公开(公告)号：US12196090B1

公开(公告)日：2025-01-14

申请号：US18427190

申请日：2024-01-30

Applicant: Pratt & Whitney Canada Corp.

Inventor： Louis-Philippe Larose

IPC: F01D21/00 ,  B64D27/34 ,  B64D31/18 ,  B64D35/022 ,  F01D13/00 ,  F01D15/10

Abstract: A method of braking a rotational air mover portion of an aircraft propulsion system is provided. The method includes: using an electrical device to apply a torque to a propulsion unit driven by a propulsion system of an aircraft, the propulsion unit including a rotational air mover configured to provide thrust for propelling the aircraft, wherein the electrical device is configured to produce electrical energy during the process of applying the torque to the propulsion unit; controlling the electrical device to apply an amount of the torque that is sufficient to cause the rotational air mover to decelerate or to maintain the rotational air mover non-rotational; and directing the electrical energy produced by the electrical device to an aircraft component.

公开(公告)号：US12050009B2

公开(公告)日：2024-07-30

申请号：US17525945

申请日：2021-11-14

Applicant: GUANGDONG UNIVERSITY OF TECHNOLOGY ,  Guangzhou Herui Energy Conservation and Environmental Protection Technology Co., Ltd.

Inventor： Xiaozhou Liu ,  Peibin Lin ,  Wei Liu ,  Longbiao Dong ,  Yu Zhang

IPC: F23G5/12 ,  F01D13/00 ,  F01D25/08 ,  F01N5/02 ,  F01N5/04 ,  F23C9/08 ,  F23G5/46 ,  F23G7/06 ,  F25B27/02

CPC classification number: F23G5/12 ,  F01D13/00 ,  F01D25/08 ,  F01N5/02 ,  F01N5/04 ,  F23C9/08 ,  F23G5/46 ,  F23G7/06 ,  F05D2220/31 ,  F05D2260/20 ,  F23G2206/10 ,  F23G2206/20 ,  F25B27/02

Abstract: A low nitrogen coupling combustion system for the disposal of waste stink gas and solid waste, including a waste pit, at least one stink gas incineration equipment and a waste incinerator, wherein the waste pit is equipped with stink gas outlets and the stink gas incineration equipment is provided with an incineration chamber for burning stink gas, as well as a stink gas inlet, a fuel inlet and a burned stink gas outlet which are connected with the incineration chamber; the stink gas inlet is connected with the stink gas outlet of the waste pit through a stink gas delivery pipe, and the fuel inlet is connected with a fuel source through a fuel delivery pipe; the burned stink gas outlet is connected with a combustion-supporting air inlet of the waste incinerator through a flue gas discharge pipe.

公开(公告)号：US11781521B2

公开(公告)日：2023-10-10

申请号：US17186739

申请日：2021-02-26

Applicant: Orville J. Birkestrand

Inventor： Orville J. Birkestrand

IPC: 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 classification number: 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

Abstract: 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.

公开(公告)号：US20220178268A1

公开(公告)日：2022-06-09

申请号：US17430398

申请日：2020-03-05

Applicant: Industrom Power LLC

Inventor： Paul Angel ,  Joseph Harris

IPC: F01D13/00 ,  F01K25/10 ,  F01K7/02 ,  F01K7/32

Abstract: 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.

公开(公告)号：US20210381431A1

公开(公告)日：2021-12-09

申请号：US16891492

申请日：2020-06-03

Applicant: Raytheon Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Paul R. Hanrahan

IPC: F02C3/107 ,  F02C9/18 ,  F01D9/06 ,  F01D13/00 ,  F01D25/16 ,  F01D17/16

Abstract: 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.

公开(公告)号：US11161603B2

公开(公告)日：2021-11-02

申请号：US15517924

申请日：2015-10-06

Applicant: SAFRAN HELICOPTER ENGINES ,  SAFRAN ELECTRICAL & POWER

Inventor： Philippe Vallart ,  Jean-Michel Bazet ,  Loïc Le Duigou

IPC: B64C27/14 ,  F01D13/00 ,  F01D19/00 ,  F02C7/36 ,  B64D27/24 ,  B64D27/02 ,  F02C7/268

Abstract: 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.

公开(公告)号：US11136922B2

公开(公告)日：2021-10-05

申请号：US16545003

申请日：2019-08-20

Applicant: ROLLS-ROYCE plc

Inventor： Craig W Bemment ,  Pascal Dunning

IPC: F02C9/28 ,  F01D11/14 ,  F01D13/00 ,  F01D25/24

Abstract: 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.

公开(公告)号：US11124311B2

公开(公告)日：2021-09-21

申请号：US15983528

申请日：2018-05-18

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jean Thomassin ,  Eric Taillon

IPC: B64D35/08 ,  F02N11/04 ,  F02C7/36 ,  F01D13/00 ,  F01D15/10 ,  F02C7/275 ,  F02C7/32 ,  B64D41/00 ,  H02J1/00 ,  H02J3/00 ,  B64C25/40

Abstract: 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.

公开(公告)号：US10927756B2

公开(公告)日：2021-02-23

申请号：US16254820

申请日：2019-01-23

Applicant: NUOVO PIGNONE TECNOLOGIE SRL

Inventor： Giuseppe Iurisci ,  Paola Di Festa ,  Francesco Cangioli ,  Davide Biliotti

IPC: F02C1/02 ,  F01D1/08 ,  F01D5/04 ,  F02C6/16 ,  F01D5/02 ,  F01D13/00 ,  F01D15/06 ,  F01D15/12 ,  F02C7/32

Abstract: 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.

公开(公告)号：US10829232B2

公开(公告)日：2020-11-10

申请号：US15745770

申请日：2016-07-21

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Nicolas Jerome Jean Tantot

IPC: B64D27/20 ,  B64D33/04 ,  B64D35/06 ,  F02K3/062 ,  B64D27/14 ,  F01D13/00 ,  B64D27/26 ,  F02C6/02 ,  F02K3/02 ,  F02K3/072

Abstract: 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.