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公开(公告)号：US20080314047A1
公开(公告)日：2008-12-25
申请号：US11767993
申请日：2007-06-25
CPC分类号： F02K3/06 , B64D13/08 , F02C6/08 , F02C7/14 , F05D2260/213 , F28D2021/0021 , Y02T50/671 , Y02T50/675
摘要： Cooling systems for an aircraft are provided. In an embodiment, a system includes an engine nacelle, an engine, a bypass duct, and a heat exchanger. The engine nacelle includes an airflow inlet. The engine is housed in the engine nacelle in flow communication with the airflow inlet. The bypass duct extends between the engine nacelle and the engine is in flow communication with the airflow inlet. The bypass duct includes an outer wall and an opening formed therein. The heat exchanger is integrated with the engine and is disposed over the opening of the bypass duct outer wall between the bypass duct outer wall and the engine nacelle.
摘要翻译： 提供飞机冷却系统。 在一个实施例中，系统包括发动机机舱，发动机，旁通管道和热交换器。 发动机舱包括气流入口。 发动机容纳在与气流入口流动连通的发动机舱中。 在发动机机舱和发动机之间延伸的旁通管与气流入口流动连通。 旁通管道包括形成在其中的外壁和开口。 热交换器与发动机一体化，并且设置在旁通管外壁和发动机机舱之间的旁通管外壁的开口上。
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公开(公告)号：US07197881B2
公开(公告)日：2007-04-03
申请号：US10811272
申请日：2004-03-25
申请人： David K. Winstanley
发明人： David K. Winstanley
IPC分类号： F02C6/08
CPC分类号： F02C6/08
摘要： A duct that preferably includes a low loss inlet section is configured to include one or more flow limiting passages that extend through a portion of the low loss inlet section. The flow limiting passages are located and configured such that in the desired operating flow range of the duct, the fluid exiting the flow limiting passages has minimal effect on fluid flow into and through the duct. However, at relatively high pressure ratios, the fluid exiting the flow limiting passages will disturb the fluid entering the duct, causing mixing and shock losses, which will limit the fluid flow rate into and through the duct.
摘要翻译： 优选地包括低损失入口部分的管道构造成包括延伸穿过低损失入口部分的一部分的一个或多个流动限制通道。 流动限制通道被定位和构造成使得在管道的期望的操作流动范围内，离开流动限制通道的流体对流入和通过管道的流体流动具有最小的影响。 然而，在相对高的压力比下，离开限流通道的流体将扰乱进入管道的流体，引起混合和冲击损失，这将限制流体流入和流过管道。
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公开(公告)号：US07856824B2
公开(公告)日：2010-12-28
申请号：US11767993
申请日：2007-06-25
IPC分类号： F02C1/00
CPC分类号： F02K3/06 , B64D13/08 , F02C6/08 , F02C7/14 , F05D2260/213 , F28D2021/0021 , Y02T50/671 , Y02T50/675
摘要： Cooling systems for an aircraft are provided. In an embodiment, a system includes an engine nacelle, an engine, a bypass duct, and a heat exchanger. The engine nacelle includes an airflow inlet. The engine is housed in the engine nacelle in flow communication with the airflow inlet. The bypass duct extends between the engine nacelle and the engine is in flow communication with the airflow inlet. The bypass duct includes an outer wall and an opening formed therein. The heat exchanger is integrated with the engine and is disposed over the opening of the bypass duct outer wall between the bypass duct outer wall and the engine nacelle.
摘要翻译： 提供飞机冷却系统。 在一个实施例中，系统包括发动机机舱，发动机，旁通管道和热交换器。 发动机舱包括气流入口。 发动机容纳在与气流入口流动连通的发动机舱中。 在发动机机舱和发动机之间延伸的旁通管与气流入口流动连通。 旁通管道包括形成在其中的外壁和开口。 热交换器与发动机一体化，并且设置在旁通管外壁和发动机机舱之间的旁通管外壁的开口上。
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公开(公告)号：US5246340A
公开(公告)日：1993-09-21
申请号：US794756
申请日：1991-11-19
CPC分类号： B23P15/04 , F01D5/147 , F01D5/187 , F05D2260/201
摘要： A hollowed, internally cooled airfoil per gas turbine engines with an improved internal configuration for pronounced impingement cooling. Internal ribs extend across the hollowed interior and cooling passages through these ribs cause impingement cooling of the next-adjacent rib as well as the internal surfaces of both the pressure side and suction side of the airfoil.
摘要翻译： 每个燃气涡轮发动机采用中空的内部冷却翼型，具有改进的内部结构，用于明显的冲击冷却。 内肋延伸穿过中空的内部，并且通过这些肋的冷却通道使得下一个相邻肋的冲击冷却以及翼型的压力侧和吸入侧的内表面。
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