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公开(公告)号：US20070101721A1
公开(公告)日：2007-05-10
申请号：US11269700
申请日：2005-11-09
Applicant: Kevin Dooley , Nashed Youssef
Inventor： Kevin Dooley , Nashed Youssef
IPC: F03G7/00
Abstract: The system is used for taxiing an aircraft and comprises at least one multi-spool gas turbine engine, the engine having an electrical motor in a torque-driving engagement with a low pressure spool of the engine. The low pressure spool has a propulsor connected thereon to generate thrust when rotated. A controller is connected to the electrical motor and an electrical power source to control an amount of electrical power provided from the power source to the electrical motor so as to drive the propulsor and cause at least a major portion of the thrust to be generated by the propulsor for moving the aircraft during taxiing.
Abstract translation: 该系统用于滑行飞行器并且包括至少一个多线轴燃气涡轮发动机，该发动机具有与发动机的低压阀芯的扭矩驱动接合的电动机。 低压阀芯具有连接在其上的推进器，以在旋转时产生推力。 控制器连接到电动机和电源，以控制从电源向电动机提供的电力的量，以便驱动推进器并使至少主要部分的推力由 推进者在滑行期间移动飞机。
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公开(公告)号：US06488469B1
公开(公告)日：2002-12-03
申请号：US09680281
申请日：2000-10-06
Applicant: Nashed Youssef , Gary Weir
Inventor： Nashed Youssef , Gary Weir
IPC: F01D106
CPC classification number: F04D29/441 , F02C3/08 , F04D17/06 , F04D17/12 , F04D17/122 , F05D2240/302 , Y02T50/671 , Y02T50/673
Abstract: A two stage compressor for a gas turbine engine with a mixed flow first stage, a centrifugal second stage, and an intermediate duct. The mixed flow stage has a mixed rotor rotatable about the central compressor axis with a circumferential array of mixed flow blades between the mixed flow hub and an associated mixed flow shroud. The downstream centrifugal stage has a centrifugal rotor rotatable about the same compressor axis. The centrifugal rotor has a circumferential array of radially extending centrifugal flow blades between the centrifugal flow hub and an associated centrifugal flow shroud. An intermediate duct has an inner duct wall defining an axially curvilinear transition surface of revolution between an outlet end of the mixed flow hub and an inlet end of the centrifugal flow hub and an outer duct wall defining an axially curvilinear transition surface of revolution between an outlet end of the mixed flow shroud and an inlet end of the centrifugal flow shroud. Preferably, the intermediate duct has a median inlet radius greater than an intermediate duct median outlet radius whereby air flow from the mixed rotor is directed radially inwardly and axially rearwardly toward the centrifugal rotor.
Abstract translation: 一种用于具有混合流量第一级，离心式第二级和中间管道的燃气轮机的双级压缩机。 混合流动台具有可围绕中心压缩机轴线旋转的混合转子，在混合流动毂和相关联的混合流动护罩之间具有周向阵列的混合流动叶片。 下游离心级具有绕同一压缩机轴线旋转的离心转子。 离心转子在离心流动毂和相关的离心流动护罩之间具有径向延伸的离心流动叶片的圆周阵列。 中间管道具有限定在混合流动轮毂的出口端和离心流动轮毂的入口端之间的旋转的轴向曲线过渡表面的内部管道壁，以及限定出口之间的旋转的轴向曲线过渡表面的外部管道壁 混合流动护罩的末端和离心流动护罩的入口端。 优选地，中间管道具有大于中间管道中间出口半径的中间入口半径，由此来自混合转子的空气流动径向向内并且朝向离心转子轴向向后。
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Patent Agency Ranking
公开(公告)号：US08181442B2
公开(公告)日：2012-05-22
申请号：US12114962
申请日：2008-05-05
Applicant: Nashed Youssef
Inventor： Nashed Youssef
IPC: F02K3/02
CPC classification number: F02C3/113 , F02C7/36 , F02K3/06 , F05D2260/4031
Abstract: A gas turbine aircraft engine with power variability is provided. The gas turbine aircraft engine comprises a compressor and a turbine mounted on a common shaft, and, a continuously variable transmission coupled to the shaft for transmitting power to a propulsion load.
Abstract translation: 提供了具有功率变化性的燃气轮机飞机发动机。 燃气涡轮机飞机发动机包括安装在公共轴上的压缩机和涡轮机，以及联接到轴的无级变速器，用于将动力传递到推进负载。
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公开(公告)号：US20090272121A1
公开(公告)日：2009-11-05
申请号：US12114962
申请日：2008-05-05
Applicant: Nashed Youssef
Inventor： Nashed Youssef
IPC: F02C6/04
CPC classification number: F02C3/113 , F02C7/36 , F02K3/06 , F05D2260/4031
Abstract: A gas turbine aircraft engine with power variability is provided. The gas turbine aircraft engine comprises a compressor and a turbine mounted on a common shaft, and, a continuously variable transmission coupled to the shaft for transmitting power to a propulsion load.
Abstract translation: 提供了具有功率变化性的燃气轮机飞机发动机。 燃气涡轮机飞机发动机包括安装在公共轴上的压缩机和涡轮机，以及联接到轴的无级变速器，用于将动力传递到推进负载。
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公开(公告)号：US07802757B2
公开(公告)日：2010-09-28
申请号：US11269700
申请日：2005-11-09
Applicant: Kevin Allan Dooley , Nashed Youssef
Inventor： Kevin Allan Dooley , Nashed Youssef
Abstract: The system is used for taxiing an aircraft and comprises at least one multi-spool gas turbine engine, the engine having an electrical motor in a torque-driving engagement with a low pressure spool of the engine. The low pressure spool has a propulsor connected thereon to generate thrust when rotated. A controller is connected to the electrical motor and an electrical power source to control an amount of electrical power provided from the power source to the electrical motor so as to drive the propulsor and cause at least a major portion of the thrust to be generated by the propulsor for moving the aircraft during taxiing.
Abstract translation: 该系统用于滑行飞行器并且包括至少一个多线轴燃气涡轮发动机，该发动机具有与发动机的低压阀芯的扭矩驱动接合的电动机。 低压阀芯具有连接在其上的推进器，以在旋转时产生推力。 控制器连接到电动机和电源，以控制从电源向电动机提供的电力的量，以便驱动推进器并使至少主要部分的推力由 推进者在滑行期间移动飞机。
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公开(公告)号：US07540450B2
公开(公告)日：2009-06-02
申请号：US10892125
申请日：2004-07-16
Applicant: Joseph Horace Brand , Kevin Dooley , Michael Dowhan , Nashed Youssef , Richard Harvey , William Savage
Inventor： Joseph Horace Brand , Kevin Dooley , Michael Dowhan , Nashed Youssef , Richard Harvey , William Savage
IPC: B64D27/00
Abstract: An aircraft propulsion system comprises a power plant driving a number of outboard propulsion units to propel a fixed wing aircraft.
Abstract translation: 飞机推进系统包括驱动多个外侧推进单元以驱动固定翼飞机的发电厂。
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公开(公告)号：US20060011780A1
公开(公告)日：2006-01-19
申请号：US10892125
申请日：2004-07-16
Applicant: Joseph Brand , Kevin Dooley , Michael Dowhan , Nashed Youssef , Richard Harvey , William Savage
Inventor： Joseph Brand , Kevin Dooley , Michael Dowhan , Nashed Youssef , Richard Harvey , William Savage
Abstract: An aircraft propulsion system comprises a power plant driving a number of outboard propulsion units to propel a fixed wing aircraft.
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