CPC F02C 6/18 (2013.01) [F02C 7/32 (2013.01); F02C 9/18 (2013.01); F05D 2220/62 (2013.01); F05D 2260/10 (2013.01); F05D 2260/213 (2013.01); F05D 2260/232 (2013.01)] | 15 Claims |
1. A turbine engine assembly comprising:
a core engine including a core flow path where a core airflow is compressed in a main compressor section, communicated to a combustor section, mixed with fuel, and ignited to generate an exhaust gas flow that is expanded through a turbine section, wherein the turbine section is coupled to drive the main compressor section through an engine drive shaft;
a tap at a location upstream of the combustor section where a bleed airflow is drawn;
an auxiliary compressor section where a first portion of the bleed airflow is pressurized to generate a first compressed airflow;
a bleed air heat exchanger where a second portion of the bleed airflow directly from the tap is preheated;
an exhaust heat exchanger where the preheated second portion of the bleed airflow is heated by the exhaust gas flow;
a power turbine coupled to drive the auxiliary compressor section and driven by heated bleed airflow from the exhaust heat exchanger; and
an accessory system receiving pressurized airflow from the auxiliary compressor section.
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