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公开(公告)号：US10808618B2
公开(公告)日：2020-10-20
申请号：US15322844
申请日：2015-06-30
发明人： Kevin Richard Leamy , Benjamin Paul Breig , Michael Jay Epstein , Javier Armando Parrilla , Matthew John Hurt , Thomas Edward Brinson , Andrew James Fleming , George Eugene Wilmot, Jr.
IPC分类号： F02C7/18 , B64D13/00 , B64D13/06 , F01D13/02 , F02C6/08 , B64D13/08 , F01D17/08 , F01D17/10 , F01D25/12 , F02C9/18 , F02C7/32 , F01D17/14
摘要： Methods and devices for cooling systems (100, 700) are provided that are in fluid communication with bleed air from a jet engine compressor. The cooling systems include: a first precooler (210) receiving bleed air from the jet engine compressor; a heat exchanger (730) downstream from the first precooler (210); a cooling system compressor (220) downstream from the first precooler (210), wherein the heat exchanger (730) and the cooling system compressor (220) are in separate flow paths from the first precooler (210); a cooling system precooler (230) downstream from the cooling system compressor (220); a cooling system turbine (240) with variable guide vanes—VGT—and downstream from the cooling system precooler (230); and a discharge conduit (245) downstream from the cooling system turbine (240) and the heat exchanger (730). A bypass line (290) can also be included that bypasses the cooling system turbine (240).
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公开(公告)号：US10247100B2
公开(公告)日：2019-04-02
申请号：US14755398
申请日：2015-06-30
发明人： Kevin Richard Leamy , Benjamin Paul Breig , Michael Jay Epstein , Javier Armando Parrilla , Matthew John Hurt , Thomas Edward Brinson , Andrew James Fleming
IPC分类号： F02C1/00 , F02C7/18 , B64D13/00 , B64D13/06 , F01D13/02 , F01D17/08 , F01D17/10 , F01D25/12 , F02C6/08 , F02C9/18
摘要： Airplanes and jet engines are provided that includes an engine compressor; a combustor in flow communication with the engine compressor; an engine turbine in flow communication with the combustor to receive combustion products from the combustor; and a bleed air cooling system in fluid communication with bleed air from the engine compressor. The bleed air cooling system can include a first precooler in fluid communication with the bleed air from the engine compressor; a cooling system turbine in fluid communication with and downstream from the first precooler; and a discharge conduit from the cooling system turbine that is configured to be in fluid communication with at least one of an aircraft thermal management system and an aircraft environmental control system. Methods are also described for providing cooling fluid from a jet engine.
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公开(公告)号：US20180194479A1
公开(公告)日：2018-07-12
申请号：US15322842
申请日：2015-06-30
发明人： Kevin Richard Leamy , Benjamin Paul Breig , Michael Jay Epstein , Javier Armando Parrilla , Matthew John Hurt , Thomas Edward Brinson , Andrew James Fleming , George Eugene Wilmot
摘要： Methods and devices for cooling systems (700) are provided that are in fluid communication with bleed air from a jet engine compressor. The cooling system can include: a first precooler (210) receiving bleed air from the jet engine compressor; a heat exchanger (730) downstream from the first precooler (210); a cooling system compressor (220) downstream from the first precooler (210), wherein the heat exchanger (730) and the cooling system compressor (220) are in separate flow paths from the first precooler (210); a cooling system precooler (230) downstream from the cooling system compressor (220); a VGT cooling system turbine (240) downstream from the cooling system precooler (230); and a discharge conduit (245) downstream from the cooling system turbine (240) and the heat exchanger (730). A bypass line (290) for bypassing the turbine can also be included.
