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1. 发明授权

US11781521B2 Toroidal lift force engine 有权
公开(公告)号：US11781521B2
公开(公告)日：2023-10-10
申请号：US17186739
申请日：2021-02-26
申请人： Orville J. Birkestrand
发明人： Orville J. Birkestrand
IPC分类号： F03D1/02 , F03B3/04 , F01D13/00 , F01D5/02 , F01D13/02 , F03D13/10 , F03D1/06 , F03D7/02 , F03B3/18 , F03B3/12 , F03D3/02 , F03B3/02
CPC分类号： F03D1/02 , F01D5/021 , F01D13/00 , F01D13/003 , F01D13/006 , F01D13/02 , F03B3/02 , F03B3/04 , F03B3/12 , F03B3/18 , F03D1/0633 , F03D3/02 , F03D7/0276 , F03D13/10
摘要： A toroidal lift force engine is provided. Illustratively, the toroidal lift force engine operates in an enclosed environment without heat and/or expelling particles of any kind, utilizing asymmetric pressure distribution on lift turbine blades solely to generate thrust with the normal component of this lift force, while using the tangential component of this lift force to drive accessories, provide control to the fluid velocity, and/or provide motivation of the fluid's flow. The toroidal lift force engine may be utilized to generate thrust, heat and/or electricity for powering vehicles, homes, etc.

2. 发明申请

US20220178268A1 Intercooled Cascade Cycle Waste Heat Recovery System 有权
公开(公告)号：US20220178268A1
公开(公告)日：2022-06-09
申请号：US17430398
申请日：2020-03-05
申请人： Industrom Power LLC
发明人： Paul Angel , Joseph Harris
IPC分类号： F01D13/00 , F01K25/10 , F01K7/02 , F01K7/32
摘要： Provided herein is a power generation system and method for transforming thermal energy, such as waste heat, into mechanical energy and/or electrical energy. The system employs features designed to accelerate start times, reduce size, lower cost, and be more environmentally friendly. Tire system may include multiple compressors on separate pinion shafts with multiple expanders, a temperature valve upstream of compressors with a mass management system downstream, an intercooler between compressors, and a cascade exchanger. In one embodiment, the system is configured to drive a synchronous generator, with the separate pinion shafts rotating at two separate, but constant, speeds.

3. 发明申请

US20210381431A1 SPLITTER AND GUIDE VANE ARRANGEMENT FOR GAS TURBINE ENGINES 有权
公开(公告)号：US20210381431A1
公开(公告)日：2021-12-09
申请号：US16891492
申请日：2020-06-03
申请人： Raytheon Technologies Corporation
发明人： Daniel Bernard Kupratis , Paul R. Hanrahan
IPC分类号： F02C3/107 , F02C9/18 , F01D9/06 , F01D13/00 , F01D25/16 , F01D17/16
摘要： A section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor including a row of blades extending in a radial direction outwardly from a hub. The row of blades deliver flow to a bypass flow path, an intermediate flow path, and a core flow path. A first case surrounds the row of blades to establish the bypass flow path. A first flow splitter divides flow between the bypass flow path and a second duct. A row of guide vanes extends in the radial direction across the bypass flow path. A second flow splitter radially inboard of the first flow splitter divides flow from the second duct between the intermediate flow path and the core flow path. A bypass port interconnects the intermediate and bypass flow paths. A method of operation for a gas turbine engine is also disclosed.

