公开(公告)号：US10400615B2

公开(公告)日：2019-09-03

申请号：US15070696

申请日：2016-03-15

Applicant: United Technologies Corporation

Inventor： Nicholas Waters Oren ,  Steven D. Porter

IPC: F01D9/02 ,  F01D5/02 ,  F02C3/04 ,  F01D5/06 ,  F01D5/30

Abstract: A disc of a gas turbine engine system with particular retaining ring placement and engagement implementation are provided. For example, the disc includes a disc bore including, a groove formed on an axially extending surface of the disc bore, wherein the groove includes a forward surface that extends radially into the disc bore to a groove floor that is cut into the disc bore, and wherein the groove extends axially to an aft surface that extends radially outward to at least the axially extending surface of the disc bore, and a disc web that extends radially outward from the disc bore, relative to an axis of rotation of the gas turbine engine.

公开(公告)号：US20190257248A1

公开(公告)日：2019-08-22

申请号：US15902171

申请日：2018-02-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Steven D. Porter

IPC: F02C7/18

Abstract: A heat shield panel for use in a gas turbine engine combustor is disclosed. In various embodiments, the heat shield panel includes a hot side, a cold side spaced from the hot side, a rail member disposed on the cold side proximate an outer perimeter, the rail member having an outer wall and an inner wall and an orifice extending through the rail member, from the inner wall to the outer wall, the orifice having an entrance portion having an entrance opening positioned on the inner wall and extending at least to an intermediate portion of the rail member and an exit portion having an exit opening positioned on the outer wall and extending at least to the intermediate portion of the rail member, the entrance portion of the orifice being angled relative to the exit portion of the orifice.

公开(公告)号：US10329929B2

公开(公告)日：2019-06-25

申请号：US15070703

申请日：2016-03-15

Applicant: United Technologies Corporation

Inventor： Nicholas Waters Oren ,  Steven D. Porter

IPC: F02C3/04 ,  F01D9/02 ,  F01D5/02 ,  F01D5/06 ,  F01D5/08 ,  F01D5/30

Abstract: A disc of a gas turbine engine system with particular retaining ring placement and engagement implementation are provided. For example, the disc includes a disc bore including, a groove formed on an axially extending surface of the disc bore, wherein the groove includes a forward surface that extends radially into the disc bore to a groove floor that is cut into the disc bore and extends axially to an aft surface that extends radially outward to at least the axially extending surface of the disc bore, and a scallop formed along at least one surface of the groove, wherein the scallop is configured to provide a flow path, and a disc web that extends radially outward from the disc bore, relative to an axis of rotation of the gas turbine engine.

公开(公告)号：US20190063750A1

公开(公告)日：2019-02-28

申请号：US15686344

申请日：2017-08-25

Applicant: United Technologies Corporation

Inventor： Steven D. Porter ,  John W. Mubeezi

IPC: F23R3/00 ,  B22C7/02

Abstract: According to one embodiment, a heat shield panel for a combustor of a gas turbine engine is provided. The heat shield comprising: a panel body having a first surface configured to be oriented toward a combustion zone of a combustor, and a second surface opposite the first surface, the second surface being configured to be oriented toward a combustor liner of the combustor; a plurality of first pin fins projecting from the second surface of the panel body, wherein each of the plurality of first pin fins has a rounded top opposite the second surface; and one or more second pin fins projecting from the second surface of the panel body, wherein each of the one or more second pin fins has a flat top opposite the second surface.

公开(公告)号：US20190063323A1

公开(公告)日：2019-02-28

申请号：US15690555

申请日：2017-08-30

Applicant: United Technologies Corporation

Inventor： Steven D. Porter ,  Shawn M. McMahon ,  Kevin Zacchera ,  Noah Wadsworth ,  Christopher Whitfield ,  Sean D. Bradshaw ,  Dennis M. Moura

IPC: F02C7/18 ,  F02C7/28 ,  F01D9/04 ,  F23R3/42

Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A combustor assembly and method are also disclosed.

公开(公告)号：US20190024896A1

公开(公告)日：2019-01-24

申请号：US15656742

申请日：2017-07-21

Applicant: United Technologies Corporation

Inventor： Steven D. Porter ,  Cara M. Redding

IPC: F23R3/14 ,  F23R3/28 ,  F23C7/00

CPC classification number: F23R3/14 ,  F23C7/004 ,  F23D2206/10 ,  F23R3/28 ,  F23R3/286

Abstract: A combustor for a gas turbine engine includes an annular combustor shell, the annular combustor shell defining a combustion chamber, and a fuel injector extending at least partially into the combustion chamber, and configured to deliver a flow of fuel and a flow of combustion air into the combustion chamber for combustion. The fuel injector includes a swirler with a swirler exit having a circumferential width along a circumferential axis greater than a radial width along a radial axis. A swirler for a gas turbine engine includes a swirler entrance and a swirler exit. The swirler exit has a circumferential width along a curvilinear circumferential axis greater than a radial width along a radial axis.

