公开(公告)号：US20200010172A1

公开(公告)日：2020-01-09

申请号：US16504043

申请日：2019-07-05

Applicant: United Technologies Corporation

Inventor： John Harner ,  James J. McPhail

IPC: B64C11/14 ,  F02C7/04 ,  F04D29/52

Abstract: A nosecone assembly having an axially extending centerline is provided. The assembly includes a nosecone body and at least one access panel. The nosecone body has at least one wall that defines an interior cavity. The wall has an interior surface contiguous with the interior cavity, and at least one window aperture extending through the wall. The access panel has first and second face surfaces. The access panel is attached to the wall interior surface within an attachment region that includes first and second attachment region portions partially contiguous with one another. The first and second attachment region portions define an interior unattached region, and the interior unattached region is aligned with the window aperture.

公开(公告)号：US10132174B2

公开(公告)日：2018-11-20

申请号：US14685030

申请日：2015-04-13

Applicant: United Technologies Corporation

Inventor： Colin J. Kling ,  Thomas J. Robertson ,  Carney R. Anderson ,  James J. McPhail

IPC: F01D5/32 ,  F01D5/28 ,  F01D5/30 ,  F02K7/06

Abstract: The present disclosure provides devices related to aircraft engine fan assemblies and blade lock retainers. In various embodiments, a blade lock retainer is formed from sheet metal and comprises an annular ring portion, an outer retainer tab portion, and an inner tab portion. In various embodiments, the outer retainer tab portion is disposed on an outer circumference of the annular ring portion, oriented substantially perpendicular to the annular ring portion, and extends in an aft direction from the annular ring portion. In various embodiments, the inner retainer tab portion is disposed on an inner circumference of the annular ring portion and radially aligned with the outer retainer tab portion, oriented substantially perpendicular to the annular ring portion, and extends in a forward direction from the annular ring portion.

公开(公告)号：US20160298469A1

公开(公告)日：2016-10-13

申请号：US14685030

申请日：2015-04-13

Applicant: United Technologies Corporation

Inventor： Colin J. Kling ,  Thomas J. Robertson ,  Carney R. Anderson ,  James J. McPhail

IPC: F01D5/32 ,  F01D5/28

CPC classification number: F01D5/326 ,  F01D5/282 ,  F01D5/3015 ,  F01D5/3076 ,  F02K7/06 ,  F05D2220/36 ,  F05D2230/54 ,  F05D2300/121 ,  F05D2300/133 ,  F05D2300/173 ,  F05D2300/174 ,  F05D2300/175 ,  F05D2300/603 ,  Y02T50/672

Abstract: The present disclosure provides devices related to aircraft engine fan assemblies and blade lock retainers. In various embodiments, a blade lock retainer is formed from sheet metal and comprises an annular ring portion, an outer retainer tab portion, and an inner tab portion. In various embodiments, the outer retainer tab portion is disposed on an outer circumference of the annular ring portion, oriented substantially perpendicular to the annular ring portion, and extends in an aft direction from the annular ring portion. In various embodiments, the inner retainer tab portion is disposed on an inner circumference of the annular ring portion and radially aligned with the outer retainer tab portion, oriented substantially perpendicular to the annular ring portion, and extends in a forward direction from the annular ring portion.

Abstract translation: 本公开提供了与飞机发动机风扇组件和叶片锁定保持器相关的装置。 在各种实施例中，刀片锁定保持器由金属板形成并且包括环形环部分，外部保持器突出部分和内部突出部分。 在各种实施例中，外保持器突片部分设置在环形环部分的外圆周上，该圆环部分的外圆周基本上垂直于环形环部分，并且从环形环部分沿向后的方向延伸。 在各种实施例中，内部保持器突出部分设置在环形环部分的内圆周上并且与外部保持器突片部分径向对准，该外部保持器突出部分基本上垂直于环形环部分定向，并且从环形环部分向前方向延伸 。

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：US20160229543A1

公开(公告)日：2016-08-11

申请号：US14615543

申请日：2015-02-06

Applicant: United Technologies Corporation

Inventor： James J. McPhail ,  Isaac Jon Hogate ,  Victor G. Filipenco

IPC: B64D15/00 ,  F01D25/02 ,  F01D5/02

CPC classification number: B64D15/00 ,  F01D5/02 ,  F01D25/02 ,  F02C7/04 ,  F05D2220/32 ,  F05D2250/713 ,  F05D2300/10 ,  F05D2300/512 ,  F05D2300/611

Abstract: A gas turbine engine is provided having a nose cone, wherein the nose cone is symmetrically disposed about an axis. The nose cone includes a leading edge and a base. A forward section is disposed between the leading edge and the base and has a radius at any axial location defined by a first equation. A transition section is disposed between the forward section and the base and has a radius at any axial location defined by a second equation. The first equation is different than the second equation.

Abstract translation: 提供了一种具有鼻锥体的燃气涡轮发动机，其中鼻锥体围绕轴线对称设置。 鼻锥包括前缘和底座。 前进部分设置在前缘和基座之间，并且在由第一等式限定的任何轴向位置处具有半径。 过渡部分设置在前部和基部之间，并且在由第二等式限定的任何轴向位置处具有半径。 第一个方程与第二个方程不同。