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1.发明授权公开(公告)号：US12129813B1
公开(公告)日：2024-10-29
申请号：US18633815
申请日：2024-04-12
CPC分类号： F02K7/10 , F02C1/08 , F02C1/10 , F04D21/00 , F05D2220/10 , F05D2220/76
摘要： A new power plant cycle facilitated by an innovative vapor compression apparatus to repressurize the air vapor and generate renewable energy for heat input to the cycle. The new cycle can be used in place of the conventional low efficiency Rankine cycle or other cycles to provide economical production of electricity without air pollution. The new cycle can also be used on-board land-based vehicles, aircraft, and watercraft to power them electrically or mechanically, or be used in a package unit for supplying electricity and controlling temperatures of indoor homes, business, and other structures. The new cycle can be used in Ramjet aircraft applications.
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公开(公告)号：US12123432B2
公开(公告)日：2024-10-22
申请号：US18201875
申请日：2023-05-25
发明人： Bruce L. Morin , Detlef Korte
IPC分类号： F02C7/36 , F01D5/06 , F01D5/14 , F01D15/12 , F01D25/24 , F02C3/04 , F02C3/107 , F02K3/04 , F02K3/06 , F04D25/04 , F04D29/053 , F04D29/32 , F04D29/66 , G06F30/17
CPC分类号： F04D29/663 , F01D5/06 , F01D5/14 , F01D15/12 , F01D25/24 , F02C3/04 , F02C3/107 , F02C7/36 , F02K3/04 , F02K3/06 , F04D25/045 , F04D29/053 , F04D29/321 , F04D29/325 , G06F30/17 , F05D2220/323 , F05D2230/50 , F05D2260/40311 , F05D2260/96 , F05D2270/304 , F05D2270/333
摘要： An aircraft system includes, among other things, an aircraft and a gas turbine engine coupled to the aircraft. The gas turbine engine includes a propulsor section including a propulsor, a compressor section, a turbine section including a first turbine and a second turbine, and a gear reduction between the propulsor and the second turbine. The second turbine includes a number of turbine blades in each of a plurality of rows of the second turbine. The second turbine blades operating at least some of the time at a rotational speed. The number of blades and the rotational speed being such that the following formula holds true for a majority of the blade rows of the second turbine: 5500 Hz≤(number of blades×speed)/60 sec≤10000 Hz. The gas turbine engine is rated to produce 15,000 pounds of thrust or more.
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公开(公告)号：US12123351B2
公开(公告)日：2024-10-22
申请号：US17484897
申请日：2021-09-24
申请人： ROLLS-ROYCE plc
CPC分类号： F02C7/18 , F01D25/12 , F02C7/04 , F02C7/143 , F02C7/185 , F02K3/065 , F05D2260/213 , F05D2260/232 , F05D2260/36 , F05D2260/606
摘要： A turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly comprises a plurality of fan blades defining a fan diameter (D), and the heat exchanger module comprises a plurality of heat exchanger elements. The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, with the heat exchanger module having an axial length along a central axis between an upstream-most face of the heat exchanger elements and a downstream-most face of the heat exchanger elements. The axial length is in the range of 0.1*D to 5.0*D.
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公开(公告)号：US12123350B2
公开(公告)日：2024-10-22
申请号：US17190076
申请日：2021-03-02
发明人： Daniel Alan Niergarth , Nicholas M. Daggett , Steven Douglas Johnson , Anand P. Roday , Scott Alan Schimmels
CPC分类号： F02C7/18 , F02C7/14 , F02C7/047 , F02K3/077 , F05D2240/12 , F05D2260/213
摘要： A three-stream engine is provided. The three-stream engine includes a fan section, a core engine disposed downstream of the fan section, and a core cowl annularly encasing the core engine and at least partially defining a core duct. A fan cowl is disposed radially outward from the core cowl and annularly encasing at least a portion of the core cowl. The fan cowl at least partially defining an inlet duct and a fan duct. The fan duct and the core duct at least partially co-extending axially on opposite sides of the core cowl. A heat exchanger disposed within the fan duct. The heat exchanger provides for thermal communication between a fluid flowing through fan duct and a motive fluid flowing through the heat exchanger.
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公开(公告)号：US12122529B2
公开(公告)日：2024-10-22
申请号：US17381360
申请日：2021-07-21
发明人： Mirosław Czarnik , Tomasz Edward Berdowski , Paweł Zdrojewski , Łukasz Maciej Janczak , Maciej Grunwald
CPC分类号： B64D29/02 , B64D27/12 , B64D27/24 , B64D27/026 , B64F5/40
摘要： Propulsion engines and methods of accessing components within propulsor cavities of propulsion engines are disclosed. A propulsion engine includes an outer engine housing that includes a propulsor cavity located therein. The propulsor cavity is axially located between a low-pressure compressor and a fan of the propulsion engine. An electric converter is disposed within the propulsor cavity.
