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公开(公告)号：US20170369180A1
公开(公告)日：2017-12-28
申请号：US15190931
申请日：2016-06-23
发明人： Anthony C. Jones , Behzad Hagshenas
CPC分类号： B64D41/00 , B64C13/38 , B64D2221/00 , F01D15/08 , F01D15/10 , F02C6/00 , F02C7/262 , F02C7/277 , F02C9/42 , F05D2220/323 , F05D2220/50 , Y02T50/44
摘要： An aircraft system includes a component configured to operate with a minimum power demand. The aircraft system also includes an auxiliary power unit including an engine. The auxiliary power unit is configured to power the component and to operate the engine in a plurality of operating modes including a power mode and a standby mode. The auxiliary power unit generates a first power output at least equal to the minimum power demand during the power mode. The auxiliary power unit generates a second power output less than the minimum power demand during the standby mode.
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公开(公告)号：US11835000B2
公开(公告)日：2023-12-05
申请号：US14972289
申请日：2015-12-17
发明人： Victor Pascu , Anthony C. Jones
CPC分类号： F02C9/18 , F01D17/145 , F02C6/08 , F05D2220/323 , F05D2240/128 , F05D2240/35 , F05D2260/232 , F05D2270/101
摘要： Methods and systems for a gas turbine engine comprising a modulated bleed valve are provided. The gas turbine engine may comprise a turbine nozzle coupled to a controller, a modulated bleed valve in communication with the controller, and a tangible, non-transitory memory providing instructions to the controller to perform operations. The operations may include receiving parameter values from the parameter sensor at various times, determining desired bleed airflows to flow through the modulated bleed valve at various times, and/or commanding the modulated bleed valve to assume an open configuration or a closed configuration at various times. The modulated bleed valve may be configured to allow bleed airflow to bypass a nozzle choke area of the turbine nozzle and join a nozzle airflow.
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3.发明申请公开(公告)号：US20160356280A1
公开(公告)日：2016-12-08
申请号：US14731047
申请日：2015-06-04
发明人： Victor Pascu , Anthony C. Jones
CPC分类号： F04D27/004 , F02C9/16 , F02C9/28 , F04D17/10 , F05D2220/50 , F05D2270/03 , F05D2270/061 , F05D2270/07 , F05D2270/112 , F05D2270/20 , F05D2270/303 , F05D2270/304 , F05D2270/313
摘要： Systems and methods for controlling an auxiliary power unit (APU) are provided. The systems and methods may comprise detecting an operating condition of the APU, determining an optimal APU frequency in response to the operating condition, and setting an angular velocity of the APU to the optimal APU frequency.
摘要翻译： 提供了用于控制辅助电源单元（APU）的系统和方法。 系统和方法可以包括检测APU的操作状态，响应于操作条件确定最佳APU频率，并将APU的角速度设置为最佳APU频率。
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公开(公告)号：US20160001890A1
公开(公告)日：2016-01-07
申请号：US14771431
申请日：2014-03-03
CPC分类号： B64D33/06 , B64D41/00 , B64D2041/002 , F01D25/30 , F02C7/24 , F02C7/32 , F05D2220/50 , F05D2260/96 , Y02T50/44
摘要： An exhaust system for an APU in a gas turbine engine aircraft having a tail cone in which exhaust noise is reduced. An APU exhaust liner is attached to the APU and extending to an oval cutout at the tail cone The liner has a first constant cross section from the APU to a point proximate the tail cone, and a second, increasing cross section from the point proximate the tail cone to the liner cutout. The liner is turned toward the side of the tail. The liner cutout is further enlarged with at least one larger cutout.
摘要翻译： 一种用于燃气涡轮发动机飞行器中的APU的排气系统，其具有减少排气噪声的尾锥。 APU排气衬套连接到APU并延伸到尾锥处的椭圆形切口。衬套具有从APU到靠近尾锥的点的第一恒定横截面，以及从接近尾部点的第二个增加的横截面 尾锥到衬里切口。 衬里转向尾部侧面。 衬套切口进一步放大至少一个更大的切口。
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公开(公告)号：US09845806B2
公开(公告)日：2017-12-19
申请号：US14731047
申请日：2015-06-04
发明人： Victor Pascu , Anthony C. Jones
CPC分类号： F04D27/004 , F02C9/16 , F02C9/28 , F04D17/10 , F05D2220/50 , F05D2270/03 , F05D2270/061 , F05D2270/07 , F05D2270/112 , F05D2270/20 , F05D2270/303 , F05D2270/304 , F05D2270/313
摘要： Systems and methods for controlling an auxiliary power unit (APU) are provided. The systems and methods may comprise detecting an operating condition of the APU, determining an optimal APU frequency in response to the operating condition, and setting an angular velocity of the APU to the optimal APU frequency.
