公开(公告)号：US20240077030A1

公开(公告)日：2024-03-07

申请号：US17902307

申请日：2022-09-02

Applicant: Raytheon Technologies Corporation

Inventor： Lawrence A. Binek ,  Sean R. Jackson

IPC: F02C7/264 ,  F02C9/16

CPC classification number: F02C7/264 ,  F02C9/16

Abstract: An engine system is provided that includes a gas turbine engine and an actuation system. The gas turbine engine includes a compressor section, a combustor section, a turbine section and a flowpath extending through the compressor section, the combustor section and the turbine section. The actuation system includes a fluid reservoir, a flow regulator and a flow circuit. The flow regulator is configured as or otherwise includes a barrier between the fluid reservoir and the flow circuit. The flow regulator is configured to fluidly decouple the fluid reservoir from the flow circuit when the barrier is intact. The flow regulator is configured to fluidly couple the fluid reservoir with the flow circuit when the barrier breaks. The flow circuit is configured to direct gas from the fluid reservoir into the flowpath when the barrier breaks.

公开(公告)号：US11746712B2

公开(公告)日：2023-09-05

申请号：US16968584

申请日：2019-02-13

Applicant: Siemens Energy Global GmbH & Co. KG

Inventor： Vili Panov

IPC: F02C9/48 ,  F02C9/16 ,  F02C9/50 ,  F02C7/22

CPC classification number: F02C9/48 ,  F02C7/22 ,  F02C9/16 ,  F02C9/50 ,  F05D2240/35 ,  F05D2270/304 ,  F05D2270/3061

Abstract: A controller for a gas turbine, wherein the gas turbine includes the compressor arranged to operate at a rotational speed n, the combustor and the fuel supply including the first fuel supply and the second fuel supply, wherein the compressor is arranged to provide air to the combustor at a steady state air mass flow rate mss and wherein the fuel supply is arranged to supply fuel at a fuel mass flow rate mtotal to the combustor. The controller is arranged to, responsive to a load change ΔL to the load L, control the compressor to provide air to the combustor at a new air mass flow rate mTR, wherein the new air mass flow rate mTR is within a range between a first threshold mLBO and a second threshold mSUR.

公开(公告)号：US20230184176A1

公开(公告)日：2023-06-15

申请号：US17548779

申请日：2021-12-13

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Michel LABRECQUE ,  Kevin Nguyen ,  Ninad Joshi

IPC: F02C9/16 ,  F02C3/04

CPC classification number: F02C9/16 ,  F02C3/04 ,  F05D2220/30 ,  F05D2240/35 ,  F05D2270/051 ,  F05D2270/303 ,  F05D2270/3013

Abstract: A method and a system for synthesizing thrust from a turbofan engine are provided. The turbofan engine comprising a compressor section, a combustor, and a turbine section in serial fluid flow communication. The engine is operated and, during the operating of the turbofan engine, a pressure of fluid at an exit of the compressor section and a temperature of fluid at a location upstream of the exit of the compressor section are determined. A synthesized value of thrust from the turbofan engine is determined based on a product of at least a first factor and a second factor, the first factor being a function of the pressure and the second factor being a function of the temperature. The synthesized value of thrust from the turbofan engine is output.

公开(公告)号：US20230175410A1

公开(公告)日：2023-06-08

申请号：US17543475

申请日：2021-12-06

Applicant: Solar Turbines Incorporated

Inventor： Yong W. KIM ,  John F. LOCKYER ,  Raymond I. ALVAREZ

IPC: F02C9/16 ,  F02C3/04

CPC classification number: F02C9/16 ,  F02C3/04 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2240/24

Abstract: In the turbine of a gas turbine engine, disk cavities exist between rotor and stator assemblies. These disk cavities enable hot gas from the hot gas flow path to ingress between the rotor and stator assemblies with detrimental effects to the durability of the turbine. Thus, a flow discourager is disclosed that can be integrated into the platform of a stator assembly that is downstream from a rotor assembly. The flow discourager comprises a continuous external surface that defines a recirculation zone within a disk cavity that is aft to a rotor assembly to circulate the hot gas back out into the hot gas flow path.

