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1
US2020141578A1
COWL INTEGRATION TO COMBUSTOR WALL
Publication/Patent Number: US2020141578A1 Publication Date: 2020-05-07 Application Number: 16/180,388 Filing Date: 2018-11-05 Inventor: Sauer, Kevin   Dailey, Lewis   Mccormick, Keith   Assignee: Rolls-Royce Corporation   IPC: F23R3/00 Abstract: A combustion section of a gas turbine engine may include a cassette configured to couple to an annular combustor dome arranged around a flow path for the gas turbine engine. The annular combustor dome may include a dome wall comprising a plurality of inlets configured to receive compressed air for a combustion chamber located downstream, relative to the flow path, from the annular combustor dome. The cassette may include a combustor wall extended away from the dome wall in a downstream direction. The cassette may further include a cowl integral to the combustor wall. At least a portion of the cowl may extend away from the dome wall in an upstream direction relative to the flow path. The cowl may receive compressed air from a diffusor and guide the compressed air to a space upstream from the inlets, relative to the flow path.
2
US10619856B2
Notched gas turbine combustor cowl
Publication/Patent Number: US10619856B2 Publication Date: 2020-04-14 Application Number: 15/809,835 Filing Date: 2017-11-10 Inventor: Mccormick, Keith Alan   Denman, Paul Ashley   Assignee: Rolls-Royce Corporation   IPC: F23R3/04 Abstract: A gas turbine engine includes a combustion system. The combustion system may include a combustor positioned in a chamber created by an outer wall. A compressor, such as a centrifugal compressor may provide a flow of compressed air into the chamber along an inner surface of the outer wall since an inlet for the flow of compressed air is outboard of the combustor. The pressurized flow of air may be redirected by a cowl included in the chamber. The cowl may include a collar defining a notch in the cowl. The collar may redirect the flow of pressurized air so as to minimize a high velocity component of the flow of pressurized air flowing radially toward a central axis of the engine prior to entering a head of a fuel nozzle included in the combustion system.
3
EP3647661A1
COMBUSTOR DOME VIA ADDITIVE LAYER MANUFACTURING
Publication/Patent Number: EP3647661A1 Publication Date: 2020-05-06 Application Number: 19202152.5 Filing Date: 2019-10-09 Inventor: Sauer, Kevin   Dailey, Lewis   Mccormick, Keith   Smith, Duane   Debruhl, Christopher   Assignee: Rolls-Royce Corporation   Rolls-Royce North American Technologies, Inc.   IPC: F23R3/10 Abstract: A combustor dome (102) may be formed by way of additive layer manufacturing. The combustor dome (102) may further include a raised outer surface (604) and a recessed outer surface (606) on a hot axial side (106) of the combustor dome (102). The recessed outer surfaces (606) may be closer to a cold axial side (104) than the raised outer surfaces (604). The combustor dome (102) may include a shadow surface (608) defined between the raised outer surface (604) and recessed outer surface (606). The shadow surface (608) may define a corresponding cooling outlet (402) in fluid communication with an internal cooling channel (502) defined inside of the combustor dome (102). The cooling outlet (402) may release air from the internal cooling channel (502) to the hot axial side (106) of the combustor dome (102).
4
US10634352B2
Gas turbine engine afterburner
Publication/Patent Number: US10634352B2 Publication Date: 2020-04-28 Application Number: 15/663,203 Filing Date: 2017-07-28 Inventor: Mccormick, Keith A.   Roesler, Timothy C.   Verdouw, Albert J.   Assignee: Rolls-Royce North American Technologies Inc.   IPC: F23R3/20 Abstract: An afterburner for use with a gas turbine engine includes a plurality of vanes distributed downstream of a turbine of the gas turbine engine. The vanes can include one or more exit apertures through which hot combustion flow from a pilot can be injected. The exit apertures can be protrusions or slots in some forms. In some embodiments, cooling passages are arranged around the exit apertures. An upstream vane portion can be positioned to inject fuel to be combusted via interaction with hot flow that is discharged through the exit apertures.
