公开(公告)号：US12060828B1

公开(公告)日：2024-08-13

申请号：US18228194

申请日：2023-07-31

申请人： Stolle Machinery Company, LLC

发明人： John Nigel Grainger

IPC分类号： F02C6/18 ,  B21D51/26 ,  F02C6/04

CPC分类号： F02C6/04 ,  B21D51/26 ,  F02C6/18 ,  F05D2220/32 ,  F05D2220/62 ,  F05D2220/764 ,  F05D2260/213

摘要： A turbine system structured to generate electricity from waste gas includes a combustor structured to burn gas to heat air, a heat exchanger structured to receive the heated air, and a turbine energy conversion system including a compressor turbine structured to compress ambient air and provide the compressed air to the heat exchanger, wherein the heat exchanger is structured to heat the compressed air with the heated air, a generator turbine structured to be turned by the heated compressed air from the decompressor turbine, and a generator structured to be turned by the generator turbine and to generate electricity in response to being turned. The turbine system further includes a mixer structured to receive excess air from the heat exchanger and the generator turbine and to mix the excess air with ambient air to a desired temperature.

公开(公告)号：US20240246689A1

公开(公告)日：2024-07-25

申请号：US18243049

申请日：2023-09-06

申请人： JETOPTERA, INC.

发明人： Andrei Evulet

IPC分类号： B64D33/04 ,  B64C9/38 ,  B64C15/00 ,  B64C15/14 ,  B64C21/00 ,  B64C21/04 ,  B64C23/00 ,  B64C39/02 ,  B64D27/10 ,  B64D27/18 ,  B64D29/02 ,  B64D33/02 ,  B64U30/00 ,  B64U30/10 ,  F02C3/04 ,  F02C6/04 ,  F02K1/00 ,  F02K1/36

CPC分类号： B64D33/04 ,  B64C9/38 ,  B64C15/00 ,  B64C15/14 ,  B64C21/00 ,  B64C21/04 ,  B64C23/00 ,  B64C23/005 ,  B64C39/024 ,  B64D27/10 ,  B64D27/18 ,  B64D29/02 ,  B64D33/02 ,  F02C3/04 ,  F02C6/04 ,  F02K1/002 ,  F02K1/36 ,  B64C2230/04 ,  B64C2230/06 ,  B64C2230/16 ,  B64D2033/0273 ,  B64U30/00 ,  B64U30/10 ,  F05D2220/90 ,  Y02T50/10 ,  Y02T50/30 ,  Y02T50/40

摘要： A propulsion system coupled to a vehicle. The system includes a convex surface, a diffusing structure coupled to the convex surface, and at least one conduit coupled to the convex surface. The conduit is configured to introduce to the convex surface a primary fluid produced by the vehicle. The system further includes an intake structure coupled to the convex surface and configured to introduce to the diffusing structure a secondary fluid accessible to the vehicle. The diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid and secondary fluid.

公开(公告)号：US20240003270A1

公开(公告)日：2024-01-04

申请号：US17856401

申请日：2022-07-01

申请人： GENERAL ELECTRIC COMPANY

发明人： Raub Warfield Smith ,  Majed Sammak

IPC分类号： F01K23/08 ,  F02C6/04 ,  F01K23/10

CPC分类号： F01K23/08 ,  F02C6/04 ,  F01K23/10 ,  F05D2220/32 ,  F05D2220/31 ,  F05D2220/72 ,  F05D2220/74 ,  F05D2260/213

摘要： A combined cycle power plant including a gas turbine engine having a compressor inlet and a turbine outlet that is configured to discharge a first exhaust gas stream therefrom. A heat recovery steam generator is configured to receive the first exhaust gas stream, extract heat from the first exhaust gas stream to make steam, and discharge a second exhaust gas stream therefrom. A steam turbine is configured to discharge a steam stream therefrom, a carbon capture system is configured to receive the steam stream, a recirculation blower is configured to pressurize a portion of the second exhaust gas stream for recirculation towards the compressor inlet, and an air inlet blower is configured to pressurize an airflow stream channeled towards the compressor inlet, such that a pressurized mixed flow stream, formed from the portion of the second exhaust gas stream and the airflow stream, is received at the compressor inlet.

