发明名称 |
REVERSE-FLOW CORE GAS TURBINE ENGINE WITH A PULSE DETONATION SYSTEM |
摘要 |
<p>The engine (10) includes a low spool (16) disposed aft of an air inlet (12) and a high spool (34) disposed aft of the low spool (16). An intake reverse-duct (44) is disposed radially outward of the high spool (34) and reverses direction of low pressure compressed air from the low spool (16) into a forward-flow high pressure compressor (40) of the high spool (34). A discharge reverse-manifold (48) directs flow of an exhaust gas stream (50} from a forward-flow low pressure turbine (20) into a rearward-flow direction and into at least one pulse detonation firing tube (54). An annular bypass air duct (72) directs cooling air along the engine (10) - The at least, one firing tube is positioned radially outward of the high spool (34), overlies the high spool (34) and is also positioned within the bypass air duct (72).</p> |
申请公布号 |
WO2014120115(A1) |
申请公布日期 |
2014.08.07 |
申请号 |
WO2013US23565 |
申请日期 |
2013.01.29 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
KUPRATIS, DANIEL, B.;MOON, FRANCIS, R. |
分类号 |
F02K3/02 |
主分类号 |
F02K3/02 |
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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