公开(公告)号：US20230167809A1

公开(公告)日：2023-06-01

申请号：US18153721

申请日：2023-01-12

Applicant: DropTech, LLC

Inventor： Paul Kirch

IPC: F03G7/00 ,  F02C1/02 ,  F02C6/14 ,  F17D1/02 ,  F02C9/16

CPC classification number: F03G7/0252 ,  F03G7/027 ,  F02C1/02 ,  F02C6/14 ,  F17D1/02 ,  F02C9/16 ,  H02P9/02

Abstract: A system includes a generator using a fluid mixture obtained via a generator inlet, a compressor having a compressor inlet that is connected to a generator outlet by a first set of conduits, a second set of conduits connected to the compressor outlet and the generator inlet, and a sensor in communication with the second set of conduits, where a portion of the fluid mixture includes gas from a gas emission source, and where exhaust fluid of the generator is provided to the compressor. A process includes obtaining a target fluid property and a fluid measurement using the sensor and modifying a parameter of a fluid control device to modify a first flow rate of the flow of the exhaust fluid through the second set of conduits relative to a second flow rate of the flow of the gas provided by gas emission source through the first set of conduits.

公开(公告)号：US20190249603A1

公开(公告)日：2019-08-15

申请号：US16202194

申请日：2018-11-28

Applicant: DOOSAN HEAVY INDUSTRIES & CONSTRUCTION CO., LTD.

Inventor： Seung Min Lee ,  Dong Hun Kim ,  Jong Hwa Lee

IPC: F02C7/20 ,  F23R3/28 ,  F02C3/06 ,  F02C9/16 ,  F02C7/22

CPC classification number: F02C7/20 ,  F02C3/06 ,  F02C7/22 ,  F02C9/16 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/90 ,  F23R3/283 ,  F23R2900/00005 ,  F23R2900/00017

Abstract: A combustor of a gas turbine includes a nozzle plate to accommodate an arrangement of fuel injection nozzles; an outer cap coupled with the nozzle plate while surrounding an outer circumferential periphery of the nozzle plate; a plurality of first protrusions radially protruding from the outer cap toward a center of the outer cap, the first protrusions arranged in a circumferential direction of the outer cap; and a plurality of first guide holes arranged at the outer circumferential periphery of the nozzle plate in a circumferential direction, to be respectively engaged with the first protrusions. Each first guide hole communicates with a linear recess and with a first fixing recess disposed at an end of the linear recess. The combustor, and a gas turbine including the combustor, evenly distribute stress to the nozzle plate and the outer cap, while minimizing thermal deformation of combustor components in a high-temperature operating environment.

公开(公告)号：US20190195379A1

公开(公告)日：2019-06-27

申请号：US15850520

申请日：2017-12-21

Applicant: Hamilton Sundstrand Corporation

Inventor： James S. Elder ,  John W. Kowalski ,  Codrin Dan Sandu

IPC: F16K27/02 ,  F02C9/16 ,  F16K31/363 ,  F16K1/22 ,  B33Y80/00 ,  F16K31/122

CPC classification number: F16K27/0218 ,  B33Y80/00 ,  F01D17/148 ,  F01D25/24 ,  F02C9/16 ,  F02C9/18 ,  F05D2230/31 ,  F05D2270/56 ,  F05D2270/64 ,  F05D2300/133 ,  F05D2300/174 ,  F16K1/22 ,  F16K1/221 ,  F16K31/1223 ,  F16K31/363

Abstract: An engine air valve assembly for a gas turbine engine includes a butterfly valve having a translation shaft and a fueldraulic actuator including a piston. The piston is mechanically linked to the translation shaft by an axial to rotational conversion linkage. A regulating valve housing contains the butterfly valve and the fueldraulic actuator. The regulating valve housing includes an actuator housing portion and a valve housing portion joined via a joint section. The regulating valve housing is a single integral piece.

公开(公告)号：US20190186287A1

公开(公告)日：2019-06-20

申请号：US15848467

申请日：2017-12-20

Applicant: Plasma Igniter, LLC

Inventor： Andrew D. Lowery ,  James E. Smith

IPC: F01D21/00 ,  F02C9/28 ,  F02C9/16 ,  F02C6/18 ,  F02C7/266 ,  G05B15/02 ,  G01M15/14 ,  H05H1/46

CPC classification number: F01D21/003 ,  F02C6/18 ,  F02C7/266 ,  F02C9/16 ,  F02C9/28 ,  F05D2220/32 ,  F05D2260/80 ,  F05D2260/99 ,  F05D2270/20 ,  F05D2270/306 ,  G01M15/14 ,  G05B15/02 ,  H05H1/46 ,  H05H2001/4645