4. 发明授权

US11161603B2 Architecture for a propulsion system of a helicopter including a hybrid turboshaft engine and a system for reactivating said hybrid turboshaft engine 有权
公开(公告)号：US11161603B2
公开(公告)日：2021-11-02
申请号：US15517924
申请日：2015-10-06
申请人： SAFRAN HELICOPTER ENGINES , SAFRAN ELECTRICAL & POWER
发明人： Philippe Vallart , Jean-Michel Bazet , Loïc Le Duigou
IPC分类号： B64C27/14 , F01D13/00 , F01D19/00 , F02C7/36 , B64D27/24 , B64D27/02 , F02C7/268
摘要： The invention relates to an architecture of a propulsion system of a multi-engine helicopter comprising turboshaft engines connected to a power transmission gearbox, characterised in that it comprises: at least one hybrid turboshaft engine (20) capable of operating in at least one standby mode during a stable cruise flight of the helicopter; at least two systems (30; 40) for controlling each hybrid turboshaft engine (20), each system (30; 40) comprising an electric machine (31; 41) connected to the hybrid turboshaft engine (20) and suitable for rotating the gas generator thereof, and at least one source (33; 43) of electrical power for said electric machine (31; 41), each reactivation system (30; 40) being configured such that it can drive said turboshaft engine (20) in at least one operating mode among a plurality of predetermined modes.

5. 发明授权

US11136922B2 Gas turbine engine transfer efficiency 有权
公开(公告)号：US11136922B2
公开(公告)日：2021-10-05
申请号：US16545003
申请日：2019-08-20
申请人： ROLLS-ROYCE plc
发明人： Craig W Bemment , Pascal Dunning
IPC分类号： F02C9/28 , F01D11/14 , F01D13/00 , F01D25/24
摘要： A gas turbine engine for an aircraft includes an engine core including a first, lower pressure, turbine, a first compressor, and a first core shaft connecting the first turbine to the first compressor; and a second, higher pressure, turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor, and a fan located upstream of the engine core and including a plurality of fan blades extending from a hub. A low pressure turbine temperature change is defined as: the ⁢ ⁢ first ⁢ ⁢ turbine ⁢ ⁢ entrance ⁢ ⁢ temperature the ⁢ ⁢ first ⁢ ⁢ turbine ⁢ ⁢ exit ⁢ ⁢ temperature . A fan tip temperature rise is defined as: the ⁢ ⁢ fan ⁢ ⁢ tip ⁢ ⁢ rotor ⁢ ⁢ exit ⁢ ⁢ temperature the ⁢ ⁢ fan ⁢ ⁢ rotor ⁢ ⁢ entry ⁢ ⁢ temperature . A turbine to fan tip temperature change ratio of: the ⁢ ⁢ low ⁢ ⁢ pressure ⁢ ⁢ turbine ⁢ ⁢ temperature ⁢ ⁢ change the ⁢ ⁢ fan ⁢ ⁢ tip ⁢ ⁢ temperature ⁢ ⁢ rise is in the range from 1.46 to 2.0.

6. 发明授权

US11124311B2 Engine assembly with a dedicated voltage bus 有权
公开(公告)号：US11124311B2
公开(公告)日：2021-09-21
申请号：US15983528
申请日：2018-05-18
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Jean Thomassin , Eric Taillon
IPC分类号： B64D35/08 , F02N11/04 , F02C7/36 , F01D13/00 , F01D15/10 , F02C7/275 , F02C7/32 , B64D41/00 , H02J1/00 , H02J3/00 , B64C25/40
摘要： There is provided an engine assembly for an aircraft, comprising a heat engine in driving engagement with an engine shaft having a first end coupled to a mechanical gearbox and a second end opposite the first end, an electric generator coupled to the second end to provide a generator output voltage, the electric generator separate from the mechanical gearbox, a power electronics module connected to the electric generator and configured to regulate the generator output voltage to provide a regulated output voltage that meets an electrical power demand of at least one aircraft accessory, and a voltage bus connected to the power electronics module and configured to supply the regulated output voltage to the at least one aircraft accessory.

7. 发明授权

US10927756B2 Multi-stage radial turboexpander 有权
公开(公告)号：US10927756B2
公开(公告)日：2021-02-23
申请号：US16254820
申请日：2019-01-23
申请人： NUOVO PIGNONE TECNOLOGIE SRL
发明人： Giuseppe Iurisci , Paola Di Festa , Francesco Cangioli , Davide Biliotti
IPC分类号： F02C1/02 , F01D1/08 , F01D5/04 , F02C6/16 , F01D5/02 , F01D13/00 , F01D15/06 , F01D15/12 , F02C7/32
摘要： A multi-stage turboexpander and a method for generating mechanical power therewith are disclosed. The multi-stage turboexpander includes a casing and a shaft, arranged for rotation in the casing. The shaft is supported by a first bearing at a first shaft end portion and a second bearing at a second shaft end portion. A first radial impeller and a second radial impeller are arranged between the first bearing and the second bearing on the shaft for co-rotation therewith around a rotation axis.

