公开(公告)号：US20200157959A1

公开(公告)日：2020-05-21

申请号：US16195925

申请日：2018-11-20

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Steven D. Porter ,  Caroline Karanian

IPC: F01D11/00 ,  F01D9/02 ,  F23R3/00

Abstract: A gas turbine engine includes a combustor disposed about an engine central axis and a circumferential row of vanes adjacent an exit region of the combustor. The combustor includes a combustor wall and a combustion chamber. The combustor wall has a lip at the exit region. Each vane includes a platform and an airfoil section extending from the platform. The forward edges of the platforms are adjacent the lip of the combustor wall. The lip defines a first annular slot and the forward edges of the vanes collectively define a second annular slot. The first and second annular slots together define an annular seal slot. An annular feather seal is entrapped in the annular seal slot between the combustor wall and the platform.

公开(公告)号：US10570766B2

公开(公告)日：2020-02-25

申请号：US16033746

申请日：2018-07-12

Applicant: United Technologies Corporation

Inventor： Jonathan Lemoine ,  Steven D. Porter

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

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：US10563626B2

公开(公告)日：2020-02-18

申请号：US16020021

申请日：2018-06-27

Applicant: United Technologies Corporation

Inventor： Steven D. Porter ,  Jon E. Sobanski

IPC: F02M27/04 ,  F02B51/04 ,  F23D11/32 ,  F02B23/10 ,  F23C99/00 ,  F23D11/24 ,  F02M39/00

Abstract: A method of controlling fuel injection into a combustor of a gas turbine engine including: applying a first electrical charge to fuel such that the fuel becomes a charged fuel; and applying a second electrical charge to a component of the combustor, wherein the first electrical charge is applied to the fuel at a first frequency and the second electrical charge is applied to the component at a second frequency such that at least one of a selected tone, a selected screech, and a selected noise is produced by spraying the charged fuel through the component and into a combustion chamber of the combustor from a fuel nozzle.

公开(公告)号：US20200025210A1

公开(公告)日：2020-01-23

申请号：US14997864

申请日：2016-01-18

Applicant: United Technologies Corporation

Inventor： Steven D. Porter ,  Julian Partyka

IPC: F04D29/32 ,  F01D5/02 ,  F01D5/06 ,  F01D5/08 ,  F01D25/08

Abstract: According to one embodiment, a mini-disk of a gas turbine engine having an axis is provided. The mini-disk includes a bore, a web extending radially with respect to the axis of the gas turbine engine from the bore, a base extending axially with respect to the axis of the gas turbine engine from the bore, a connector located on an end of the base, the connector configured to connect with a hub arm of the gas turbine engine, and an expansion feature configured in the base and located between the bore and the connector, the expansion feature configured to reduce an axial stiffness of the base.

公开(公告)号：US10539029B2

公开(公告)日：2020-01-21

申请号：US15070789

申请日：2016-03-15

Applicant: United Technologies Corporation

Inventor： Nicholas Waters Oren ,  Steven D. Porter

IPC: F01D9/02 ,  F01D25/24 ,  F02C3/04

Abstract: According to one or more embodiments, a cover plate for a gas turbine engine is provided. The cover plate includes a cover plate body that extends from a disc blade attachment radially along an outside surface of a disc web to a disc bore of a disc creating a cavity between the cover plate body and the disc web of the disc, and an attachment protrusion extending from the inner most end of the cover plate body toward the disc bore, and wherein the attachment protrusion is configured to engage with a retention ring.

公开(公告)号：US20190249873A1

公开(公告)日：2019-08-15

申请号：US15893324

申请日：2018-02-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Steven D. Porter ,  James Tilsley Auxier

IPC: F23R3/00 ,  F23R3/06

CPC classification number: F23R3/002 ,  F05D2260/231 ,  F23R3/06 ,  F23R3/50 ,  F23R3/60 ,  F23R2900/00005 ,  F23R2900/00017 ,  F23R2900/03041 ,  F23R2900/03044 ,  F23R2900/03045

Abstract: A heat shield panel for use in a gas turbine engine combustor is disclosed. The heat shield panel includes a hot side, a cold side and at least one attachment mechanism having a stud and a central axis extending through the stud and a plurality of standoff pins positioned circumferentially around the stud, the standoff pins having a radial extent, a circumferential extent that is greater than the radial extent, a radially outer surface having a radially convex shape and a radially inner surface having a radially concave shape.

公开(公告)号：US20190242580A1

公开(公告)日：2019-08-08

申请号：US15889793

申请日：2018-02-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Steven D. Porter ,  Jon E. Sobanski

IPC: F23R3/16 ,  F23R3/60 ,  F23R3/00

CPC classification number: F23R3/002 ,  F01D5/187 ,  F01D9/065 ,  F23M5/04 ,  F23R3/50 ,  F23R3/60 ,  F23R2900/00012 ,  F23R2900/00017 ,  F23R2900/00018 ,  F23R2900/03043 ,  F23R2900/03044

Abstract: A heat shield panel for a gas turbine engine combustor is disclosed. The heat shield panel includes a hot side defining a first surface having an outer perimeter, a cold side defining a second surface spaced from the first surface, a rail member disposed on the cold side proximate a first portion of the outer perimeter, the rail member having an outer wall and an inner wall, an undercut portion within the second surface proximate the inner wall of the rail member and an orifice extending through the rail member, from the inner wall to the outer wall.

公开(公告)号：US10371010B2

公开(公告)日：2019-08-06

申请号：US14598574

申请日：2015-01-16

Applicant: United Technologies Corporation

Inventor： Jorge I. Farah ,  Steven D. Porter ,  Paul K. Sanchez ,  Joseph J. Sedor

IPC: F01D25/28 ,  F01D9/06 ,  F01D25/16 ,  F02C7/20

Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case that includes a bolt opening and at least one spoke for connecting an outer frame case to the inner frame case that includes an inlet passage that extends in a radial direction. A central bolt extends through the bolt opening for securing at least one spoke to the inner frame case.

公开(公告)号：US10344603B2

公开(公告)日：2019-07-09

申请号：US14907003

申请日：2014-06-19

Applicant: United Technologies Corporation

Inventor： John T. Ols ,  Steven D. Porter

IPC: F01D9/04 ,  F01D11/00 ,  F01D11/02 ,  F01D25/16

Abstract: A vane pack for a gas turbine engine includes an annular arrangement of vanes. A ring is secured around the vanes and extends proud of an axial end of the vanes.

公开(公告)号：US10161256B2

公开(公告)日：2018-12-25

申请号：US14603033

申请日：2015-01-22

Applicant: United Technologies Corporation

Inventor： Steven D. Porter ,  Seth A. Max

IPC: F01D11/00 ,  F01D25/12 ,  F01D25/16 ,  F02C7/08 ,  F16J15/08 ,  F02C7/28

Abstract: A sealing arrangement has a turbine static structure with contact surfaces, a bearing compartment with contact surfaces, and a cavity between the turbine static structure and the bearing compartment. There are also two seals, wherein each seal is configured to contact the turbine static structure and the bearing compartment.