发明名称 |
Reduced gain thrust control valve |
摘要 |
<p>A reduced gain thrust control valve (10) for use in a rocket engine has a housing with a fluid inlet and a piston and cylinder unit (14) for controlling a fluid output of the control valve. The fluid inlet is formed by at least one metering element (30) formed in the housing. The at least one metering element (30) has a rectangular portion (32) for producing improved control stability, a tee and slot portion (34) for controlling thrust during a start transient engine phase, and a fixed turbine bypass portion (36) for accommodating a retainer (38). The retainer (38) incorporates at least one fluid channel (54) so as to produce repeatable fixed bypass flow metering.</p> |
申请公布号 |
EP1593831(A3) |
申请公布日期 |
2009.01.21 |
申请号 |
EP20050252381 |
申请日期 |
2005.04.15 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
AVAMPATO, TIM JOSEPH;TEPPER, BETH ELLEN;BAUTISTA, ANTONY |
分类号 |
F02K9/58;F02C9/26;F16K3/24;F16K3/32;F16K31/122;G05D7/00 |
主分类号 |
F02K9/58 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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