Mixed Flow Turbocore

Abstract: A gas turbine engine is provided having a compressor section, a combustion section located downstream of the compressor section, and a turbine section located downstream of the combustion section. A structural member extends from the compressor section to the turbine section for strengthening one or more components of the gas turbine engine. The structural member also defines a flowpath extending between an inlet in airflow communication with the compressor section and an outlet in airflow communication with the turbine section. The flowpath is configured to provide bleed air from the compressor section to the turbine section to capture at least a portion of the energy in such bleed air. FIG.1

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