公开(公告)号：US11661889B1

公开(公告)日：2023-05-30

申请号：US17581375

申请日：2022-01-21

Applicant: Raytheon Technologies Corporation

Inventor： Marc J. Muldoon ,  Joseph B. Staubach

IPC: F02C7/18 ,  F02C3/22 ,  F02C7/141 ,  F02C5/02

CPC classification number: F02C7/18 ,  F02C3/22 ,  F02C5/02 ,  F02C7/141 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2250/312 ,  F05D2260/213 ,  F05D2260/232

Abstract: Aircraft propulsion systems include a fan shaft connected to a fan, the fan shaft defining a centerline axis of the aircraft propulsion system, one or more offset cores arranged at an angle to the centerline axis, the one or more offset cores each comprising a hydrogen burning combustor, a centerline cavity defined along the centerline axis, and a heat exchanger arranged within the centerline cavity. In operation, a portion of air is directed from the fan into the centerline cavity to provide a first working fluid to the heat exchanger within the centerline cavity.

公开(公告)号：US10072573B2

公开(公告)日：2018-09-11

申请号：US14969079

申请日：2015-12-15

Applicant: General Electric Company

Inventor： Joseph Philip Klosinski ,  Alston Ilford Scipio ,  Sanji Ekanayake ,  George Vargese Mathai

IPC: F02C9/18 ,  F02C6/06 ,  F02C6/18 ,  F02C3/04 ,  H02K7/18 ,  F01D25/30 ,  F02C6/08 ,  F02C7/18

CPC classification number: F02C6/06 ,  F01D25/305 ,  F01K17/02 ,  F01K17/06 ,  F01K23/10 ,  F02C3/04 ,  F02C6/08 ,  F02C6/18 ,  F02C7/141 ,  F02C7/185 ,  F02C9/18 ,  H02K7/1823 ,  Y02E20/14 ,  Y02E20/16

Abstract: A power plant includes a turbine disposed downstream from a combustor. The turbine includes an extraction port that is in fluid communication with a hot gas path of the turbine and which provides a flow path for a stream of combustion gas to flow out of the turbine. An exhaust duct is disposed downstream from the turbine and receives exhaust gas from the turbine. An ejector coupled to the extraction port and to an air supply cools the stream of combustion gas upstream from the exhaust duct. The cooled combustion gas flows into the exhaust duct at a higher temperature than the exhaust gas. The cooled combustion gas mixes with the exhaust gas within the exhaust duct to provide a heated exhaust gas mixture to a heat exchanger disposed downstream from the exhaust duct. The heat exchanger may extract thermal energy from the exhaust gas mixture to produce steam.

公开(公告)号：US20180229167A1

公开(公告)日：2018-08-16

申请号：US15397797

申请日：2017-01-04

Applicant: General Electric Company

Inventor： Jeffrey Douglas Rambo

IPC: B01D45/16 ,  F01D25/32 ,  F02C7/141 ,  B01D49/02

CPC classification number: B01D45/16 ,  B01D49/02 ,  F01D25/32 ,  F02C7/052 ,  F02C7/141 ,  F05D2210/40 ,  F05D2220/32 ,  F05D2250/232 ,  F05D2260/20 ,  F05D2260/213 ,  F05D2260/607 ,  Y02T50/676

Abstract: A method and apparatus for a turbine engine having a compressor section, combustion section, and a turbine section in an axial flow arrangement with a cooling circuit in fluid communication with at least one of the compressor section, combustion section, or turbine section. The method and apparatus further including separating particles from a cooling air that flows through the cooling circuit.

公开(公告)号：US20180216901A1

公开(公告)日：2018-08-02

申请号：US15884575

申请日：2018-01-31

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Cyrille BRICAUD ,  Daniel Ponca ,  Stephan Strueken ,  Marcos Escudero Olano

IPC: F28F19/01 ,  F02C7/141

CPC classification number: F28F19/01 ,  F02C7/052 ,  F02C7/141 ,  F02C7/185 ,  F05D2260/213 ,  F05D2260/607 ,  F28D7/16

Abstract: A heat exchanger is disclosed which includes a pressure vessel with an inlet for air, an outlet for air, and a bundle of pipes housed within the pressure vessel for a thermo-vector fluid. A gas/solid separator is provided within the pressure vessel for separating particles drawn by the air.

公开(公告)号：US20180216900A1

公开(公告)日：2018-08-02

申请号：US15420326

申请日：2017-01-31

Applicant: Braden Manufacturing, LLC

Inventor： Laquinnia Lawson, JR. ,  Sanjay Mahapatra

IPC: F28F13/14 ,  F28D7/00 ,  F28D7/08 ,  F02C7/04 ,  F02C7/141

CPC classification number: F28F13/14 ,  F02C7/04 ,  F02C7/052 ,  F02C7/141 ,  F02C7/143 ,  F05D2220/32 ,  F05D2260/213 ,  F28D7/0058 ,  F28D7/082 ,  F28D2021/0026 ,  F28F2200/00 ,  F28F2210/10 ,  F28F2215/04

Abstract: A chiller coil system for an air intake system of a combustion gas turbine system includes an array of chiller cooler modules. The chiller coil system includes at least one first chiller coil and at least one second chiller coil. The first chiller coil has a first overall thermal conductance. The second chiller coil has a second overall thermal conductance greater than the first overall thermal conductance.

