COMPRESSOR BLEED AUXILIARY TURBINE

摘要

A gas turbine engine is provided having a compressor section, a combustion section, and a turbine section. The compressor section includes one or more compressors and the turbine section includes one or more turbines. The one or more compressors and the one or more turbines are each rotatable about a longitudinal centerline of the gas turbine engine. Additionally, a bleed air flowpath is provided extending between an inlet in airflow communication with the compressor section and an outlet. An auxiliary turbine is positioned in airflow communication with the bleed air flowpath for extracting energy from a flow of bleed air through the bleed air flowpath.

主权项

1. A gas turbine engine comprising:
a compressor section including one or more compressors; a combustion section located downstream of the compressor section; a turbine section located downstream of the combustion section and including one or more turbines; a bleed air flowpath extending between an inlet and an outlet, the inlet in airflow communication with the compressor section for receiving a flow of bleed air from the compressor section; and an auxiliary turbine positioned in airflow communication with the bleed air flowpath between the inlet of the bleed air flowpath and the outlet of the bleed air flowpath for extracting energy from the flow of bleed air through the bleed air flowpath.