8. 发明授权

US10829232B2 Aircraft comprising a propulsion assembly including a fan on the rear of the fuselage 有权
公开(公告)号：US10829232B2
公开(公告)日：2020-11-10
申请号：US15745770
申请日：2016-07-21
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Nicolas Jerome Jean Tantot
IPC分类号： B64D27/20 , B64D33/04 , B64D35/06 , F02K3/062 , B64D27/14 , F01D13/00 , B64D27/26 , F02C6/02 , F02K3/02 , F02K3/072
摘要： The present invention relates to an aircraft including a fuselage and a thruster downstream of the fuselage. The thruster includes a power turbine, located inside a main flow jet, and at least one fan, located inside a secondary flow jet and mechanically driven by the power turbine. The main flow jet of the power turbine and the secondary flow jet of the fan are concentric. The power turbine is supplied with gases from two gas turbine gas generators via two supply channels. The gas turbine gas generators have axes parallel to that of the fuselage. The air inlet sleeve is spaced apart from the fuselage, and the supply channels each have a hatch for controlling the flow between a position for guiding the gas flow to the power turbine and a position for ejecting the gases into the atmosphere while bypassing the power turbine.

9. 发明申请

US20200347742A1 GAS TURBINE ENGINE WITH A DOUBLE WALL CORE CASING 审中-公开
公开(公告)号：US20200347742A1
公开(公告)日：2020-11-05
申请号：US16520740
申请日：2019-07-24
申请人： ROLLS-ROYCE plc
发明人： Chathura K. KANNANGARA , Jillian C. GASKELL , Stewart T. THORNTON , Timothy PHILP
IPC分类号： F01D13/00 , F01D5/12 , F01D5/30
摘要： A gas turbine engine includes an engine core including: a compressor system including first, lower pressure, compressor, and a second, higher pressure, compressor; and an outer core casing surrounding the compressor system and including a first flange connection arranged to allow separation of the outer core casing at an axial position of the first flange connection, wherein the first flange connection is the first flange connection that is downstream of an axial position defined by the axial midpoint between the mid-span axial location on the trailing edge of the most downstream aerofoil of the first compressor and the mid-span axial location on the leading edge of the most upstream aerofoil of the second compressor; a nacelle surrounding the engine core and defining a bypass duct between the engine core and the nacelle; wherein an axial midpoint of the radially outer edge is defined as the fan OGV tip centrepoint.

10. 发明授权

US10450849B2 System and method for system and method for a turbomachine multiphase hyrdrocarbon pump having an auger coupling 有权
公开(公告)号：US10450849B2
公开(公告)日：2019-10-22
申请号：US15787281
申请日：2017-10-18
申请人： Salvatore F. Grande, III , Sami Suheil
发明人： Salvatore F. Grande, III , Sami Suheil
IPC分类号： E21B43/38 , F01D1/34 , F01D15/02 , F01D21/14 , B01D45/14 , E21B43/12 , B01D21/26 , B01D21/24 , F01D13/00
摘要： A bladeless conical radial rotary machine method and system are disclosed. Turbo-machinery and methods are disclosed for a bladeless conical radial rotary machine wherein fluid is directed axially within the pump body to produce an axial output. The rotor comprises a plurality of spaced apart conical elements. The fluid is smoothly directed to any number of subsequent boundary layer pumping stages which are axially positioned with respect to each other. The fluid is smoothly directed to any number of subsequent boundary layer pumping stages which are axially positioned with respect to each other. A coupling between pumping stages is disclosed.

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