公开(公告)号：WO2014028082A3

公开(公告)日：2014-05-01

申请号：PCT/US2013041066

申请日：2013-05-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： AIELLO NICHOLAS ,  COSBY JAMES ,  CORCORAN KEVIN L

IPC: F01D5/02 ,  F02C7/00

CPC classification number: F01D5/303 ,  F01D5/3038 ,  F01D5/32 ,  F05D2260/30

Abstract: A rotor body rotates about an axis of rotation. A ledge provides a holding structure for holding blades. A plurality of blades are positioned beneath the ledge, load slot is sized to allow a mount portion of the blades to be moved radially inwardly of the ledge. The blades are moved circumferentially to have the mounted structure radially inwardly of the ledge. A lock slot is positioned on one circumferential side of the load slot. The lock slot is formed to receive a lock, and the lock is partially received within a portion of at least one of the blades, to lock the blades within the rotor, and a shield slot on a second circumferential side of the load slot. The shield slot is sized to be different from the lock slot such that a lock cannot be inadvertently positioned within the shield slot.

Abstract translation: 转子主体围绕旋转轴线旋转。 凸缘提供用于保持叶片的保持结构。 多个叶片定位在突出部下方，装载槽的尺寸被设计成允许叶片的安装部分沿着突出部的径向内侧移动。 刀片沿圆周方向移动以将安装结构径向向内突出。 锁槽位于装载槽的一个圆周侧。 锁槽形成为接收锁定，并且锁部分地容纳在至少一个叶片的一部分内，以将叶片锁定在转子内，以​​及在装载槽的第二周向侧上的屏蔽槽。 屏蔽槽的尺寸被设计成不同于锁槽，使得锁不能被无意地定位在屏蔽槽内。

公开(公告)号：WO2014204542A2

公开(公告)日：2014-12-24

申请号：PCT/US2014031818

申请日：2014-03-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： COSBY JAMES ,  HUI KWAN ,  WEISSE MICHAEL A

CPC classification number: F01D5/3007 ,  F01D5/12 ,  F01D5/141 ,  F01D5/28 ,  F01D5/30 ,  F01D5/3023 ,  F01D5/303 ,  F01D5/3038 ,  F01D5/3053 ,  Y02T50/671 ,  Y02T50/673

Abstract: A blade for use in a gas turbine engine has an airfoil and a dovetail. The airfoil extends radially outwardly of the dovetail. An inner surface of the dovetail includes a slot extending along a length of the dovetail between a leading edge and a trailing edge. A rotor and a gas turbine engine are also disclose

Abstract translation: 用于燃气涡轮发动机的叶片具有翼型件和燕尾形件。 翼型件沿燕尾径向向外延伸。 燕尾榫的内表面包括沿着燕尾榫的长度在前缘和后缘之间延伸的槽。 还公开了一种转子和燃气涡轮发动机

公开(公告)号：EP2893168A4

公开(公告)日：2016-11-16

申请号：EP13835799

申请日：2013-09-08

Applicant: UNITED TECHNOLOGIES CORP

Inventor： COSBY JAMES ,  TOMEO PETER V ,  SANTIAGO ANGEL L ,  RODRIGUEZ HERIBERTO ,  ANDERSON CARNEY R

IPC: G01P3/488 ,  F01D21/00 ,  F01D25/00 ,  F02C7/00 ,  F02C9/28 ,  F02K3/00

CPC classification number: G01P3/44 ,  F01D21/003 ,  F05D2220/30 ,  F05D2240/60 ,  F05D2270/80 ,  F05D2300/11 ,  G01P3/488 ,  Y10T74/19949

Abstract: A non-ferrous shaft includes multiple non-integral ferrous tooth components, thereby allowing a sensor to detect the shaft speed.

Abstract translation: 有色金属轴包括多个非整体铁牙组件，从而允许传感器检测轴速度。

公开(公告)号：EP2855846A4

公开(公告)日：2016-06-22

申请号：EP13829639

申请日：2013-05-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： AIELLO NICHOLAS ,  COSBY JAMES ,  CORCORAN KEVIN L

IPC: F01D5/02 ,  F01D5/30 ,  F02C7/00

CPC classification number: F01D5/303 ,  F01D5/3038 ,  F01D5/32 ,  F05D2260/30

Abstract: A rotor body rotates about an axis of rotation. A ledge provides a holding structure for holding blades. A plurality of blades are positioned beneath the ledge. A load slot is sized to allow a mount portion of the blades to be moved radially inwardly of the ledge. The blades are moved circumferentially to have the mounted structure radially inwardly of the ledge. A lock slot is positioned on one circumferential side of the load slot. The lock slot is formed to receive a lock, and the lock is partially received within a portion of at least one of the blades, to lock the blades within the rotor, and a shield slot on a second circumferential side of the load slot. The shield slot is sized to be different from the lock slot such that a lock cannot be inadvertently positioned within the shield slot.

