公开(公告)号：US20160288902A1

公开(公告)日：2016-10-06

申请号：US15030787

申请日：2014-05-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Colin J. Kling ,  Scot A. Webb ,  James J. McPhail

IPC: B64C11/14 ,  F02C3/04

CPC classification number: B64C11/14 ,  F01D5/066 ,  F02C3/04 ,  F05D2220/36 ,  F05D2230/23 ,  Y02T50/672

Abstract: A fan assembly of a gas turbine engine, a method for fabricating a fan assembly for a gas turbine engine, and a gas turbine engine are disclosed. The fan assembly of the gas turbine engine may include a spinner section, a fan hub section aft of the spinner section, and a joint therebetween. The fan assembly may further include a support ring for internally supporting the spinner, the support ring including a first portion facing the fan hub and a second portion connected to the spinner at the joint, wherein the connection between the second portion and the joint is a bonded connection.

Abstract translation: 公开了一种燃气涡轮发动机的风扇组件，用于制造燃气涡轮发动机的风扇组件的方法和燃气涡轮发动机。 燃气涡轮发动机的风扇组件可以包括旋转器部分，旋转器部分的后部的风扇毂部分以及它们之间的接头。 风扇组件还可以包括用于内部支撑旋转器的支撑环，支撑环包括面向风扇毂的第一部分和在接头处连接到旋转器的第二部分，其中第二部分和关节之间的连接是 绑定连接。

公开(公告)号：US20160215784A1

公开(公告)日：2016-07-28

申请号：US14917485

申请日：2014-08-04

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Lee M. Drozdenko ,  James O. Hansen ,  Maria C. Kirejczyk ,  Scot A. Webb ,  Jesse C. Meyer ,  Brandon A. Gates ,  Richard B. Bergethon ,  Michael A. Morden

IPC: F04D29/02 ,  F04D29/32 ,  F04D29/64 ,  F04D29/38

CPC classification number: F04D29/023 ,  F01D5/288 ,  F04D29/324 ,  F04D29/325 ,  F04D29/388 ,  F04D29/644 ,  F05D2240/303 ,  F05D2300/173 ,  F05D2300/174 ,  F05D2300/6033

Abstract: An airfoil member (100) comprising has a substrate (120) along at least a portion of an airfoil (102) of the airfoil member. A sheath (122) has a channel (144) receiving a portion (160) of the substrate. A scrim (200) is between the substrate and the sheath. A spacer (220) is between the sheath and the substrate and has a plurality of spaced-apart portions (232, 234) with gaps between the spaced-apart portions.

Abstract translation: 翼型件（100）包括沿翼型件的翼型（102）的至少一部分具有基底（120）。 护套（122）具有容纳衬底的一部分（160）的通道（144）。 稀松布（200）在基材和护套之间。 间隔物（220）位于护套和衬底之间并且具有多个间隔开的部分（232,234），其间隔开间隔开的部分。

公开(公告)号：US20160017803A1

公开(公告)日：2016-01-21

申请号：US14781943

申请日：2014-03-31

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas W. Ward ,  Scot A. Webb

IPC: F02C7/047

CPC classification number: F02C7/047 ,  F01D25/02 ,  F05D2300/5024 ,  Y02T50/672

Abstract: A de-icing system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a forward assembly and a rear assembly adjacent to the forward assembly. One of the forward assembly and the rear assembly is rotatable relative to the other to generate an amount of air friction between said forward and rear assemblies.

Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的除冰系统包括与前部组件相邻的前组件和后组件。 前组件和后组件中的一个可相对于另一组件旋转，以在所述前组件和后组件之间产生一定量的空气摩擦。