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公开(公告)号：US08479718B2
公开(公告)日：2013-07-09
申请号：US13507072
申请日：2012-05-31
Applicant: Alexander Nelson Brooks , James Gallagher Daley
Inventor： Alexander Nelson Brooks , James Gallagher Daley
CPC classification number: F02B37/12 , B60W2710/0644 , B60Y2400/435 , F01N3/20 , F01N9/00 , F02B29/0412 , F02B33/40 , F02B37/013 , F02B37/18 , F02B37/20 , F02B43/10 , F02B73/00 , F02C7/26 , F02D19/024 , F02D29/06 , F02D41/0007 , F02D41/0025 , F02D41/065 , F02D41/083 , F02D41/1446 , F02M21/0206 , Y02T10/144 , Y02T10/146 , Y02T10/32
Abstract: A hydrogen fueled powerplant including an internal combustion engine that drives a motor-generator, and has a two-stage turbocharger, for an aircraft. A control system controls the operation of the motor-generator to maintain the engine at a speed selected based on controlling the engine equivalence ratio. The control system controls an afterburner, an intercooler and an aftercooler to maximize powerplant efficiency. The afterburner also adds power to the turbochargers during high-altitude restarts. The turbochargers also include motor-generators that extract excess power from the exhaust.
Abstract translation: 一种氢燃料动力装置，包括用于飞机的驱动电动发电机的内燃机，并具有两级涡轮增压器。 控制系统控制电动发电机的运行，以将发动机维持在基于控制发动机当量比所选择的速度。 控制系统控制加力燃烧器，中间冷却器和后冷器以最大限度地发挥动力装置效率。 在高空重启时，补燃器还增加了涡轮增压器的功率。 涡轮增压器还包括从排气中抽取多余动力的电动发电机。
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公开(公告)号：US20130074812A1
公开(公告)日：2013-03-28
申请号：US13507160
申请日：2012-06-08
Applicant: Alexander Nelson Brooks , James Gallagher Daley , Bart Dean Hibbs
Inventor： Alexander Nelson Brooks , James Gallagher Daley , Bart Dean Hibbs
CPC classification number: F02B43/00 , F01P2050/20 , F01P2060/02 , F01P2060/10 , F02B29/0412 , F02B29/0493 , F02C6/12 , F02C7/143 , F02C7/16 , F02C7/224 , F02M31/02 , F02M31/16 , F02M31/20 , F05D2260/205 , Y02T10/126 , Y02T10/146 , Y02T50/675
Abstract: A high-altitude aircraft powerplant including an engine, a two-stage turbocharger having an intercooler and an aftercooler, a cryogenic hydrogen fuel source, and a cooling system including a hydrogen heat exchanger. Aided by a ram-air cooler that cools a coolant to a near-ambient temperature, the heat exchanger is configured to heat the hydrogen using the coolant, and to cool the coolant to a temperature well below the ambient temperature during high-altitude flight. The intercooler and aftercooler use the sub-ambient temperature coolant, as does a separate sensor. The ram-air cooler includes a front portion and a rear portion. The cooling system includes three cooling loops which respectively incorporate only the front portion, only the rear portion, and both portions of the ram-air cooler.
Abstract translation: 包括发动机的高空飞机动力装置，具有中间冷却器和后冷器的两级涡轮增压器，低温氢燃料源和包括氢热交换器的冷却系统。 在冷却剂冷却至接近环境温度的冲压空气冷却器的帮助下，热交换器被配置为使用冷却剂加热氢气，并且在高空飞行期间将冷却剂冷却至远低于环境温度的温度。 中间冷却器和后冷却器与单独的传感器一样使用次环境温度的冷却液。 冲压空气冷却器包括前部和后部。 冷却系统包括三个冷却回路，其仅分别仅包括前部，后部和压缩空气冷却器的两个部分。
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公开(公告)号：US08196862B2
公开(公告)日：2012-06-12
申请号：US12586631
申请日：2009-09-23
Applicant: Alexander Nelson Brooks , James Gallagher Daley , Bart Dean Hibbs
Inventor： Alexander Nelson Brooks , James Gallagher Daley , Bart Dean Hibbs
IPC: B64D27/00
CPC classification number: F02B43/00 , F01P2050/20 , F01P2060/02 , F01P2060/10 , F02B29/0412 , F02B29/0493 , F02C6/12 , F02C7/143 , F02C7/16 , F02C7/224 , F02M31/02 , F02M31/16 , F02M31/20 , F05D2260/205 , Y02T10/126 , Y02T10/146 , Y02T50/675
Abstract: A high-altitude aircraft powerplant including an engine, a two-stage turbocharger having an intercooler and an aftercooler, a cryogenic hydrogen fuel source, and a cooling system including a hydrogen heat exchanger. Aided by a ram-air cooler that cools a coolant to a near-ambient temperature, the heat exchanger is configured to heat the hydrogen using the coolant, and to cool the coolant to a temperature well below the ambient temperature during high-altitude flight. The intercooler and aftercooler use the sub-ambient temperature coolant, as does a separate sensor. The ram-air cooler includes a front portion and a rear portion. The cooling system includes three cooling loops which respectively incorporate only the front portion, only the rear portion, and both portions of the ram-air cooler.