5
US2020141579A1
COMBUSTOR DOME VIA ADDITIVE LAYER MANUFACTURING
Publication/Patent Number: US2020141579A1 Publication Date: 2020-05-07 Application Number: 16/180,529 Filing Date: 2018-11-05 Inventor: Sauer, Kevin   Dailey, Lewis   Mccormick, Keith   Smith, Duane   Debruhl, Christopher D.   Assignee: Rolls-Royce Corporation   Rolls-Royce North American Technologies Inc.   IPC: F23R3/00 Abstract: A combustor dome may be formed by way of additive layer manufacturing. The combustor dome may further include a raised outer surface and a recessed outer surface on a hot side of the combustor dome. The recessed outer surfaces may be closer to the cold side than the raised outer surfaces. The combustor dome may include a shadow surface defined between the raised outer surface and recessed outer surface. The shadow surface may define a corresponding cooling outlet in fluid communication with an internal cooling channel defined inside of the combustor dome. The cooling outlet may release air from the internal cooling channel to the hot axial side of the combustor dome.
6
US10311456B2
Dispensation delay prediction systems and methods
Publication/Patent Number: US10311456B2 Publication Date: 2019-06-04 Application Number: 15/801,180 Filing Date: 2017-11-01 Inventor: Mccormick, Keith Dean   Assignee: Quick Bites, Inc.   IPC: G06Q30/02 Abstract: Provided herein are systems and methods relating to prediction in a context of first and second client devices related to a provider facility (a drive-through that sells comestible goods, e.g.) wherein the first client device is aboard a first vehicle and predictive data relating to the first client device is improved by retaining data relating to the second client device (having visited the provider facility on a prior same-type day, e.g.).
7
US2018204231A1
DISPENSATION DELAY PREDICTION SYSTEMS AND METHODS
Publication/Patent Number: US2018204231A1 Publication Date: 2018-07-19 Application Number: 15/801,180 Filing Date: 2017-11-01 Inventor: Mccormick, Keith Dean   Assignee: Quick Bites, Inc.   IPC: G06Q10/06 Abstract: Provided herein are systems and methods relating to prediction in a context of first and second client devices related to a provider facility (a drive-through that sells comestible goods, e.g.) wherein the first client device is aboard a first vehicle and predictive data relating to the first client device is improved by retaining data relating to the second client device (having visited the provider facility on a prior same-type day, e.g.).
8
EP3376111A1
Combustor cowl
Publication/Patent Number: EP3376111A1 Publication Date: 2018-09-19 Application Number: 18157528.3 Filing Date: 2018-02-20 Inventor: Mccormick, Keith   Denman, Paul   Assignee: Rolls-Royce Corporation   IPC: F23R3/50 Abstract: A gas turbine engine includes a combustion system (200). The combustion system includes a combustor positioned in a chamber created by an outer wall. A compressor, such as a centrifugal compressor provides a flow of compressed air into the chamber along an inner surface of the outer wall since an inlet for the flow of compressed air is outboard of the combustor. The pressurized flow of air may is redirected by a cowl (552) included in the chamber. The cowl ncludes a collar (516) defining a notch (504) in the cowl. The collar redirects the flow of pressurized air so as to minimize a high velocity component of the flow of pressurized air flowing radially toward a central axis of the engine prior to entering a head (226) of a fuel nozzle (224) included in the combustion system.
