公开(公告)号：US10323535B2

公开(公告)日：2019-06-18

申请号：US15102978

申请日：2014-11-19

Applicant: United Technologies Corporation

Inventor： Timothy M. Davis ,  Jose R. Paulino ,  Brian Duguay

IPC: F01D11/18 ,  F01D5/02 ,  F01D5/12

Abstract: A blade tip clearance system includes first and second control rings. The first control ring has a first coefficient of thermal expansion (CTE) and a first thermal response rate. The second control ring is located radially outward of and operatively connected to the first control ring and has a second CTE that is different from the first CTE and a second thermal response rate that is different from the first thermal response rate. Thermal expansion and contraction of the first and the second control rings controls a radial position of the blade tip clearance system relative to a rotating blade component.

公开(公告)号：US20180058239A1

公开(公告)日：2018-03-01

申请号：US15252942

申请日：2016-08-31

Applicant: United Technologies Corporation

Inventor： Jose R. Paulino ,  Conway Chuong ,  Joey Wong ,  Christopher J. Peters ,  Ross Wilson

IPC: F01D11/02 ,  F01D5/02 ,  F01D25/24 ,  F04D29/08 ,  F04D29/32 ,  F04D29/053 ,  F04D29/52

CPC classification number: F01D11/025 ,  F01D5/02 ,  F01D25/24 ,  F04D29/053 ,  F04D29/083 ,  F04D29/321 ,  F04D29/522 ,  F05D2220/32 ,  F05D2240/60 ,  F05D2260/38 ,  F16J15/442 ,  F16J15/445

Abstract: Aspects of the disclosure are directed to a floating, non-contact seal comprising: a shoe, and at least three beams, each beam having a first axial end and a second axial end, where the first axial ends are coupled to the shoe and the second axial ends are coupled to a ring structure. Aspects of the disclosure are directed to an engine comprising: a first structure, a second structure configured to rotate relative to the first structure, and a floating, non-contact seal that interfaces the first structure and the second structure, where the seal includes: a shoe, and at least three beams, where each beam has a first axial end and a second axial end, where the first axial ends are coupled to the shoe and the second axial ends are coupled to a ring structure.

公开(公告)号：US20170268678A1

公开(公告)日：2017-09-21

申请号：US15073224

申请日：2016-03-17

Applicant: United Technologies Corporation

Inventor： Paul M. Lutjen ,  Jose R. Paulino

IPC: F16J15/3288 ,  F01D11/00 ,  F01D11/08

CPC classification number: F16J15/3288 ,  F01D11/001 ,  F01D11/003 ,  F05D2220/32 ,  F05D2240/56 ,  F05D2250/18

Abstract: Aspects of the disclosure are directed to a brush seal comprising: a bristle pack that includes: a first plurality of bristles, each of the first plurality of bristles having a first dimension, and a second plurality of bristles, each of the second plurality of bristles having a second dimension that is different from the first dimension, where a ratio of the first dimension to the second dimension has a range of 2:1 to 5:1.

公开(公告)号：US11913343B2

公开(公告)日：2024-02-27

申请号：US16592001

申请日：2019-10-03

Applicant: United Technologies Corporation

Inventor： Jose R. Paulino ,  Veronika Reynolds ,  Jason David Liles

IPC: F01D21/00 ,  F01D11/12 ,  B33Y80/00

CPC classification number: F01D21/003 ,  F01D11/122 ,  B33Y80/00 ,  F05D2230/80 ,  F05D2240/55 ,  F05D2250/141 ,  F05D2250/15 ,  F05D2250/283 ,  F05D2270/821

Abstract: A replaceable rotor blade tip clearance measurement device for a gas turbine engine, includes a threaded section along an axis and an integral abradable tip with an internal lattice geometry that extends from the threaded section along the axis.

