公开(公告)号：US20200217271A1

公开(公告)日：2020-07-09

申请号：US16823643

申请日：2020-03-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Alex J. Simpson ,  Robert T. Knowlton

IPC: F02K1/06 ,  B64D33/04 ,  F16C11/06 ,  F16C11/02 ,  F02K1/12 ,  F16C11/04 ,  F02K3/075

Abstract: Disclosed is a linkage assembly for a gas turbine engine having a link having a first end, a second end, and a rod extending therebetween, the first end having a first sliding bearing disposed within a first sliding bearing housing, a fastener comprising a first flange and a second flange, a pin extending between the first flange and the second flange, wherein the first sliding bearing is pivotally connected to the pin; and a biasing member secured between the first flange and the sliding bearing housing, the biasing member contacting the sliding bearing housing and biasing the link against rotation about a center axis for the rod of the link.

公开(公告)号：US20190078533A1

公开(公告)日：2019-03-14

申请号：US15700042

申请日：2017-09-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Alex J. Simpson ,  Robert T. Knowlton

IPC: F02K1/06

Abstract: Disclosed is a linkage assembly for a gas turbine engine having a link having a first end, a second end, and a rod extending therebetween, the first end having a first sliding bearing disposed within a first sliding bearing housing, a fastener comprising a first flange and a second flange, a pin extending between the first flange and the second flange, wherein the first sliding bearing is pivotally connected to the pin; and a biasing member secured between the first flange and the sliding bearing housing, the biasing member contacting the sliding bearing housing and biasing the link against rotation about a center axis for the rod of the link.

公开(公告)号：US10100779B2

公开(公告)日：2018-10-16

申请号：US15095041

申请日：2016-04-09

Applicant: United Technologies Corporation

Inventor： Hannes A. Alholm ,  Joseph J. Czapski, Jr. ,  Bessem Jlidi ,  Alex J. Simpson

IPC: F02K1/12 ,  B23P15/00 ,  F16C23/04 ,  B64C15/00 ,  F02K1/15

Abstract: A drive link assembly includes a case having a spherically formed inner ring. A clevis is affixed to a surface of the case such that is disposed horizontally between a first end and a second end of the clevis. A spacer having a spherical inset portion is positioned on the surface horizontally between the clevis and the spherically formed inner ring, such that the spherical inset portion is aligned with the spherically formed inner ring. A spherical bearing is seated within the spherically formed inner ring. A rod is affixed to an outer surface of the spherical bearing.

公开(公告)号：US20160146040A1

公开(公告)日：2016-05-26

申请号：US14933497

申请日：2015-11-05

Applicant: United Technologies Corporation

Inventor： Alex J. Simpson ,  Bryan P. Dube ,  John E. Paul

IPC: F01D25/06 ,  F04D29/32 ,  F01D5/02 ,  F01D9/04

CPC classification number: F01D25/06 ,  F01D9/041 ,  F04D29/544 ,  F04D29/666 ,  F05D2260/961

Abstract: A vane assembly for a gas turbine engine may include a plurality of vanes being arranged in vane groupings symmetrically spaced circumferentially from each other. Each vane grouping may include at least a first and a second vane. The at least first and second vanes may be spaced from each other at a first pitch. Each vane grouping may be spaced from each other at a second pitch. The first pitch may be dissimilar from the second pitch.

Abstract translation: 用于燃气涡轮发动机的叶片组件可以包括多个叶片，其布置在叶片组中，彼此对称地间隔开。 每个叶片组可包括至少第一和第二叶片。 所述至少第一和第二叶片可以以第一间距彼此间隔开。 每个叶片组可以以第二间距彼此间隔开。 第一音调可能与第二音高不同。

公开(公告)号：US10598211B2

公开(公告)日：2020-03-24

申请号：US15161831

申请日：2016-05-23

Applicant: United Technologies Corporation

Inventor： Alex J. Simpson ,  Edward A. Krystowski

IPC: F16C11/04

Abstract: A bearing joint assembly may include a bearing sleeve, a first collar, a first mount, a pair of second mounts and a fastener, which projects through the bearing sleeve and secures the bearing sleeve to the second mounts. The bearing sleeve extends axially along a centerline and includes a spherical bearing. The first collar is configured with the bearing sleeve. A first annular channel is formed by and extends axially between the spherical bearing and the first collar. The first mount is mounted on and slidably engages the spherical bearing. The spherical bearing and the first collar are axially between the second mounts.

公开(公告)号：US10060535B2

公开(公告)日：2018-08-28

申请号：US15053696

申请日：2016-02-25

Applicant: United Technologies Corporation

Inventor： Alex J. Simpson ,  Christopher J. Peters ,  Zachary D. Ryan

IPC: F16J15/44 ,  F01D11/02 ,  F01D11/08 ,  F02C7/28 ,  F16J15/447

CPC classification number: F16J15/447 ,  F01D11/02 ,  F01D11/025 ,  F01D11/08 ,  F02C7/28 ,  F05D2240/55 ,  F05D2240/56 ,  F16J15/441 ,  F16J15/442 ,  F16J15/4472

Abstract: A non-contact seal assembly includes a plurality of seal shoes, a seal base and a plurality of spring elements. A first of the spring elements includes a first mount, a second mount and a spring beam. The spring beam extends a length longitudinally along a centerline from the first mount to the second mount. The spring beam includes opposing first and second surfaces. The first surface is disposed a first distance from the centerline, and the second surface is disposed a second distance from the centerline. The first distance and the second distance change as the spring beam extends longitudinally along the centerline to provide at least a portion of the spring beam with a tapered geometry. The portion of the spring beam has a longitudinal length that is at least about five percent of the length of the spring beam.

公开(公告)号：US09938854B2

公开(公告)日：2018-04-10

申请号：US14712067

申请日：2015-05-14

Applicant: United Technologies Corporation

Inventor： Alex J. Simpson ,  Timothy Charles Nash

IPC: F01D25/06 ,  F01D9/04 ,  F01D5/14 ,  F01D5/16 ,  F01D5/22 ,  F01D5/26 ,  F01D5/10 ,  F01D1/02 ,  F01D5/02

CPC classification number: F01D25/06 ,  F01D1/02 ,  F01D5/02 ,  F01D5/10 ,  F01D5/141 ,  F01D5/143 ,  F01D5/145 ,  F01D5/16 ,  F01D5/22 ,  F01D5/26 ,  F01D9/04 ,  F01D9/041 ,  F01D9/047 ,  F05D2220/32 ,  F05D2260/96 ,  Y02T50/673

Abstract: A gas turbine engine includes an array of airfoils. Each airfoil includes a first circumferentially extreme position. The first circumferentially extreme positions of the airfoils are circumferentially spaced apart from one another a pitch. Each airfoil includes a second circumferentially extreme position circumferentially spaced from the first circumferentially extreme position in an angular spacing that is at least one half the pitch.