Power plants – Reaction motor – Air passage bypasses combustion chamber
Reexamination Certificate
2006-05-20
2010-02-09
Cuff, Michael (Department: 3741)
Power plants
Reaction motor
Air passage bypasses combustion chamber
C060S226100, C060S204000
Reexamination Certificate
active
07658063
ABSTRACT:
A gas turbine engine used in an aircraft includes a fan to provide a bypass flow through the engine. The fan delivers some airflow to the compressor for compression, and a fuel is mixed with the compressed air and delivered to a turbine to drive the engine and compressor and fan. The fan also delivers airflow to a central bypass passage located inward of the compressor. Guide vanes both upstream and downstream of the combustor each with cooling air passages therein, pass the bypass airflow from the inner bypass passage into an outer bypass passage located outward of the combustor and the turbine. The bypass flow through the guide vanes also cool the guide vanes and pass over and around the combustor to cool the combustor. The bypass airflow exits the engine at a location outward of the hot gas flow from the turbine. In an alternative embodiment, an inner bypass passage located inward of the central bypass passage also carries bypass airflow from the fan and through the engine to be mixed with the hot gas flow and the outward bypass flow.
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Cuff Michael
Florida Turbine Technologies, Inc.
Ryznic John
Wongwian Phutthiwat
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