Abstract: Example implementations relate to power-generation turbines that include resonator-based diagnostics. An example implementation includes a power-generation turbine. The power-generation turbine includes a combustion chamber configured to house a combustion event of a fuel mixture. The power-generation turbine also includes a resonator having a characteristic impedance and a resonant wavelength. The resonator includes a first conductor and a second conductor separated from one another by an interstitial space that is exposed to an environment of the combustion chamber. Further, the power-generation turbine includes a controller communicatively coupled to the resonator and configured to perform operations. The operations include determining a characteristic of the resonator selected from the group consisting of the characteristic impedance and the resonant wavelength. The operations also include, based on the determined characteristic, determining a parameter of the combustion chamber.

公开(公告)号：US20180363533A1

公开(公告)日：2018-12-20

申请号：US16058625

申请日：2018-08-08

Applicant: General Electric Company

Inventor： Jessica Lynn Plummer ,  Gail Leroy Detar ,  Shashi Kiran ,  Shridhar Shrikant Kulkarni ,  Lawrence Heverley, III

IPC: F01N13/00 ,  F01N13/02 ,  B01D46/00 ,  F01N3/021 ,  F01N3/022 ,  F01N3/025 ,  F01N3/20 ,  F01N3/28 ,  F01N9/00 ,  F01N13/04 ,  F01N13/08 ,  F02C9/16 ,  F02B61/00 ,  F01N13/18 ,  B01D53/94 ,  F02D41/04 ,  F02D41/08

CPC classification number: F01N13/002 ,  B01D46/0002 ,  B01D46/002 ,  B01D46/0027 ,  B01D53/9477 ,  B01D2267/30 ,  B01D2267/70 ,  B01D2279/30 ,  F01N3/021 ,  F01N3/0222 ,  F01N3/0256 ,  F01N3/2066 ,  F01N3/208 ,  F01N3/2803 ,  F01N9/002 ,  F01N13/0097 ,  F01N13/017 ,  F01N13/02 ,  F01N13/04 ,  F01N13/08 ,  F01N13/18 ,  F01N13/1805 ,  F01N2590/08 ,  F01N2610/02 ,  F01N2610/03 ,  F01N2610/10 ,  F01N2610/1406 ,  F01N2610/1433 ,  F02B61/00 ,  F02C9/16 ,  F02D41/045 ,  F02D41/083 ,  Y02A50/2325 ,  Y02T10/24 ,  Y02T10/47

Abstract: Methods and systems are provided related to an emissions control system. The emissions control system has an exhaust after-treatment system defining a plurality of distinct exhaust flow passages through which at least a portion of an exhaust stream can flow, e.g., the exhaust stream is produced by an engine. The emissions control system also includes a controller for controlling injection of reductant into the exhaust stream flowing through each of the flow passages. In one example, the emissions control system is configured for use in a vehicle, such as a locomotive or other rail vehicle.

公开(公告)号：US20180355800A1

公开(公告)日：2018-12-13

申请号：US15621347

申请日：2017-06-13

Applicant: General Electric Company

Inventor： Thomas Edward Johnson ,  Kaitlin Marie Graham ,  Geoffrey David Myers

IPC: F02C7/232 ,  F02C7/236 ,  F02C7/22 ,  F02B19/18

CPC classification number: F02C7/232 ,  F02B19/108 ,  F02B19/18 ,  F02C7/20 ,  F02C7/222 ,  F02C7/2365 ,  F02C9/16 ,  F23D11/36 ,  F23D2206/10 ,  F23R3/286 ,  F23R3/30

Abstract: An inlet manifold includes a main inlet oriented along a first direction and a pilot inlet oriented along a second direction perpendicular to the first direction. A wye passage includes an inlet branch in fluid communication with the main inlet. The inlet manifold also includes a first main passage in fluid communication with a first outlet branch of the wye passage and a second main passage in fluid communication with a second outlet branch of the wye passage. The first main passage extends generally along the first direction between the wye passage and a first main outlet. The second main passage extends generally along the first direction between the wye passage and a second main outlet. The inlet manifold also includes a pilot passage in fluid communication with the pilot inlet. The pilot passage extends generally along the first direction between the pilot inlet and a pilot outlet.