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公开(公告)号：US20080179466A1
公开(公告)日：2008-07-31
申请号：US11829497
申请日：2007-07-27
CPC分类号： F02C7/04 , B64D41/00 , B64D2033/0213 , B64D2041/002 , F02C6/06 , F02C7/042 , Y02T50/44 , Y02T50/671 , Y10T137/0536
摘要： Dual flow auxiliary power unit (APU) inlets and associated systems and methods are disclosed. An inlet in accordance with one embodiment of the invention includes an entrance aperture and a divider positioned in the inlet and located to separate a first portion of the inlet from a second portion of the inlet. The first portion can be configured to couple to an engine air intake of an APU, and the second portion can be configured to direct air away from the air intake. The divider can be positioned to direct air having a first total pressure level and a first distortion level to the first portion of the inlet, and direct air having a second total pressure level and second distortion level to the second portion of the inlet. The first total pressure level can be approximately the same as or higher than the second total pressure level, or the second distortion level can be approximately the same as or higher than the first distortion level, or both.
摘要翻译： 公开了双流辅助动力单元（APU）入口及相关系统和方法。 根据本发明的一个实施例的入口包括入口孔和分隔件，其定位在入口中并且定位成将入口的第一部分与入口的第二部分分开。 第一部分可以被配置成联接到APU的发动机进气口，并且第二部分可被配置成将空气引导离开进气口。 分隔器可以定位成将具有第一总压力水平和第一失真水平的空气引导到入口的第一部分，并且具有第二总压力水平和第二失真水平的直接空气到入口的第二部分。 第一总压力水平可以大致等于或高于第二总压力水平，或者第二失真水平可以大致等于或高于第一失真水平，或两者。
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公开(公告)号：US07611093B2
公开(公告)日：2009-11-03
申请号：US11829497
申请日：2007-07-27
IPC分类号： B64D41/00
CPC分类号： F02C7/04 , B64D41/00 , B64D2033/0213 , B64D2041/002 , F02C6/06 , F02C7/042 , Y02T50/44 , Y02T50/671 , Y10T137/0536
摘要： Dual flow auxiliary power unit (APU) inlets and associated systems and methods are disclosed. An inlet in accordance with one embodiment of the invention includes an entrance aperture and a divider positioned in the inlet and located to separate a first portion of the inlet from a second portion of the inlet. The first portion can be configured to couple to an engine air intake of an APU, and the second portion can be configured to direct air away from the air intake. The divider can be positioned to direct air having a first total pressure level and a first distortion level to the first portion of the inlet, and direct air having a second total pressure level and second distortion level to the second portion of the inlet. The first total pressure level can be approximately the same as or higher than the second total pressure level, or the second distortion level can be approximately the same as or higher than the first distortion level, or both.
摘要翻译： 公开了双流辅助动力单元（APU）入口及相关系统和方法。 根据本发明的一个实施例的入口包括入口孔和分隔件，其定位在入口中并且定位成将入口的第一部分与入口的第二部分分开。 第一部分可以被配置成联接到APU的发动机进气口，并且第二部分可被配置成将空气引导离开进气口。 分隔器可以定位成将具有第一总压力水平和第一失真水平的空气引导到入口的第一部分，并且具有第二总压力水平和第二失真水平的直接空气到入口的第二部分。 第一总压力水平可以大致等于或高于第二总压力水平，或者第二失真水平可以大致等于或高于第一失真水平，或两者。
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公开(公告)号：US07344107B2
公开(公告)日：2008-03-18
申请号：US10974167
申请日：2004-10-26
IPC分类号： B64D41/00
CPC分类号： F02C7/04 , B64D41/00 , B64D2033/0213 , B64D2041/002 , F02C6/06 , F02C7/042 , Y02T50/44 , Y02T50/671 , Y10T137/0536
摘要： Dual flow auxiliary power unit (APU) inlets and associated systems and methods are disclosed. An inlet in accordance with one embodiment of the invention includes an entrance aperture and a divider positioned in the inlet and located to separate a first portion of the inlet from a second portion of the inlet. The first portion can be configured to couple to an engine air intake of an APU, and the second portion can be configured to direct air away from the air intake. The divider can be positioned to direct air having a first total pressure level and a first distortion level to the first portion of the inlet, and direct air having a second total pressure level and second distortion level to the second portion of the inlet. The first total pressure level can be approximately the same as or higher than the second total pressure level, or the second distortion level can be approximately the same as or higher than the first distortion level, or both.
摘要翻译： 公开了双流辅助动力单元（APU）入口及相关系统和方法。 根据本发明的一个实施例的入口包括入口孔和分隔件，其定位在入口中并且定位成将入口的第一部分与入口的第二部分分开。 第一部分可以被配置成联接到APU的发动机进气口，并且第二部分可被配置成将空气引导离开进气口。 分隔器可以定位成将具有第一总压力水平和第一失真水平的空气引导到入口的第一部分，并且具有第二总压力水平和第二失真水平的直接空气到入口的第二部分。 第一总压力水平可以大致等于或高于第二总压力水平，或者第二失真水平可以大致等于或高于第一失真水平，或两者。
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公开(公告)号：US20080099630A1
公开(公告)日：2008-05-01
申请号：US11553170
申请日：2006-10-26
申请人： Pradip G. Parikh , Robert H. Willie
发明人： Pradip G. Parikh , Robert H. Willie
IPC分类号： B64D33/00
CPC分类号： B64D13/00 , B64D33/08 , B64D2013/0622 , B64D2033/0226 , B64D2241/00 , Y02T50/56 , Y10T137/0536
摘要： An inlet apparatus and method for use with a cabin air compressor on a high speed, airborne mobile platform, such as a commercial or military aircraft. The apparatus includes a Pitot inlet of a desired shape that is supported outside an exterior surface of a fuselage of the aircraft by a diverter structure. The diverter structure diverts a low energy portion of a boundary layer so that the low energy portion does not enter the Pitot inlet. The Pitot inlet receives the higher energy portion of the boundary layer and channels a ram airflow to an inlet of a cabin air compressor. The apparatus provides a recovery factor (RF) of at least about 0.8 at a cabin air compressor (CAC) inlet face, which keeps the electric power required to drive the CAC within available power limits, while minimizing the drag of the inlet apparatus.