Abstract translation: 包括发动机的高空飞机动力装置，具有中间冷却器和后冷器的两级涡轮增压器，低温氢燃料源和包括氢热交换器的冷却系统。 在冷却剂冷却至接近环境温度的冲压空气冷却器的帮助下，热交换器被配置为使用冷却剂加热氢气，并且在高空飞行期间将冷却剂冷却至远低于环境温度的温度。 中间冷却器和后冷却器与单独的传感器一样使用次环境温度的冷却液。 冲压空气冷却器包括前部和后部。 冷却系统包括三个冷却回路，其仅分别仅包括前部，后部和压缩空气冷却器的两个部分。
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Patent Agency Ranking
公开(公告)号：US20120247122A1
公开(公告)日：2012-10-04
申请号：US13507072
申请日：2012-05-31
Applicant: Alexander Nelson Brooks , James Gallagher Daley
Inventor： Alexander Nelson Brooks , James Gallagher Daley
IPC: F02C9/00
CPC classification number: F02B37/12 , B60W2710/0644 , B60Y2400/435 , F01N3/20 , F01N9/00 , F02B29/0412 , F02B33/40 , F02B37/013 , F02B37/18 , F02B37/20 , F02B43/10 , F02B73/00 , F02C7/26 , F02D19/024 , F02D29/06 , F02D41/0007 , F02D41/0025 , F02D41/065 , F02D41/083 , F02D41/1446 , F02M21/0206 , Y02T10/144 , Y02T10/146 , Y02T10/32
Abstract: A hydrogen fueled powerplant including an internal combustion engine that drives a motor-generator, and has a two-stage turbocharger, for an aircraft. A control system controls the operation of the motor-generator to maintain the engine at a speed selected based on controlling the engine equivalence ratio. The control system controls an afterburner, an intercooler and an aftercooler to maximize powerplant efficiency. The afterburner also adds power to the turbochargers during high-altitude restarts. The turbochargers also include motor-generators that extract excess power from the exhaust.
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公开(公告)号：US20100192890A1
公开(公告)日：2010-08-05
申请号：US12586631
申请日：2009-09-23
Applicant: Alexander Nelson Brooks , James Gallagher Daley , Bart Dean Hibbs
Inventor： Alexander Nelson Brooks , James Gallagher Daley , Bart Dean Hibbs
CPC classification number: F02B43/00 , F01P2050/20 , F01P2060/02 , F01P2060/10 , F02B29/0412 , F02B29/0493 , F02C6/12 , F02C7/143 , F02C7/16 , F02C7/224 , F02M31/02 , F02M31/16 , F02M31/20 , F05D2260/205 , Y02T10/126 , Y02T10/146 , Y02T50/675
Abstract: A high-altitude aircraft powerplant including an engine, a two-stage turbocharger having an intercooler and an aftercooler, a cryogenic hydrogen fuel source, and a cooling system including a hydrogen heat exchanger. Aided by a ram-air cooler that cools a coolant to a near-ambient temperature, the heat exchanger is configured to heat the hydrogen using the coolant, and to cool the coolant to a temperature well below the ambient temperature during high-altitude flight. The intercooler and aftercooler use the sub-ambient temperature coolant, as does a separate sensor. The ram-air cooler includes a front portion and a rear portion. The cooling system includes three cooling loops which respectively incorporate only the front portion, only the rear portion, and both portions of the ram-air cooler.