公开(公告)号：US20210172527A1

公开(公告)日：2021-06-10

申请号：US16706183

申请日：2019-12-06

Applicant: United Technologies Corporation

Inventor： Jose R. Paulino ,  Neil L. Tatman ,  Paul J. Burgess

IPC: F16J15/3288

Abstract: A seal joint assembly is provided that includes a stationary seal carrier, a stationary seal land and a brush seal. The stationary seal land includes a seal land surface. The brush seal is mounted to the stationary seal carrier. The brush seal includes a first set of bristles and a second set of bristles. The first set of bristles includes a first bristle that contacts the seal land surface. The second set of bristles includes a second bristle that contacts the seal land surface. The second bristle crosses the first bristle.

公开(公告)号：US20210102474A1

公开(公告)日：2021-04-08

申请号：US16592001

申请日：2019-10-03

Applicant: United Technologies Corporation

Inventor： Jose R. Paulino ,  Veronika Reynolds ,  Jason David Liles

IPC: F01D21/00 ,  F01D11/12

Abstract: A replaceable rotor blade tip clearance measurement device for a gas turbine engine, includes a threaded section along an axis and an integral abradable tip with an internal lattice geometry that extends from the threaded section along the axis.

公开(公告)号：US10746049B2

公开(公告)日：2020-08-18

申请号：US15941041

申请日：2018-03-30

Applicant: United Technologies Corporation

Inventor： Jonathan Jeffery Eastwood ,  Adam Lee Hart ,  Brian Levy ,  Luis Miguel Ayalde ,  Brian Craig ,  Jose R. Paulino ,  Esref Yaylagan

IPC: F01D25/16 ,  F01D25/18 ,  F01D25/24 ,  F01D9/06

Abstract: An example case for a gas turbine engine includes a bearing compartment, a radially outer ring, and a radially inner ring. The radially outer ring and radially inner ring are connected by a plurality of circumferentially spaced apart struts and define an annular flow path therebetween. The radially inner ring includes a first flange that extends radially outward from the bearing compartment. The first flange includes an undulation that extends axially away from the plurality of struts, and defines a load path between the bearing compartment and the radially outer ring.

公开(公告)号：US20200256206A1

公开(公告)日：2020-08-13

申请号：US16270789

申请日：2019-02-08

Applicant: United Technologies Corporation

Inventor： Paul M. Lutjen ,  Christopher W. Strock ,  Jose R. Paulino

IPC: F01D11/12

Abstract: A component for a gas turbine engine includes a surface adjacent a flow of hot gases. A plurality of cavities is in a portion of the surface. The plurality of cavities have a first group of cavities with a first cross-section and a second group of cavities with a second cross-section different from the first cross-section. The first and second groups of cavities are arranged such that there is no straight line across the portion of the surface that does not intersect one of the plurality of cavities. A thermal barrier coating is over the surface and fills each of the plurality of cavities.

公开(公告)号：US20190316485A1

公开(公告)日：2019-10-17

申请号：US15950549

申请日：2018-04-11

Applicant: United Technologies Corporation

Inventor： Adam Lee Hart ,  Brian Levy ,  Luis Miguel Ayalde ,  Jose R. Paulino ,  Patrick Scheelk ,  Nicolas Bueno

IPC: F01D25/12 ,  F01D11/08

Abstract: A blade outer air seal (BOAS) for a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion; and a multitude of cooling fins disposed around the radially outer face of the seal body, at least one of the multitude of cooling fins having at least one aperture.

公开(公告)号：US10443425B2

公开(公告)日：2019-10-15

申请号：US15118521

申请日：2015-02-12

Applicant: United Technologies Corporation

Inventor： Dmitriy A. Romanov ,  Jose R. Paulino ,  Ken F. Blaney

IPC: F01D11/08 ,  B22C9/10 ,  B22C9/24 ,  F01D11/24

Abstract: A blade outer air seal according to an exemplary aspect of the present disclosure includes, among other things, a body to be distributed circumferentially about a blade array. The body has a plurality of grooves, which can, for example, improve the aerodynamic efficiency of a turbine. A fin is between a first groove and a second groove of the plurality of grooves. The fin extends radially from the body and terminates at a radially inner fin face that provides one or more cooling outlets.