摘要翻译： 一种用于在高速，机载移动平台（如商用或军用飞机）上的机舱空气压缩机的入口装置和方法。 该装置包括一个所需形状的皮托特入口，该导入口通过分流器结构支撑在飞行器的机身的外表面外部。 分流器结构转移边界层的低能量部分，使得低能量部分不进入皮托特入口。 皮托特入口接收边界层的较高能量部分，并将冲压气流引导到机舱空气压缩机的入口。 该设备在机舱空气压缩机（CAC）入口面处提供至少约0.8的恢复因子（RF），其保持将CAC驱动到可用功率限制内所需的电力，同时最小化入口设备的阻力。
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公开(公告)号：US20100313545A1
公开(公告)日：2010-12-16
申请号：US12483424
申请日：2009-06-12
摘要： In one embodiment, a gas turbine engine exhaust nozzle comprises a housing having a length which extends along a central longitudinal axis and comprising an interior surface and an exterior surface, and a row of chevrons extending from an aft end of the housing, the chevrons having a root region and a tip, wherein at least a portion of at least one of the interior surface or the exterior surface is scalloped proximate the root region of a chevron. Other embodiments may be described.
摘要翻译： 在一个实施例中，燃气涡轮发动机排气喷嘴包括具有沿着中心纵向轴线延伸并且包括内表面和外表面的长度的壳体以及从壳体的后端延伸的一排人字形，所述人字形具有 根部区域和尖端，其中内表面或外表面中的至少一个的至少一部分在楔形物的根部区域附近是扇形的。 可以描述其他实施例。
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6.发明申请公开(公告)号：US20140202164A1
公开(公告)日：2014-07-24
申请号：US13746277
申请日：2013-01-21
IPC分类号： F02K9/97
CPC分类号： F02K1/34 , F05D2240/14
摘要： A gas turbine engine exhaust nozzle comprises a housing having an aft end that terminates in a row of chevrons. At least one surface of the housing has scalloped root regions proximate bases of adjacent chevrons. The scalloped root regions have a reduced thickness relative to the rest of the aft end.
摘要翻译： 燃气涡轮发动机排气喷嘴包括具有终止于一排人字形的后端的壳体。 壳体的至少一个表面具有靠近相邻人字形底部的扇形根部区域。 扇形根部区域相对于后端的其余部分具有减小的厚度。
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公开(公告)号：US08356468B2
公开(公告)日：2013-01-22
申请号：US12483424
申请日：2009-06-12
摘要： In one embodiment, a gas turbine engine exhaust nozzle comprises a housing having a length which extends along a central longitudinal axis and comprising an interior surface and an exterior surface, and a row of chevrons extending from an aft end of the housing, the chevrons having a root region and a tip, wherein at least a portion of at least one of the interior surface or the exterior surface is scalloped proximate the root region of a chevron. Other embodiments may be described.
摘要翻译： 在一个实施例中，燃气涡轮发动机排气喷嘴包括具有沿着中心纵向轴线延伸并且包括内表面和外表面的长度的壳体以及从壳体的后端延伸的一排人字形，所述人字形具有 根部区域和尖端，其中内表面或外表面中的至少一个的至少一部分在楔形物的根部区域附近是扇形的。 可以描述其他实施例。
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公开(公告)号：US07861968B2
公开(公告)日：2011-01-04
申请号：US11553170
申请日：2006-10-26
申请人： Pradip G. Parikh , Robert H. Willie
发明人： Pradip G. Parikh , Robert H. Willie
IPC分类号： B64D11/00
CPC分类号： B64D13/00 , B64D33/08 , B64D2013/0622 , B64D2033/0226 , B64D2241/00 , Y02T50/56 , Y10T137/0536
摘要： An inlet apparatus and method for use with a cabin air compressor on a high speed, airborne mobile platform, such as a commercial or military aircraft. The apparatus includes a Pitot inlet of a desired shape that is supported outside an exterior surface of a fuselage of the aircraft by a diverter structure. The diverter structure diverts a low energy portion of a boundary layer so that the low energy portion does not enter the Pitot inlet. The Pitot inlet receives the higher energy portion of the boundary layer and channels a ram airflow to an inlet of a cabin air compressor. The apparatus provides a recovery factor (RF) of at least about 0.8 at a cabin air compressor (CAC) inlet face, which keeps the electric power required to drive the CAC within available power limits, while minimizing the drag of the inlet apparatus.
摘要翻译： 一种用于在高速，机载移动平台（如商用或军用飞机）上的机舱空气压缩机的入口装置和方法。 该装置包括一个所需形状的皮托特入口，该导入口通过分流器结构支撑在飞行器的机身的外表面外部。 分流器结构转移边界层的低能量部分，使得低能量部分不进入皮托特入口。 皮托特入口接收边界层的较高能量部分，并将冲压气流引导到机舱空气压缩机的入口。 该设备在机舱空气压缩机（CAC）入口面处提供至少约0.8的恢复因子（RF），其保持将CAC驱动到可用功率限制内所需的电力，同时最小化入口设备的阻力。
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