Abstract translation: 包括发动机的高空飞机动力装置，具有中间冷却器和后冷器的两级涡轮增压器，低温氢燃料源和包括氢热交换器的冷却系统。 在冷却剂冷却至接近环境温度的冲压空气冷却器的帮助下，热交换器被配置为使用冷却剂加热氢气，并且在高空飞行期间将冷却剂冷却至远低于环境温度的温度。 中间冷却器和后冷却器与单独的传感器一样使用次环境温度的冷却液。 冲压空气冷却器包括前部和后部。 冷却系统包括三个冷却回路，其仅分别仅包括前部，后部和压缩空气冷却器的两个部分。
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公开(公告)号：US20100100300A1
公开(公告)日：2010-04-22
申请号：US12586627
申请日：2009-09-23
Applicant: Alexander Nelson Brooks , James Gallagher Daley
Inventor： Alexander Nelson Brooks , James Gallagher Daley
CPC classification number: F02B37/12 , B60W2710/0644 , B60Y2400/435 , F01N3/20 , F01N9/00 , F02B29/0412 , F02B33/40 , F02B37/013 , F02B37/18 , F02B37/20 , F02B43/10 , F02B73/00 , F02C7/26 , F02D19/024 , F02D29/06 , F02D41/0007 , F02D41/0025 , F02D41/065 , F02D41/083 , F02D41/1446 , F02M21/0206 , Y02T10/144 , Y02T10/146 , Y02T10/32
Abstract: A hydrogen fueled powerplant including an internal combustion engine that drives a motor-generator, and has a two-stage turbocharger, for an aircraft. A control system controls the operation of the motor-generator to maintain the engine at a speed selected based on controlling the engine equivalence ratio. The control system controls an afterburner, an intercooler and an aftercooler to maximize powerplant efficiency. The afterburner also adds power to the turbochargers during high-altitude restarts. The turbochargers also include motor-generators that extract excess power from the exhaust.
Abstract translation: 一种氢燃料动力装置，包括用于飞机的驱动电动发电机的内燃机，并具有两级涡轮增压器。 控制系统控制电动发电机的运行，以将发动机维持在基于控制发动机当量比所选择的速度。 控制系统控制加力燃烧器，中间冷却器和后冷器以最大限度地发挥动力装置效率。 在高空重启时，补燃器还增加了涡轮增压器的功率。 涡轮增压器还包括从排气中抽取多余动力的电动发电机。
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公开(公告)号：US08200413B2
公开(公告)日：2012-06-12
申请号：US12586627
申请日：2009-09-23
Applicant: Alexander Nelson Brooks , James Gallagher Daley
Inventor： Alexander Nelson Brooks , James Gallagher Daley
IPC: F02D29/06
CPC classification number: F02B37/12 , B60W2710/0644 , B60Y2400/435 , F01N3/20 , F01N9/00 , F02B29/0412 , F02B33/40 , F02B37/013 , F02B37/18 , F02B37/20 , F02B43/10 , F02B73/00 , F02C7/26 , F02D19/024 , F02D29/06 , F02D41/0007 , F02D41/0025 , F02D41/065 , F02D41/083 , F02D41/1446 , F02M21/0206 , Y02T10/144 , Y02T10/146 , Y02T10/32
Abstract: A hydrogen fueled powerplant including an internal combustion engine that drives a motor-generator, and has a two-stage turbocharger, for an aircraft. A control system controls the operation of the motor-generator to maintain the engine at a speed selected based on controlling the engine equivalence ratio. The control system controls an afterburner, an intercooler and an aftercooler to maximize powerplant efficiency. The afterburner also adds power to the turbochargers during high-altitude restarts. The turbochargers also include motor-generators that extract excess power from the exhaust.
Abstract translation: 一种氢燃料动力装置，包括用于飞机的驱动电动发电机的内燃机，并具有两级涡轮增压器。 控制系统控制电动发电机的运行，以将发动机维持在基于控制发动机当量比所选择的速度。 控制系统控制加力燃烧器，中间冷却器和后冷器以最大限度地发挥动力装置效率。 在高空重启时，补燃器还增加了涡轮增压器的功率。 涡轮增压器还包括从排气中抽取多余动力的电动发电机。
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公开(公告)号：US08490917B2
公开(公告)日：2013-07-23
申请号：US13507160
申请日：2012-06-08
Applicant: Alexander Nelson Brooks , James Gallagher Daley , Bart Dean Hibbs
Inventor： Alexander Nelson Brooks , James Gallagher Daley , Bart Dean Hibbs
IPC: B64D27/00
CPC classification number: F02B43/00 , F01P2050/20 , F01P2060/02 , F01P2060/10 , F02B29/0412 , F02B29/0493 , F02C6/12 , F02C7/143 , F02C7/16 , F02C7/224 , F02M31/02 , F02M31/16 , F02M31/20 , F05D2260/205 , Y02T10/126 , Y02T10/146 , Y02T50/675
Abstract: A high-altitude aircraft powerplant including an engine, a two-stage turbocharger having an intercooler and an aftercooler, a cryogenic hydrogen fuel source, and a cooling system including a hydrogen heat exchanger. Aided by a ram-air cooler that cools a coolant to a near-ambient temperature, the heat exchanger is configured to heat the hydrogen using the coolant, and to cool the coolant to a temperature well below the ambient temperature during high-altitude flight. The intercooler and aftercooler use the sub-ambient temperature coolant, as does a separate sensor. The ram-air cooler includes a front portion and a rear portion. The cooling system includes three cooling loops which respectively incorporate only the front portion, only the rear portion, and both portions of the ram-air cooler.
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