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公开(公告)号：US20160025005A1
公开(公告)日：2016-01-28
申请号：US14774933
申请日：2014-03-26
CPC分类号： F02C7/04 , B64D33/02 , B64D2033/0273 , F02C3/04 , F02C7/06 , F05D2220/323 , F05D2250/51 , F05D2250/80 , F05D2250/82
摘要： A gas turbine engine has a nose cone with a nose cone upstream end and an inlet housing including a plurality of separate flow paths at a housing upstream end which is downstream of the nose cone upstream end. The inlet housing includes a mixing portion downstream of the housing upstream end which mixes airflow from the separate flow paths, such that the airflow is generally around 360 degrees of a rotational axis of the gas turbine engine. A rotor and a turbine drive a shaft to drive the rotor with the shaft including a bearing mounted at a location downstream of the nose cone upstream end.
摘要翻译： 燃气涡轮发动机具有鼻锥体，其具有鼻锥上游端，并且入口壳体在壳体上游端处包括多个分离的流动路径，其在鼻锥上游端的下游。 入口壳体包括在壳体上游端下游的混合部分，其混合来自分离的流动路径的气流，使得气流通常大约为燃气涡轮发动机的旋转轴线的360度。 转子和涡轮机驱动轴以驱动转子，轴包括安装在鼻锥上游端下游位置的轴承。
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公开(公告)号：US20210131352A1
公开(公告)日：2021-05-06
申请号：US14972289
申请日：2015-12-17
发明人： Victor Pascu , Anthony C. Jones
摘要： Methods and systems for a gas turbine engine comprising a modulated bleed valve are provided. The gas turbine engine may comprise a turbine nozzle coupled to a controller, a modulated bleed valve in communication with the controller, and a tangible, non-transitory memory providing instructions to the controller to perform operations. The operations may include receiving parameter values from the parameter sensor at various times, determining desired bleed airflows to flow through the modulated bleed valve at various times, and/or commanding the modulated bleed valve to assume an open configuration or a closed configuration at various times. The modulated bleed valve may be configured to allow bleed airflow to bypass a nozzle choke area of the turbine nozzle and join a nozzle airflow.
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公开(公告)号：US09540114B2
公开(公告)日：2017-01-10
申请号：US14771431
申请日：2014-03-03
CPC分类号： B64D33/06 , B64D41/00 , B64D2041/002 , F01D25/30 , F02C7/24 , F02C7/32 , F05D2220/50 , F05D2260/96 , Y02T50/44
摘要： An exhaust system for an APU in a gas turbine engine aircraft having a tail cone in which exhaust noise is reduced. An APU exhaust liner is attached to the APU and extending to an oval cutout at the tail cone The liner has a first constant cross section from the APU to a point proximate the tail cone, and a second, increasing cross section from the point proximate the tail cone to the liner cutout. The liner is turned toward the side of the tail. The liner cutout is further enlarged with at least one larger cutout.
摘要翻译： 一种用于燃气涡轮发动机飞行器中的APU的排气系统，其具有减少排气噪声的尾锥。 APU排气衬套连接到APU并延伸到尾锥处的椭圆形切口。衬套具有从APU到靠近尾锥的点的第一恒定横截面，以及从接近尾部的点增加的第二截面 尾锥到衬里切口。 衬里转向尾部侧面。 衬套切口进一步放大至少一个更大的切口。
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公开(公告)号：US20160001892A1
公开(公告)日：2016-01-07
申请号：US14769316
申请日：2014-01-27
发明人： Gordon F. Jewess , Anthony C. Jones
CPC分类号： B64D41/00 , B64D2041/002 , F01D25/28 , F02C7/20 , F05D2220/50 , F16M13/02
摘要： An auxiliary power unit bracket, according to an exemplary aspect of the present disclosure includes, among other things, a gearbox mounting face and a compartment mounting face, the gearbox mounting face configured to attach to an auxiliary power unit gearbox below a sump level line, the compartment mounting face configured to attach to a portion of an auxiliary power unit compartment above the sump level line.
摘要翻译： 根据本公开的示例性方面的辅助动力单元支架包括齿轮箱安装面和舱室安装面，其中齿轮箱安装面被配置为附接到在贮槽水平线下方的辅助动力单元齿轮箱， 所述隔间安装面被配置为附接到所述贮槽水平线上方的辅助动力单元隔室的一部分。
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公开(公告)号：US20140208714A1
公开(公告)日：2014-07-31
申请号：US13719706
申请日：2012-12-19
发明人： Anthony C. Jones , Charles Brian Travelbee , Patrick M. Lydon , Eric J. Alexander , Nagamany Thayalakhandan
CPC分类号： F02K3/02 , B64C39/02 , B64C2201/048 , B64D27/20 , B64D33/02 , B64D33/08 , B64D2033/0273 , F02C7/18 , F02C9/18 , F02K1/822 , F42B15/10 , Y02T50/675
摘要： A gas turbine engine has an inlet duct, which is configured to communicate with an inlet to a compressor. The inlet duct is further configured to communicate air outwardly of an outer casing of the gas turbine engine, and to pass the air along an axial length of the gas turbine engine to cool a component associated with the gas turbine engine.
摘要翻译： 燃气涡轮发动机具有入口管道，其构造成与压缩机的入口连通。 入口管道进一步构造成将空气向外传送到燃气涡轮发动机的外壳，并沿着燃气涡轮发动机的轴向长度通过空气以冷却与燃气涡轮发动机相关联的部件。
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