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公开(公告)号：US10815890B2
公开(公告)日：2020-10-27
申请号：US15322842
申请日：2015-06-30
发明人： Kevin Richard Leamy , Benjamin Paul Breig , Michael Jay Epstein , Javier Armando Parrilla , Matthew John Hurt , Thomas Edward Brinson , Andrew James Fleming , George Eugene Wilmot
IPC分类号： F02C7/18 , B64D13/00 , B64D13/06 , F01D13/02 , F02C6/08 , B64D13/08 , F01D17/08 , F01D17/10 , F01D25/12 , F02C9/18 , F02C7/32 , F01D17/14
摘要： Methods and devices for cooling systems (700) are provided that are in fluid communication with bleed air from a jet engine compressor. The cooling system can include: a first precooler (210) receiving bleed air from the jet engine compressor; a heat exchanger (730) downstream from the first precooler (210); a cooling system compressor (220) downstream from the first precooler (210), wherein the heat exchanger (730) and the cooling system compressor (220) are in separate flow paths from the first precooler (210); a cooling system precooler (230) downstream from the cooling system compressor (220); a VGT cooling system turbine (240) downstream from the cooling system precooler (230); and a discharge conduit (245) downstream from the cooling system turbine (240) and the heat exchanger (730). A bypass line (290) for bypassing the turbine can also be included.
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5.发明授权Systems and methods for control of an adaptive-cycle engine with power-thermal management system 有权使用电力热管理系统控制自适应循环发动机的系统和方法公开(公告)号：US09354621B2
公开(公告)日：2016-05-31
申请号：US14305063
申请日：2014-06-16
发明人： Eric Richard Westervelt , Benjamin Paul Breig , Mustafa Tekin Dokucu , Neil Richard Garrigan , William Dwight Gerstler , Javier Armando Parrilla
CPC分类号： G05B13/026 , G05B15/02 , G05D23/1917
摘要： A control system for an adaptive-power thermal management system of an aircraft having at least one adaptive cycle gas turbine engine includes a real time optimization solver that utilizes a plurality of models of systems to be controlled, the plurality of models each being defined by algorithms configured to predict changes to each system caused by current changes in input to each system. The real time optimization solver is configured to solve an open-loop optimal control problem on-line at each of a plurality of sampling times, to provide a series of optimal control actions as a solution to the open-loop optimal control problem. The real time optimization solver implements a first control action in a sequence of control actions and at a next sampling time the open-loop optimal control problem is re-posed and re-solved.
摘要翻译： 用于具有至少一个自适应循环燃气涡轮发动机的飞机的自适应功率热管理系统的控制系统包括利用要控制的多个系统模型的实时优化求解器，所述多个模型各自由算法 配置为预测由每个系统的输入的当前变化引起的每个系统的变化。 实时优化求解器被配置为在多个采样时间中的每一个在线解决开环最优控制问题，以提供作为开环最优控制问题的解决方案的一系列最佳控制动作。 实时优化求解器在控制动作序列中实现第一控制动作，并且在下一个采样时间，重新提出并解决了开环最优控制问题。
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公开(公告)号：US09777963B2
公开(公告)日：2017-10-03
申请号：US14713363
申请日：2015-05-15
发明人： Ramon Martinez , Benjamin Paul Breig , Keith Alan Joerger , Gregg Hunt Wilson , Matthew John Hunt , Donald Michael Corsmeier , Paul Charles Johnson
IPC分类号： F02C7/12 , F28D1/047 , B23P15/26 , F02C7/14 , F02C7/18 , F28F9/02 , F28D7/08 , F02K3/06 , F28D21/00
CPC分类号： F28D1/0477 , B23P15/26 , F02C7/14 , F02C7/18 , F02K3/06 , F05D2250/185 , F05D2260/213 , F28D7/082 , F28D2021/0021 , F28F9/0224 , Y02T50/671 , Y02T50/675
摘要： A method and a system for a heat exchanger assembly are provided. The heat exchanger assembly includes one or more arcuate heat exchanger segments each including an inlet header configured to extend circumferentially about a circumference of an inner surface of a fluid flow duct, and an outlet header configured to extend circumferentially about the fluid flow duct. The heat exchanger assembly also includes a first serpentine heat exchanger tube extending between the inlet header and the outlet header and including a series of flow path segments having a gradually changing direction defined by a bend radius of the tube such that a direction of flow through the serpentine heat exchanger tube reverses between the inlet and the outlet headers and a second serpentine heat exchanger tube extending between the inlet header and the outlet header, the second serpentine heat exchanger tube co-planar with the first serpentine heat exchanger tube.
