公开(公告)号：US10428684B2

公开(公告)日：2019-10-01

申请号：US15107591

申请日：2015-01-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas J. Robertson, Jr.

IPC: F01D9/04 ,  F01D25/00 ,  B29C70/68 ,  B33Y80/00 ,  B33Y30/00 ,  F01D5/14 ,  F01D17/16 ,  B22F3/105 ,  B22F7/08 ,  B33Y10/00 ,  B22F5/04 ,  B29C45/14 ,  B29K705/00 ,  B29L31/08

Abstract: A component for a gas turbine engine comprises an airfoil body formed of a plastic. A reinforcement portion has webs formed of a metallic material and extend into the airfoil. A gas turbine engine, and a method of forming a component for use in a gas turbine engine are also disclosed.

公开(公告)号：US10221718B2

公开(公告)日：2019-03-05

申请号：US14914840

申请日：2014-08-15

Applicant: United Technologies Corporation

Inventor： Steven C. Clarkson ,  Thomas J. Robertson, Jr. ,  Michael Parkin

IPC: F01D25/00 ,  F01D11/08 ,  F01D21/04 ,  F01D25/24 ,  F02K3/06 ,  F02C7/20

Abstract: A turbine engine fan case (48) comprises a composite body member (300) circumscribing an axis (500) and having an annular mounting portion (310, 410), a segmented polymer member (320, 330, 420, 440) along the annular mounting portion, and integrated therewith.

公开(公告)号：US09915168B2

公开(公告)日：2018-03-13

申请号：US14728779

申请日：2015-06-02

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas J. Robertson, Jr. ,  Steven Clarkson

IPC: F01D21/04 ,  F01D25/00 ,  F01D25/24 ,  F02C7/05

CPC classification number: F01D25/005 ,  F01D21/045 ,  F01D25/24 ,  F02C7/05 ,  F05D2240/14 ,  F05D2300/603 ,  Y02T50/672

Abstract: A turbofan engine has a fan having a circumferential array of fan blades. A fan case encircles the fan. There is at least one compressor section, a combustor, and at least one turbine section. The fan case comprises a containment case and a cartridge liner carried therein. A ballistic liner encircles at least a portion of the cartridge liner and is attached thereto.

公开(公告)号：US09909458B2

公开(公告)日：2018-03-06

申请号：US14613755

申请日：2015-02-04

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas J. Robertson, Jr. ,  Mark W. Costa ,  Steven Clarkson

IPC: F01B25/26 ,  F01D25/28 ,  F01D25/24 ,  G01D11/30

CPC classification number: F01D25/28 ,  F01D25/24 ,  F05D2230/60 ,  F05D2240/90 ,  F05D2300/121 ,  F05D2300/603 ,  G01D11/30 ,  Y02T50/672

Abstract: A method for installing a mounting hole through a wall of a fan case of a gas turbine engine is disclosed. The method may comprise: 1) installing a pilot hole through the wall of the fan case at an angle perpendicular to an outer surface of the wall, 2) inserting a boss through the pilot hole, 3) bonding the boss to the wall of the fan case, and 4) installing the mounting hole through the boss at an off-axis angle with respect to the angle perpendicular to the outer surface of the wall.