9
US2018259186A1
Chamber Fed Combustor Cowl
Publication/Patent Number: US2018259186A1 Publication Date: 2018-09-13 Application Number: 15/809,835 Filing Date: 2017-11-10 Inventor: Mccormick, Keith Alan   Denman, Paul Ashley   Assignee: Rolls-Royce Corporation   IPC: F23R3/28 Abstract: A gas turbine engine includes a combustion system. The combustion system may include a combustor positioned in a chamber created by an outer wall. A compressor, such as a centrifugal compressor may provide a flow of compressed air into the chamber along an inner surface of the outer wall since an inlet for the flow of compressed air is outboard of the combustor. The pressurized flow of air may be redirected by a cowl included in the chamber. The cowl may include a collar defining a notch in the cowl. The collar may redirect the flow of pressurized air so as to minimize a high velocity component of the flow of pressurized air flowing radially toward a central axis of the engine prior to entering a head of a fuel nozzle included in the combustion system.
10
CA2992342A1
CHAMBER FED COMBUSTOR COWL
Publication/Patent Number: CA2992342A1 Publication Date: 2018-09-13 Application Number: 2992342 Filing Date: 2018-01-18 Inventor: Denman, Paul Ashley   Mccormick, Keith Alan   Assignee: ROLLS-ROYCE CORPORATION   IPC: F23R3/02 Abstract: A gas turbine engine includes a combustion system. The combustion system may include a combustor positioned in a chamber created by an outer wall. A compressor, such as a centrifugal compressor may provide a flow of compressed air into the chamber along an inner surface of the outer wall since an inlet for the flow of compressed air is outboard of the combustor. The pressurized flow of air may be redirected by a cowl included in the chamber. The cowl may include a collar defining a notch in the cowl. The collar may redirect the flow of pressurized air so as to minimize a high velocity component of the flow of pressurized air flowing radially toward a central axis of the engine prior to entering a head of a fuel nozzle included in the combustion system.
11
US9756686B2
Method of crosstalk reduction for multi-zone induction heating systems
Publication/Patent Number: US9756686B2 Publication Date: 2017-09-05 Application Number: 12/964,963 Filing Date: 2010-12-10 Inventor: Dohmeier, Nicholas   Mccormick, Keith   Assignee: Honeywell ASCa, Inc.   IPC: H05B6/06 Abstract: Reduction of crosstalk between induction heating coils in an induction heating apparatus and particularly to reduction of crosstalk in a multi-zone induction heating system provides greater reliability for the power modules.
12
US2017343215A1
GAS TURBINE ENGINE AFTERBURNER
Publication/Patent Number: US2017343215A1 Publication Date: 2017-11-30 Application Number: 15/663,203 Filing Date: 2017-07-28 Inventor: Mccormick, Keith A.   Roesler, Timothy C.   Verdouw, Albert J.   Assignee: Rolls-Royce North American Technologies Inc.   IPC: F23R3/20 Abstract: An afterburner for use with a gas turbine engine includes a plurality of vanes distributed downstream of a turbine of the gas turbine engine. The vanes can include one or more exit apertures through which hot combustion flow from a pilot can be injected. The exit apertures can be protrusions or slots in some forms. In some embodiments, cooling passages are arranged around the exit apertures. An upstream vane portion can be positioned to inject fuel to be combusted via interaction with hot flow that is discharged through the exit apertures.
13
EP2357413B1
Dry low NOx combustion system with means for eliminating combustion noise
Publication/Patent Number: EP2357413B1 Publication Date: 2017-05-03 Application Number: 10014578.8 Filing Date: 2003-03-06 Inventor: Verdouw, Albert J.   Smith, Duane   Mccormick, Keith   Razdan, Mohan K.   Assignee: Rolls-Royce Corporation   IPC: F23R3/28 Abstract: A combustor comprises a mechanical housing and a combustion chamber disposed within the mechanical housing and having a first end and a second end and an internal volume. A premixer is coupled to the first end of the combustion chamber and in flow communication with the internal volume. The premixer includes a swirler that delivers a swirling flow of fuel and a gas to the internal volume through the first end. A dome is positioned at the first end of the combustion chamber and extends into the internal volume. The dome has an outer surface contoured to minimize flow separation of the swirling flow of fuel and the gas passing from the premixer and into the combustion chamber.
