Gas turbine having a single shaft bypass configuration
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United States of America Patent
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Feb 9, 2010
Grant Date -
N/A
app pub date -
May 20, 2006
filing date -
Jul 15, 2005
priority date (Note) -
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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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