Abstract translation: 转子体绕旋转轴线旋转。 凸缘提供用于保持叶片的保持结构。 多个叶片位于突出部下方。 装载槽的尺寸设计成允许叶片的安装部分沿着突出部分的径向内侧移动。 刀片沿圆周方向移动以使安装结构在凸缘的径向内侧。 锁槽位于装载槽的一个圆周侧。 锁槽形成为接收锁定，并且锁部分地容纳在至少一个刀片的一部分内，以将刀片锁定在转子内，以​​及在负载槽的第二周向侧上的屏蔽槽。 屏蔽槽的尺寸被设计成不同于锁槽，使得锁不能被无意地定位在屏蔽槽内。

公开(公告)号：EP2964892A4

公开(公告)日：2016-11-09

申请号：EP13877424

申请日：2013-11-08

Applicant: UNITED TECHNOLOGIES CORP

Inventor： COSBY JAMES ,  WEISSE MICHAEL A ,  HUI KWAN

IPC: F01D5/18 ,  F04D29/38

CPC classification number: F01D5/18 ,  F04D29/324 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/23 ,  F05D2230/60 ,  Y02T50/671 ,  Y02T50/676

Abstract: Hollow fan blades for gas turbine engines are disclosed. The hollow fan blades include a body having a convex side and a concave side wherein the convex side has a cavity formed therein. The cavity is covered by two covers including an inner cover that may be adhered to the body of the fan blade assembly and an outer cover that may be adhered to the inner cover and/or the body of the fan blade assembly. The covers may be made of titanium, more than two covers may be employed and more than one cavity may be employed.

Abstract translation: 公开了用于燃气涡轮发动机的中空风扇叶片。 中空风扇叶片包括具有凸侧和凹面的主体，其中凸侧具有形成在其中的空腔。 空腔由两个盖子覆盖，其中包括可以粘附到风扇叶片组件的主体的内盖和可以附着到风扇叶片组件的内盖和/或主体的外盖。 盖可以由钛制成，可以使用多于两个的盖，并且可以使用多于一个的空腔。

公开(公告)号：EP2956626A4

公开(公告)日：2016-10-19

申请号：EP14751171

申请日：2014-01-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： COSBY JAMES ,  HUI KWAN ,  WEISSE MICHAEL A

IPC: F01D5/14 ,  F01D5/18 ,  F02C7/00

CPC classification number: F01D5/147 ,  F01D5/02 ,  F01D5/3007 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2250/11 ,  F05D2250/14 ,  F05D2250/24 ,  Y02T50/671 ,  Y02T50/673

Abstract: A blade of a gas turbine engine includes a blade portion. The blade portion includes a first portion located radially outwardly that is located in a flow path and a second portion located radially inwardly of the first portion that is not located in the flow path. A plurality of external cavities is in the second portion of the blade portion.

Abstract translation: 燃气涡轮发动机的叶片包括叶片部分。 叶片部分包括位于径向向外位于流动路径中的第一部分和位于不位于流动路径中的第一部分径向向内的第二部分。 多个外部空腔位于叶片部分的第二部分中。

公开(公告)号：EP2981679A4

公开(公告)日：2016-05-25

申请号：EP14814372

申请日：2014-03-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： COSBY JAMES ,  HUI KWAN ,  WEISSE MICHAEL A

IPC: F01D5/30 ,  F01D5/14

CPC classification number: F01D5/3007 ,  F01D5/12 ,  F01D5/141 ,  F01D5/28 ,  F01D5/30 ,  F01D5/3023 ,  F01D5/303 ,  F01D5/3038 ,  F01D5/3053 ,  Y02T50/671 ,  Y02T50/673

Abstract: A blade for use in a gas turbine engine has an airfoil and a dovetail. The airfoil extends radially outwardly of the dovetail. An inner surface of the dovetail includes a slot extending along a length of the dovetail between a leading edge and a trailing edge. A rotor and a gas turbine engine are also disclose.