公开(公告)号：US20200063564A1

公开(公告)日：2020-02-27

申请号：US16108763

申请日：2018-08-22

Applicant: United Technologies Corporation

Inventor： Neil L. Tatman ,  Nathan K. Galle ,  Richard K. Hayford

IPC: F01D5/08 ,  F01D5/10

Abstract: A turbulent air reducer assembly for a gas turbine engine includes a windage cover attached to a first standoff and a second standoff, the windage cover tuned to a particular vibration response. A method of managing air within a turbine of a gas turbine engine includes reducing turbulence from a multiple of recesses within a tangential on-board injector with a turbulent air reducer assembly within each of the multiple of recesses, the turbulent air reducer assembly tuned to a particular vibration response from a turbine rotor.

公开(公告)号：US10408080B2

公开(公告)日：2019-09-10

申请号：US15023593

申请日：2014-10-06

Applicant: United Technologies Corporation

Inventor： Philip R. Rioux ,  Neil L. Tatman

IPC: F01D11/18 ,  F01D25/24

Abstract: A clearance control ring for a clearance control system of a gas turbine engine includes a contoured radial outer portion that defines a multiple of fins and a multiple of slots. A clearance control system of a gas turbine engine includes a clearance control ring with a radial inner portion from which a contoured radial outer portion extends. The contoured radial outer portion defines a multiple of fins and a multiple of slots. A blade outer air seal assembly with a clearance control ring land which receives the radial inner portion. A method of controlling a radial tip clearance within a gas turbine engine includes tailoring a multiple of fins and a multiple of slots of a clearance control ring for both steady state and transient clearance operations.

公开(公告)号：US10184354B2

公开(公告)日：2019-01-22

申请号：US14787320

申请日：2014-05-30

Applicant: United Technologies Corporation

Inventor： Philip Robert Rioux ,  Nicholas R. Leslie ,  Neil L. Tatman

IPC: F01D25/14 ,  F01D25/24 ,  F01D17/10 ,  F04D19/00 ,  F02C7/24 ,  F02C6/08

Abstract: A heat shield includes a first end configured to connect to an inner engine case at an inner connecting point, and a second end configured to connect to an outer engine case at an outer connecting point. The heat shield also includes a bulge extending in an aft direction from a radially upstream portion. A compressor section and a gas turbine engine including the heat shield are also disclosed.

公开(公告)号：US10132187B2

公开(公告)日：2018-11-20

申请号：US14910341

申请日：2014-08-07

Applicant: United Technologies Corporation

Inventor： Neil L. Tatman ,  Philip Robert Rioux

IPC: F01D11/16 ,  F01D25/24 ,  F01D11/18

Abstract: A clearance control assembly for a gas turbine engine includes a clearance control ring to position a blade outer air seal assembly radially relative to a blade tip. The clearance control ring is compression fit to the blade outer air seal assembly.

公开(公告)号：US09896955B2

公开(公告)日：2018-02-20

申请号：US14685416

申请日：2015-04-13

Applicant: United Technologies Corporation

Inventor： Neil L. Tatman ,  Jose R. Paulino

IPC: F01D11/00 ,  F01D25/24 ,  F16J15/02 ,  F01D11/08

CPC classification number: F01D11/005 ,  F01D11/08 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/12 ,  F05D2240/56 ,  F16J15/025

Abstract: A brush seal is provided. The brush seal may comprise an annular backing plate and a first bristle pack coupled to the annular backing plate. The first bristle pack may be oriented in an axial direction. A second bristle pack may be coupled to the first bristle pack and oriented in the axial direction. A bristle of the first bristle pack may have a greater diameter than a bristle of the second bristle pack. A retention structure may be coupled to the second bristle pack.

公开(公告)号：US20160123187A1

公开(公告)日：2016-05-05

申请号：US14893801

申请日：2014-06-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Nicholas R. Leslie ,  Neil L. Tatman

IPC: F01D25/14 ,  F01D25/26 ,  F01D11/08

CPC classification number: F01D25/145 ,  F01D11/08 ,  F01D25/08 ,  F01D25/26 ,  F05D2220/32 ,  F05D2240/15 ,  F05D2260/231 ,  Y02T50/675

Abstract: A heat shield assembly for a gas turbine engine includes a first heat shield segment defined about an axis and a second heat shield segment defined about the axis. A double circumferential lap joint is defined between the first heat shield segment and the second heat shield segment.

Abstract translation: 用于燃气涡轮发动机的隔热罩组件包括围绕轴线限定的第一隔热板段和围绕该轴限定的第二隔热板段。 在第一隔热片段和第二隔热片段之间限定双周向搭接接头。