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公开(公告)号：US20240344486A1
公开(公告)日：2024-10-17
申请号：US18685731
申请日：2022-08-24
申请人： SAFRAN NACELLES
CPC分类号： F02K1/763 , F02K1/72 , F05D2220/323 , F05D2240/129
摘要： A thrust reverser for an aircraft propulsion unit, including a movable system with cascade vanes and an actuator allowing moving a movable system between an advanced direct thrust position and a backward thrust reversal position, the system also including an inter-cascade structure for limiting buckling of the actuator, forming a channel crossed by the actuator and delimited by a cylindrical internal surface extending along a first closed directrix curve, the fixed portion of the actuator including an end equipped with an external ring for limiting buckling of the actuator, the ring having a cylindrical external surface extending along a second closed directrix curve, the first and second closed directrix curves preferably having the same shapes and being concentric while being spaced apart from one another with the same spacing.
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公开(公告)号：US12116940B2
公开(公告)日：2024-10-15
申请号：US17215575
申请日：2021-03-29
CPC分类号： F02C9/20 , F02K3/04 , F04D27/0246 , F05D2270/023 , F05D2270/052 , F05D2270/053 , F05D2270/3011 , F05D2270/303 , F05D2270/304 , F05D2270/335 , F05D2270/71
摘要： Herein provided are methods and systems for controlling an engine having a variable geometry mechanism. A pressure ratio between a first pressure at an inlet of the engine and a predetermined reference pressure is determined. An output power for the engine is determined. The output power is adjusted based at least in part on the pressure ratio to obtain a corrected output power. A position control signal for a variable geometry mechanism of the engine is generated based on the corrected output power and the pressure ratio. The position control signal is output to a controller of the engine to control the variable geometry mechanism.
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公开(公告)号：US12116929B2
公开(公告)日：2024-10-15
申请号：US17578795
申请日：2022-01-19
CPC分类号： F02C6/08 , B64D13/06 , F02C9/00 , F02C9/18 , F02K3/04 , B64D2013/0603 , B64D2013/0607 , B64D2013/0618 , B64D2013/0648 , F05D2220/32 , F05D2220/76
摘要： A gas turbine engine includes a turbomachine, the turbomachine defining a core flow therethrough during operation. A first heat exchange assembly is in fluid communication with the turbomachine for receiving a first bleed flow from the turbomachine. A second heat exchange assembly is in fluid communication with the turbomachine for receiving a second bleed flow from the turbomachine. A first flow outlet is provided for receiving the first bleed flow from the first heat exchange assembly and providing the first bleed flow to a first aircraft flow assembly. A second flow outlet is provided for receiving the second bleed flow and providing the second bleed flow from the second heat exchange assembly to a second aircraft flow assembly.
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公开(公告)号：US12110903B2
公开(公告)日：2024-10-08
申请号：US18316656
申请日：2023-05-12
申请人： GE Avio S.r.l.
发明人： Paolo Altamura , Giulio Zagato
CPC分类号： F04D29/323 , B64C11/32 , F05D2220/32 , F05D2260/74 , F05D2260/79
摘要： A gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order; a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis; and a pitch change mechanism operable with the plurality of fan blades to control a pitch of the plurality of fan blades. The pitch change mechanism imparts a torque to each fan blade of the plurality of fan blades via first and second forces imparted in opposite directions to each fan blade of the plurality of fan blades.
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公开(公告)号：US12110841B2
公开(公告)日：2024-10-08
申请号：US17652054
申请日：2022-02-22
发明人： Junichi Akatsuka
CPC分类号： F02K1/44 , B64C5/02 , B64C30/00 , B64D33/06 , F02K1/12 , F02K1/42 , F02K1/46 , F05D2220/80 , F05D2260/96
摘要： Provided is a supersonic aircraft including: a shield that shields an engine exhaust flow discharged from a jet engine accommodated in an engine nacelle mounted on a fuselage of the aircraft to thereby reduce sonic booms due to the engine exhaust flow; and an exhaust nozzle that is provided in an exhaust port of the engine nacelle and that generates a sound source for high-frequency components at a position at which the shield is capable of shielding the high-frequency components of the engine exhaust flow, to thereby reduce jet noise having the high-frequency components, and promotes mixing of the engine exhaust flow that generates low-frequency noise components with an external air flow to thereby reduce jet noise having the low-frequency components.
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