公开(公告)号：US11859542B2

公开(公告)日：2024-01-02

申请号：US17645162

申请日：2021-12-20

申请人： Rolls-Royce North American Technologies, Inc.

发明人： Richard K Keller ,  Paul Johnson

IPC分类号： F02C6/04 ,  F02C9/18 ,  F02K3/02

CPC分类号： F02C6/04 ,  F02C9/18 ,  F02K3/025 ,  F05D2220/90 ,  F05D2240/128 ,  F05D2260/606 ,  F05D2270/053 ,  F05D2270/335

摘要： A system including a turbine engine configured to generate rotor power and produce an engine air flow. The system is configured to provide rotor power to one of more shaft-driven lift fans to generate a first thrust on an aircraft body and provide a gas flow to one or more gas-driven lift fans to generate a second thrust on the aircraft body. The gas flow may be at least a portion of the engine air flow produced by the turbine engine. The turbine engine may be configured to exhaust another portion of the engine air flow through a jet nozzle to generate an engine thrust. In examples, the system includes at least a second turbine engine. The one of more shaft-driven lift fans and/or one of more gas-driven lift fans be powered by the turbine engine, the second turbine engine, or both the turbine engine and the second turbine engine.

公开(公告)号：US20230405545A1

公开(公告)日：2023-12-21

申请号：US17841265

申请日：2022-06-15

申请人： King Fahd University of Petroleum and Minerals ,  King Abdullah City for Atomic & Renewable Energy (K.A.CARE)

发明人： Mohammed Abdulaziz HABIB ,  Binash IMTEYAZ

IPC分类号： B01J19/24 ,  B01D53/22 ,  F02C7/12 ,  F02C6/04 ,  B01J19/00 ,  C01B3/04 ,  C01B3/02 ,  C01C1/04 ,  C01B13/02 ,  C01B32/50

CPC分类号： B01J19/2475 ,  B01D53/229 ,  B01D53/228 ,  B01D53/227 ,  F02C7/12 ,  F02C6/04 ,  B01J19/245 ,  B01J19/0013 ,  C01B3/045 ,  C01B3/025 ,  C01C1/04 ,  C01B13/0207 ,  C01B13/0251 ,  C01B32/50 ,  B01J2219/00117

摘要： A system for co-generating ammonia and power is described. The system includes oxygen transport reactors having an ion transport membrane (ITM) that separates a feed side and a permeate side. The feed side includes a feed inlet and a feed outlet, and the permeate side includes a permeate inlet and a permeate outlet. A first feed inlet receives water vapor to be converted into hydrogen and first oxygen, and a second feed inlet receives air to be split into nitrogen and second oxygen. The ITM selectively allows permeation of the first oxygen and the second oxygen to respective permeate side to support oxy-combustion process. A first feed outlet discharges hydrogen and a second feed outlet discharges nitrogen, where the hydrogen and the nitrogen are combined in a catalytic converter to form ammonia. Combustion gases from the oxygen transport reactors are used to run a gas turbine to extract power.

公开(公告)号：US11802496B2

公开(公告)日：2023-10-31

申请号：US17657472

申请日：2022-03-31

申请人： Southwest Research Institute

发明人： Grant O. Musgrove ,  Brian Connolly

IPC分类号： F01K25/10 ,  F01K19/00 ,  F01K17/04 ,  F01K7/32 ,  F02C6/04

CPC分类号： F01K25/103 ,  F01K7/32 ,  F01K17/04 ,  F01K19/00 ,  F02C6/04

摘要： Direct-fired supercritical carbon dioxide (CO2) power cycle that generates hydrogen. More specifically, the discharge of a direct fired supercritical CO2 power cycle is converted to carbon dioxide and hydrogen where the hydrogen and/or carbon dioxide can be separated and stored/utilized in another application.

