Micro reaction turbine with integrated combustion chamber and rotor
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United States of America Patent
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Dec 18, 2012
Grant Date -
Oct 23, 2008
app pub date -
Apr 24, 2008
filing date -
Feb 28, 2003
priority date (Note) -
In Force
status (Latency Note)
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Abstract
When the compressor is a multistage compressor, each compression space includes an inlet arranged in the vicinity of the center axis and an outlet arranged in the vicinity of the outer circumference of the turbine wheel, and there is a connecting conduit between the outlet of a first compressor stage and the inlet of a second compressor stage. The connecting conduit is delimited by a first wall of the space of the first compressor stage and a second wall of the space of the second compressor stage. Each wall can be a friction disk.
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