日：2014-09-11

申请号：US14099519

申请日：2013-12-06

Applicant: Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce Corporation

Inventor： Roy D. Fulayter ,  Daniel K. Vetters ,  Bronwyn Power

IPC: F01D5/12

CPC classification number: F01D5/12 ,  F01D17/162 ,  F04D29/323 ,  F04D29/563 ,  F05D2220/36 ,  Y02T50/671

Abstract: A gas turbine engine airflow member is disclosed having spherical interface shapes at a tip end and a hub end. In one embodiment, the airflow member is a fan blade. The spherical interface shapes can be convex or concave. In one form, the tip end spherical shape is axially shifted aft relative to a hub end. The tip end can include relatively little forward portion in an expanding flow path with predominant portion of the tip end in a contracting flow path. Such a configuration can occur with a midpoint and trailing edge located in the contracting flow path. A center of gravity of a swept airflow member having spherical end shape can be located on a pivot axis of the airflow member. Divot depressions can be provided to permit concave flow path shapes.

Abstract translation: 公开了一种在顶端和轮毂端具有球形界面形状的燃气涡轮发动机气流元件。 在一个实施例中，气流构件是风扇叶片。 球形界面形状可以是凸的或凹的。 在一种形式中，尖端球形相对于轮毂端轴向向后移动。 尖端可以包括在扩张流动路径中相对较小的前部，其顶端的主要部分处于收缩流动路径中。 这种配置可以发生在位于收缩流动路径中的中间点和后沿。 具有球形端部形状的扫气流构件的重心可以位于气流构件的枢轴上。 可以提供Divot凹陷以允许凹形流动路径形状。