公开(公告)号：US20220261018A1

公开(公告)日：2022-08-18

申请号：US17619105

申请日：2020-06-12

申请人： LIEBHERR-AEROSPACE TOULOUSE SAS

发明人： Jean-Luc MANCHO ,  David LOSSOUARN ,  Antoine PEYRE

IPC分类号： G05D16/18 ,  B64D13/00 ,  F02C7/18 ,  F02C6/04

摘要： The invention relates to a regulator, configured to receive a stream of hot air carrying pneumatic power via an air inlet (12), to treat this hot air and to send the treated hot air to an air outlet (14) configured 5 to supply a pneumatic actuator (16), comprising a reference pressure source and an air expansion device comprising a diaphragm (22), the diaphragm (22) being configured to control the flow rate of the hot air stream by comparing the pressure of said hot air stream with the reference pressure of the reference pressure source. The regulator is characterized in that it 10 comprises an air intake (24) configured to receive a cold source, and a pipe (25) for guiding the cold source to the diaphragm (22), so that the cold source forms the reference pressure source and a source for cooling the diaphragm (22).

公开(公告)号：US20220213838A1

公开(公告)日：2022-07-07

申请号：US17649866

申请日：2022-02-03

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Kevin NG ,  Johnny VINSKI ,  Adam LOGAN

IPC分类号： F02C6/02 ,  B64D35/08 ,  F02C6/04 ,  F02C9/18

摘要： A multi-engine aircraft includes a first engine drivingly engaged to a common rotatable load and a second engine drivingly engaged to the common rotatable load, the second engine having a bleed air system and a control system in communication with a compressed air switching system. The control system controls operation of the second engine and/or the compressed air switching system. The compressed air switching system includes a switching valve that is displaceable between at least a first position and a second position, the first position interconnecting a lower pressure inlet and a switch outlet, and the second position interconnecting a high pressure inlet and the switch outlet. The switch outlet is in communication with the bleed air system of the second engine. The control system actuates the switching valve to switch between the first and second positions.

公开(公告)号：US11378361B1

公开(公告)日：2022-07-05

申请号：US17134313

申请日：2020-12-26

申请人： COLLATERL OPPORTUNITIES, LLC

发明人： Bruce Howard Kusens

IPC分类号： F41H11/08 ,  F02C9/16 ,  F02C7/24 ,  G05B15/02 ,  G08G5/00 ,  F41H11/02 ,  F02C6/04

摘要： A system and method that uses one or more jet engines to remove unmanned aircraft from restricted airspace. Generally, the force created by a jet engine can be used to remove drones or other unwanted objects from the restricted airspace. Once the system determines the presence of an unauthorized aircraft or object within the restricted airspace, the jet engine(s) can be activated and used to pull the drone or flying object towards the jet engine though the force created by the intake of the jet engine(s), or to expel the drone or object from the restricted area through the force created by the exhaust of the jet engine(s).

公开(公告)号：US11274603B1

公开(公告)日：2022-03-15

申请号：US16999662

申请日：2020-08-21

申请人： Bob Burkett

发明人： Bob Burkett

IPC分类号： F02C7/224 ,  F02C7/08 ,  F02K3/10 ,  H02K7/20 ,  H02K7/18 ,  F02C6/18 ,  F02C6/04

摘要： Systems and methods for gas turbine or jet engines may include, among other things, one or more electric heating elements located within a combustion chamber of a gas turbine engine, a combustion chamber of a jet engine, or an afterburner of a jet engine. A combustion chamber and/or an afterburner may be configured to generate heated gas by using the one or more electric heating elements to heat gases within the combustion chamber and/or afterburner. A combustion chamber and/or an afterburner may be configured to generate an exhaust output based on the heated gas. The exhaust output may drive a turbine which generates electricity or mechanical energy. Thrust from the exhaust output from a jet engine may propel a vehicle.