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公开(公告)号：US06516605B1
公开(公告)日：2003-02-11
申请号：US09882649
申请日：2001-06-15
IPC分类号： F02K7075
CPC分类号： F02K9/97 , F02K7/075 , F05D2240/1281
摘要： An aerospike engine has at least one nozzle surface and a plurality of pulse detonation devices mounted to the nozzle surface in place of the more common deflagration-based combustors. Each pulse detonation device is oriented such that its combustion products are directed along the nozzle surface Incorporating pulse detonation devices into the aerospike engine produces the advantage of a more efficient thermodynamic cycle. The pulse detonation aerospike engine is also capable of operating on either air or oxidizer.
摘要翻译： Aerospike发动机具有至少一个喷嘴表面和多个安装到喷嘴表面的脉冲爆震装置，代替更常见的基于爆燃的燃烧器。 每个脉冲爆震装置被定向成使得其燃烧产物沿着喷嘴表面引导将脉冲爆震装置引入到空气喷射发动机中产生更有效的热力循环的优点。 脉冲爆震Aerospike发动机也能够在空气或氧化剂上操作。
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公开(公告)号：US06505462B2
公开(公告)日：2003-01-14
申请号：US09821274
申请日：2001-03-29
IPC分类号： F02C512
CPC分类号： F02K7/06 , F02C5/12 , F02K7/075 , F05D2250/411
摘要： A rotary valve for pulse detonation engines includes a rotor rotatively mounted in the forward end of the pulse detonation tube and a plurality of transfer plenums for receiving fuel and air arranged around the rotor and partially disposed over the forward end of the tube. The rotor has a plurality of internal flow passages formed therein which periodically align with a plurality of inlet ports formed near the forward end of the tube as the rotor rotates. Each one of the transfer plenums is aligned with a corresponding one of the inlet ports so that the flow passages will establish fluid communication between the tube and the transfer plenums when aligned with the inlet ports. Additional features include axial injection of the fuel-air mixture into the pulse detonation tube, pre-compression of the inlet flow and a drive system located outside of the primary gas path.
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3.发明授权公开(公告)号：US06751943B2
公开(公告)日：2004-06-22
申请号：US10266434
申请日：2002-10-08
IPC分类号： F02C500
CPC分类号： F03H1/00 , F02K7/02 , F02K7/06 , F05D2260/16
摘要： Flow control in pulse detonation engines is accomplished using magnetohydrodynamic principles. The pulse detonation engine includes a tube having an open forward end and an open aft end and a fuel-air inlet formed in the tube at the forward end. An igniter is disposed in the tube at a location intermediate the forward end and the aft end. A magnetohydrodynamic flow control system is located between the igniter and the fuel-air inlet for controlling detonation in the tube forward of the igniter. The magnetohydrodynamic flow control system utilizes magnetic and electric fields forward of the igniter to dissipate or at least reduce the ignition potential of the forward traveling detonation flame front.
摘要翻译： 脉冲爆震发动机中的流量控制是使用磁流体动力学原理完成的。 脉冲爆震发动机包括具有开口前端和开口后端的管和在前端处形成在管中的燃料空气入口。 点火器在前端和后端中间的位置设置在管中。 磁流体动力学流量控制系统位于点火器和燃料 - 空气入口之间，用于控制点火器前面的管中的爆炸。 磁流体动力学流量控制系统利用点火器前方的磁场和电场来消散或至少降低向前行进的爆震火焰前沿的点火电位。
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公开(公告)号：US06484492B2
公开(公告)日：2002-11-26
申请号：US09756895
申请日：2001-01-09
IPC分类号： F02C500
CPC分类号： F03H1/00 , F02K7/02 , F02K7/06 , F05D2260/16
摘要： Flow control in pulse detonation engines is accomplished using magnetohydrodynamic principles. The pulse detonation engine includes a tube having an open forward end and an open aft end and a fuel-air inlet formed in the tube at the forward end. An igniter is disposed in the tube at a location intermediate the forward end and the aft end. A magnetohydrodynamic flow control system is located between the igniter and the fuel-air inlet for controlling detonation in the tube forward of the igniter. The magnetohydrodynamic flow control system utilizes magnetic and electric fields forward of the igniter to dissipate or at least reduce the ignition potential of the forward traveling detonation flame front.
摘要翻译： 脉冲爆震发动机中的流量控制是使用磁流体动力学原理完成的。 脉冲爆震发动机包括具有开口前端和开口后端的管和在前端处形成在管中的燃料空气入口。 点火器在前端和后端中间的位置设置在管中。 磁流体动力学流量控制系统位于点火器和燃料 - 空气入口之间，用于控制点火器前面的管中的爆炸。 磁流体动力学流量控制系统利用点火器前方的磁场和电场来消散或至少降低向前行进的爆震火焰前沿的点火电位。
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