14
EP2514267B1
METHOD OF CROSSTALK REDUCTION FOR MULTI-ZONE INDUCTION HEATING SYSTEMS
Publication/Patent Number: EP2514267B1 Publication Date: 2015-10-28 Application Number: 10836898.6 Filing Date: 2010-12-16 Inventor: Dohmeier, Nicholas   Mccormick, Keith   Assignee: Honeywell Asca, Inc.   IPC: H05B6/06
15
EP2514267A4
METHOD OF CROSSTALK REDUCTION FOR MULTI-ZONE INDUCTION HEATING SYSTEMS
Publication/Patent Number: EP2514267A4 Publication Date: 2015-01-07 Application Number: 10836898 Filing Date: 2010-12-16 Inventor: Dohmeier, Nicholas   Mccormick, Keith   Assignee: Honeywell Asca, Inc.   IPC: H05B6/06
16
US2015121886A1
GAS TURBINE ENGINE AFTERBURNER
Publication/Patent Number: US2015121886A1 Publication Date: 2015-05-07 Application Number: 14/196,857 Filing Date: 2014-03-04 Inventor: Mccormick, Keith A.   Roesler, Timothy C.   Verdouw, Albert J.   Assignee: Rolls-Royce North American Technologies, Inc.   IPC: F23R3/20 Abstract: An afterburner is disclosed for use with a gas turbine engine and, in one form, is structured to receive a bypass air. The afterburner can be situated in a bypass duct and can be a toroidal combustor or a can combustor. In one embodiment, the afterburner includes a combustor arranged to receive bypass air and a plurality of vanes distributed downstream of a turbine of the gas turbine engine. The vanes can include one or more exit apertures through which hot combustion flow from the afterburner combustor can be injected. The exit apertures can be protrusions or slots in some forms. In one embodiment, a cooling passage is arranged around the exit apertures. An upstream vane portion can be positioned to inject fuel to be combusted via interaction with hot flow that is discharged through the exit apertures.
17
EP2514267A1
METHOD OF CROSSTALK REDUCTION FOR MULTI-ZONE INDUCTION HEATING SYSTEMS
Publication/Patent Number: EP2514267A1 Publication Date: 2012-10-24 Application Number: 10836898.6 Filing Date: 2010-12-16 Inventor: Dohmeier, Nicholas   Mccormick, Keith   Assignee: Honeywell Asca, Inc.   IPC: H05B6/08
18
EP2406429A2
SYSTEM AND METHOD FOR REDUCING CROSSTALK BETWEEN WORKCOILS IN INDUCTION HEATING APPLICATIONS
Publication/Patent Number: EP2406429A2 Publication Date: 2012-01-18 Application Number: 10738983.5 Filing Date: 2010-01-28 Inventor: Chirico, Salvatore   Dohmeier, Nicholas   Mccormick, Keith   Assignee: Honeywell International Inc.   IPC: D21F3/08
19
EP2406429A4
SYSTEM AND METHOD FOR REDUCING CROSSTALK BETWEEN WORKCOILS IN INDUCTION HEATING APPLICATIONS
Publication/Patent Number: EP2406429A4 Publication Date: 2012-11-21 Application Number: 10738983 Filing Date: 2010-01-28 Inventor: Chirico, Salvatore   Mccormick, Keith   Dohmeier, Nicholas   Assignee: Honeywell International Inc.   IPC: D21F3/08
20
EP1488086B1
DRY LOW COMBUSTION SYSTEM WITH MEANS FOR ELIMINATING COMBUSTION NOISE
Publication/Patent Number: EP1488086B1 Publication Date: 2012-11-28 Application Number: 03711450.1 Filing Date: 2003-03-06 Inventor: Verdouw, Albert J.   Smith, Duane   Mccormick, Keith   Razdan, Mohan K.   Assignee: Rolls-Royce Corporation   IPC: F23R3/28