公开(公告)号：EP3453901B1

公开(公告)日：2020-05-13

申请号：EP18182320.4

申请日：2018-07-06

Applicant: United Technologies Corporation

Inventor： SIMPSON, Alex J. ,  KNOWLTON, Robert T.

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

公开(公告)号：EP3453901A1

公开(公告)日：2019-03-13

申请号：EP18182320.4

申请日：2018-07-06

Applicant: United Technologies Corporation

Inventor： SIMPSON, Alex J. ,  KNOWLTON, Robert T.

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

Abstract: Disclosed is a linkage assembly for a gas turbine engine (20) having a link (102a-102d) having a first end (104a), a second end (104b), and a rod (106) extending therebetween, the first end having a first sliding bearing (108) disposed within a first sliding bearing housing (107), a fastener (118) comprising a first flange (126a) and a second flange (126b), a pin (120) extending between the first flange and the second flange, wherein the first sliding bearing is pivotally connected to the pin; and a biasing member (136a, 136b) 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：EP2948636B1

公开(公告)日：2019-03-06

申请号：EP14743391.6

申请日：2014-01-15

Applicant: United Technologies Corporation

Inventor： SIMPSON, Alex J. ,  NIEZELSKI, David A.

IPC: F01D5/18 ,  F02C7/12 ,  F01D5/14

公开(公告)号：EP2947269A1

公开(公告)日：2015-11-25

申请号：EP15168146.7

申请日：2015-05-19

Applicant: United Technologies Corporation

Inventor： SIMPSON, Alex J. ,  NASH, Timothy Charles

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

Abstract: A gas turbine engine includes an array (63) of airfoils (70). Each airfoil (70) includes a first circumferentially extreme position (88). The first circumferentially extreme positions (88) of the airfoils (70) are circumferentially spaced apart from one another a pitch (P). Each airfoil (70) includes a second circumferentially extreme position (90) circumferentially spaced from the first circumferentially extreme position (88) in an angular spacing that is at least one half the pitch (P).

Abstract translation: 燃气涡轮发动机包括翼型件（70）的阵列（63）。 每个翼片（70）包括第一周向极限位置（88）。 机翼（70）的第一周向极限位置（88）彼此间隔开间距（P）。 每个翼型件（70）包括与第一周向极限位置（88）周向间隔开的第二周向极限位置（90），其间距至少为间距（P）的一半。