公开(公告)号：US10006365B2

公开(公告)日：2018-06-26

申请号：US14755406

申请日：2015-06-30

Applicant: General Electric Company

Inventor： Juan Leonardo Soria Ramirez ,  Ismael Orozco Arciga ,  Luis Alberto Aguado Mandujano ,  Humberto Sanchez Moreno

IPC: F02C6/08 ,  F02C7/14 ,  F02C7/05 ,  F02C7/141 ,  F25B9/04 ,  F02C7/052 ,  F02C7/055 ,  B01D53/26

CPC classification number: F02C7/141 ,  B01D53/26 ,  F02C6/08 ,  F02C7/052 ,  F02C7/055 ,  F05D2220/32 ,  F05D2260/209 ,  F05D2260/607 ,  F25B9/04 ,  Y02T50/675

Abstract: An air supply and conditioning system for an inlet system of a gas turbine includes an air processing unit having an inlet configured to receive compressed air from a compressor of the gas turbine. The air processing unit includes a heat exchanger that is downstream from the inlet. A vortex cooler is disposed downstream from the inlet of the air processing unit. The vortex cooler is in fluid communication with the heat exchanger and with an outlet of the air processing unit. The system further includes a self-cleaning filter that is disposed within a duct of the inlet system. The self-cleaning filter is in fluid communication with at least one of the outlet of the air processing unit or an outlet of the vortex cooler.

公开(公告)号：US20180172270A1

公开(公告)日：2018-06-21

申请号：US15385041

申请日：2016-12-20

Applicant: NATIONAL CHUNG SHAN INSTITUTE OF SCIENCE AND TECHNOLOGY

Inventor： YUNG-MAO TSUEI ,  CHIH-CHUAN LEE

IPC: F23R3/02 ,  F02C3/14 ,  H02K7/18

CPC classification number: F23R3/02 ,  F02C3/145 ,  F02C7/141 ,  F23C2900/03001 ,  H02K7/1823 ,  Y02T50/675

Abstract: A micro turbine generator includes a compressor, a guide channel, an expansion chamber, and a recuperator. The expansion chamber includes an air inlet, an air outlet, and a guide vane structure. The air inlet is disposed at one end of the expansion chamber, connected with the compressor through the guide channel, and receives an air compressed by the compressor. The air outlet is disposed at the other end of the expansion chamber, connected with the recuperator, and discharges the air, allowing the air to enter the recuperator. The guide vane structure extends inward from an inner wall of the expansion chamber to allow the air to pass the guide vane structure before being discharged from the air outlet to enter the recuperator.

公开(公告)号：US09995314B2

公开(公告)日：2018-06-12

申请号：US14803862

申请日：2015-07-20

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Jeffrey Anthony Hamel

IPC: F02C7/14 ,  F04D29/58 ,  F02C7/141 ,  F02C7/16 ,  F01D5/08 ,  F04D19/02 ,  F04D29/32 ,  F04D29/54

CPC classification number: F04D29/5846 ,  F01D5/081 ,  F02C7/14 ,  F02C7/141 ,  F02C7/16 ,  F04D19/02 ,  F04D29/324 ,  F04D29/541 ,  F05D2220/32 ,  F05D2260/212 ,  Y02T50/676

Abstract: A gas turbine engine including a compressor section and a turbine section, coupled by one or more shafts, is provided. The compressor section progressively compresses air and includes an aft-stage of rotor blades rotatable about an axial direction of the gas turbine engine. A cooling system is included with the gas turbine engine for cooling compressed air in or from the compressor section. The cooling system includes a fluid tank for storing a volume of cooling fluid and one or more fluid lines in fluid communication with the fluid tank. The one or more fluid lines include an outlet positioned adjacent to the aft-stage of rotor blades for injecting cooling fluid into the compressed air proximate the aft-stage of rotor blades.

公开(公告)号：US09982629B2

公开(公告)日：2018-05-29

申请号：US15185498

申请日：2016-06-17

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies, Inc.

Inventor： Michael J. Armstrong ,  Igor Vaisman

IPC: F02C3/04 ,  F02C3/13 ,  F02C1/10 ,  F02C7/08 ,  F02K3/00 ,  F01K23/10 ,  F02K3/077 ,  F02C1/00 ,  F02C6/20 ,  F02C7/141 ,  F02C7/18 ,  F02C3/10 ,  F02K99/00 ,  F22B3/08 ,  F02C7/143 ,  F01K25/10

CPC classification number: F02K3/00 ,  F01K23/10 ,  F01K25/103 ,  F02C1/007 ,  F02C1/10 ,  F02C3/04 ,  F02C3/10 ,  F02C3/13 ,  F02C6/206 ,  F02C7/08 ,  F02C7/141 ,  F02C7/143 ,  F02C7/18 ,  F02K3/077 ,  F02K99/00 ,  F05D2210/10 ,  F05D2210/13 ,  F05D2250/311 ,  F05D2260/213 ,  F22B3/08 ,  Y02T50/676

Abstract: A gas turbine engine includes a first shaft coupled to a first turbine and a first compressor, a second shaft coupled to a second turbine and a second compressor, and a third shaft coupled to a third turbine and a fan assembly. The turbine engine includes a heat rejection heat exchanger configured to reject heat from a closed loop system with air passed from the fan assembly, and a combustor positioned to receive compressed air from the second compressor as a core stream. The closed-loop system includes the first, second, and third turbines and the first compressor and receives energy input from the combustor.

公开(公告)号：US09957892B2

公开(公告)日：2018-05-01

申请号：US14409490

申请日：2013-06-14

Applicant: Daniel Pomerleau

Inventor： Daniel Pomerleau

IPC: F02C7/141 ,  F02C3/04 ,  F23R3/28 ,  F23R3/30 ,  F02C9/40 ,  F02K9/42 ,  F02C3/22

CPC classification number: F02C7/141 ,  F02C3/04 ,  F02C3/22 ,  F02C9/40 ,  F02K9/42 ,  F23R3/286 ,  F23R3/30

Abstract: The invention relates to systems enabling the use of cryogenic fuels within combustion engines, including jet engines.