公开(公告)号：US10047623B2

公开(公告)日：2018-08-14

申请号：US14938447

申请日：2015-11-11

Applicant: United Technologies Corporation

Inventor： Jonathan Lemoine ,  Steven D. Porter

IPC: F01D11/00 ,  F16J15/44 ,  F16J15/16 ,  F16J15/56 ,  F16J9/12 ,  F02C7/28 ,  F01D9/06 ,  F01D25/16

Abstract: A compliant seal assembly that may be for an MTF of a gas turbine engine includes a housing orientated about an axis with a circumferentially extending groove in the housing opened radially outward. An annular carrier of the assembly is constructed and arranged to move radially within the groove, and includes a circumferentially extending channel that is opened radially outward for receipt of a piston ring that may seal to a surrounding cylindrical wall. In operation, the carrier moves radially with respect to the housing to compensate for radial displacement between the housing and the wall, and the piston ring moves axially along the wall to compensate for axial displacement between the housing and the wall.

公开(公告)号：US09982548B2

公开(公告)日：2018-05-29

申请号：US14890496

申请日：2014-06-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John T. Ols ,  Karl A. Mentz ,  Richard N. Allen ,  Steven D. Porter ,  Renee J. Jurek ,  Paul K. Sanchez ,  Sandra S. Pinero

IPC: F01D9/04 ,  F01D5/14 ,  F01D5/02 ,  F01D25/24

CPC classification number: F01D9/041 ,  F01D5/02 ,  F01D5/143 ,  F01D9/04 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2240/80 ,  F05D2250/71 ,  F05D2250/90 ,  Y02T50/673

Abstract: An airfoil extends between radially inner and radially outer platforms. The airfoil extends between a leading edge and a trailing edge, and merges into facing surfaces of the radially inner and outer platforms. A variable fillet merges a facing surface of one of the radially inner and outer platforms into a wall of the airfoil. The variable fillet has a length extending away from a surface of the airfoil and a height extending away from the facing surface of at least one of the radially inner and outer platforms outwardly on to the airfoil. The variable fillet has a greater length at one of the leading edge and the trailing edge. A spaced portion has a shorter length at locations spaced from at least one of the leading and trailing edges. A mid-turbine frame and a gas turbine engine are also disclosed.

公开(公告)号：US20180128119A1

公开(公告)日：2018-05-10

申请号：US15343965

申请日：2016-11-04

Applicant: United Technologies Corporation

Inventor： Raymond S Hummel ,  Steven D. Porter ,  Julian Partyka

IPC: F01D9/02

CPC classification number: F01D9/02 ,  F01D5/027 ,  F01D5/3015 ,  F01D25/04 ,  F04D29/662 ,  F05B2260/966 ,  F05D2220/32 ,  F05D2260/941 ,  F05D2260/96 ,  G01M1/32 ,  G01M1/36

Abstract: A minidisk for a rotor system may comprise a balance flange defining a hole array, which may include a first hole having a first width. The first hole may be configured to receive a balance weight. A second hole and a third hole may have a second width. The second hole and the third hole may be disposed adjacent to the first hole. The second width may be greater than the first width.

公开(公告)号：US20180087402A1

公开(公告)日：2018-03-29

申请号：US15806370

申请日：2017-11-08

Applicant: United Technologies Corporation

Inventor： Joshua Daniel Winn ,  Anthony P. Cherolis ,  Steven D. Porter ,  Christopher Treat ,  Kevin Zacchera

IPC: F01D25/14 ,  F01D25/28

CPC classification number: F01D25/145 ,  F01D9/065 ,  F01D25/12 ,  F01D25/162 ,  F01D25/24 ,  F01D25/243 ,  F01D25/28 ,  F05D2260/20 ,  Y02T50/672 ,  Y02T50/676

Abstract: A mid-turbine frame for a gas turbine engine according to an example of the present disclosure includes, among other things, a first frame case, a flange coupled to the first frame case, and a heat shield adjacent to the flange. A method of cooling a portion of a gas turbine engine is also disclosed.