发明名称 |
TIP TURBINE ENGINE WITH MULTIPLE FAN AND TURBINE STAGES |
摘要 |
<p>A tip turbine engine (10) provides first and second turbines (32) rotatably driven by a combustor (30) generating a high-energy gas stream. The first turbine (32) is mounted at an outer periphery of a first fan (24a) , such that the first fan is rotatably driven by the first turbine (32a) . The second turbine (32b) is mounted at an outer periphery of a second fan (24b) , and is rotatably driven by the high-energy gas stream. In one embodiment, the first turbine (32a) rotatably drives a plurality of stages of first compressor blades (54) in an axial compressor (22) in a first rotational direction, while the second turbine (32b) rotatably drives a plurality of stages of second compressor blades (52) in the axial compressor (22) in a second rotational direction opposite the first. By rotatably driving alternating stages of compressor blades in opposite directions, the efficiency of the axial compressor (22) is increased and/or the number of stages of compressor blades can be reduced. Other variations are described in additional embodiments.</p> |
申请公布号 |
WO2006059993(A1) |
申请公布日期 |
2006.06.08 |
申请号 |
WO2004US40105 |
申请日期 |
2004.12.01 |
申请人 |
UNITED TECHNOLOGIES CORPORATION;NORRIS, JAMES W.;NORDEEN, CRAIG A.;ROBERGE, GARY |
发明人 |
NORRIS, JAMES W.;NORDEEN, CRAIG A.;ROBERGE, GARY |
分类号 |
F02C3/073;F02C3/067;F02C3/14;F02K3/068;F02K3/072 |
主分类号 |
F02C3/073 |
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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