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公开(公告)号：US20160153359A1
公开(公告)日：2016-06-02
申请号：US14755398
申请日：2015-06-30
发明人： Kevin Richard Leamy , Benjamin Paul Breig , Michael Jay Epstein , Javier Armando Parrilla , Matthew John Hurt , Thomas Edward Brinson , Andrew James Fleming
CPC分类号： B64D13/08 , B64D13/006 , B64D13/06 , B64D2013/0618 , B64D2013/0648 , B64D2013/0688 , F01D13/02 , F01D17/08 , F01D17/10 , F01D17/14 , F01D25/12 , F02C6/08 , F02C7/185 , F02C7/32 , F02C9/18 , F05D2220/3216 , F05D2220/323 , F05D2260/211 , F05D2260/213 , F05D2260/232 , F05D2260/606 , F05D2270/301 , F05D2270/303 , Y02T50/56 , Y02T50/675 , Y02T50/676
摘要： Airplanes and jet engines are provided that includes an engine compressor; a combustor in flow communication with the engine compressor; an engine turbine in flow communication with the combustor to receive combustion products from the combustor; and a bleed air cooling system in fluid communication with bleed air from the engine compressor. The bleed air cooling system can include a first precooler in fluid communication with the bleed air from the engine compressor; a cooling system turbine in fluid communication with and downstream from the first precooler; and a discharge conduit from the cooling system turbine that is configured to be in fluid communication with at least one of an aircraft thermal management system and an aircraft environmental control system. Methods are also described for providing cooling fluid from a jet engine.
摘要翻译： 提供飞机和喷气发动机，其包括发动机压缩机; 与发动机压缩机流动连通的燃烧器; 与所述燃烧器流动连通以从所述燃烧器接收燃烧产物的发动机涡轮机; 以及与来自发动机压缩机的排出空气流体连通的排气冷却系统。 排气冷却系统可以包括与来自发动机压缩机的排出空气流体连通的第一预冷器; 与第一预冷器相流体连通和下游的冷却系统涡轮机; 以及来自冷却系统涡轮机的排放管道，其构造成与飞机热管理系统和飞行器环境控制系统中的至少一个流体连通。 还描述了用于从喷气发动机提供冷却流体的方法。
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8.发明申请SYSTEMS AND METHODS FOR CONTROL OF AN ADAPTIVE-CYCLE ENGINE WITH POWER-THERMAL MANAGEMENT SYSTEM 有权具有功率热管理系统的自适应循环发动机控制系统和方法公开(公告)号：US20150362923A1
公开(公告)日：2015-12-17
申请号：US14305063
申请日：2014-06-16
发明人： Eric Richard Westervelt , Benjamin Paul Breig , Mustafa Tekin Dokucu , Neil Richard Garrigan , William Dwight Gerstler , Javier Armando Parrilla
CPC分类号： G05B13/026 , G05B15/02 , G05D23/1917
摘要： A control system for an adaptive-power thermal management system of an aircraft having at least one adaptive cycle gas turbine engine includes a real time optimization solver that utilizes a plurality of models of systems to be controlled, the plurality of models each being defined by algorithms configured to predict changes to each system caused by current changes in input to each system. The real time optimization solver is configured to solve an open-loop optimal control problem on-line at each of a plurality of sampling times, to provide a series of optimal control actions as a solution to the open-loop optimal control problem. The real time optimization solver implements a first control action in a sequence of control actions and at a next sampling time the open-loop optimal control problem is re-posed and re-solved.
摘要翻译： 用于具有至少一个自适应循环燃气涡轮发动机的飞机的自适应功率热管理系统的控制系统包括利用要控制的多个系统模型的实时优化求解器，所述多个模型各自由算法 配置为预测由每个系统的输入的当前变化引起的每个系统的变化。 实时优化求解器被配置为在多个采样时间中的每一个在线解决开环最优控制问题，以提供作为开环最优控制问题的解决方案的一系列最佳控制动作。 实时优化求解器在控制动作序列中实现第一控制动作，并且在下一个采样时间，重新提出并解决了开环最优控制问题。
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