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1.发明授权Method of manufacturing heat exchanger cooling passages in aero propulsion structure 有权在航空推进结构中制造热交换器冷却通道的方法公开(公告)号：US08806747B2
公开(公告)日：2014-08-19
申请号：US12512515
申请日：2009-07-30
IPC分类号： B21D53/00
CPC分类号： B23P15/26 , B21D53/02 , B23H7/02 , B23H7/265 , B23H9/10 , B23H9/14 , F24H9/02 , Y10T29/49346 , Y10T29/4935 , Y10T29/49401 , Y10T29/49996
摘要： Methods and apparatus of an improved cooling structure having cooling passages are provided. A method includes forming pilot holes with an electrical discharge machine (EDM) drill near a heated flow surface. The pilot holes are then shaped with a wire EDM into cooling passages having a desired shape.
摘要翻译： 提供具有冷却通道的改进的冷却结构的方法和装置。 一种方法包括在加热流动表面附近用放电机（EDM）钻头形成导向孔。 导向孔然后用电线EDM成形为具有所需形状的冷却通道。
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2.发明申请METHOD OF MANUFACTURING HEAT EXCHANGER COOLING PASSAGES IN AERO PROPULSION STRUCTURE 有权在AERO推进结构中制造热交换器冷却通道的方法公开(公告)号：US20100108289A1
公开(公告)日：2010-05-06
申请号：US12512515
申请日：2009-07-30
CPC分类号： B23P15/26 , B21D53/02 , B23H7/02 , B23H7/265 , B23H9/10 , B23H9/14 , F24H9/02 , Y10T29/49346 , Y10T29/4935 , Y10T29/49401 , Y10T29/49996
摘要： Methods and apparatus of an improved cooling structure having cooling passages are provided. A method includes forming pilot holes with an electrical discharge machine (EDM) drill near a heated flow surface. The pilot holes are then shaped with a wire EDM into cooling passages having a desired shape.
摘要翻译： 提供了具有冷却通道的改进的冷却结构的方法和装置。 一种方法包括在加热流动表面附近用放电机（EDM）钻头形成导向孔。 导向孔然后用电线EDM成形为具有所需形状的冷却通道。
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公开(公告)号：US06715293B2
公开(公告)日：2004-04-06
申请号：US10112635
申请日：2002-03-28
申请人： Mark A. Sillence , Daniel P. Guinan , Dennis J. Nemecek , Costante Salvador , Henry K. Webster , Thomas B. Fortin , Sergio Rinella , Revi K. Nigam
发明人： Mark A. Sillence , Daniel P. Guinan , Dennis J. Nemecek , Costante Salvador , Henry K. Webster , Thomas B. Fortin , Sergio Rinella , Revi K. Nigam
IPC分类号： F02K714
CPC分类号： F02K7/14 , Y02T50/672
摘要： The present invention relates to a scram jet engine for use with a hypersonic vehicle. The scram jet engine has an upper boundary wall, a lower boundary wall, and a plurality of side walls defining an inner air flowpath. The walls are formed by a plurality of tubular heat exchanger panels. Each of the heat exchanger panels comprises a plurality of structural panels, each having a plurality of cooling passages, joined together. In the scram jet engine of the present invention, fuel may be used as a coolant and supplied to the cooling passage.
摘要翻译： 本发明涉及一种与超音速车辆一起使用的冲击式发动机。 冲击式喷气发动机具有上边界壁，下边界壁和限定内部空气流动路径的多个侧壁。 壁由多个管状热交换器板形成。 每个热交换器面板包括多个结构面板，每个结构面板具有连接在一起的多个冷却通道。 在本发明的冲击式发动机中，燃料可以用作冷却剂并被供应到冷却通道。
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