Back to results
US 12,031,481 B2Granted
Air bottoming cycle air cycle system source
AssigneeRtx Corporation
InventorsAlan Retersdorf, Stephen H. Taylor, Oliver V. Atassi
Life of this patent
Estimating the term…
Abstract
A turbine engine assembly includes a tap is at a location upstream of the combustor section where a bleed airflow is drawn. The bleed air is pressurized in an auxiliary compressor section, heated in an exhaust heat exchanger, and expanded through a power turbine that is coupled to drive the auxiliary compressor section.
Claims15
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.
5 more elements
A waste heat recovery system for a turbine engine, the waste heat recovery system comprising:
- a tap at a location upstream of a combustor where a bleed airflow is drawn;
- an auxiliary compressor section where the bleed airflow is compressed;
- a bleed air heat exchanger where the compressed bleed airflow is cooled by a second portion of the bleed airflow drawn from the tap;
- an exhaust heat exchanger where the second portion of the bleed airflow is heated by an exhaust gas flow;
- a power turbine coupled to drive the auxiliary compressor section and driven by heated bleed airflow;
- and
- an accessory system receiving pressurized airflow from the auxiliary compressor section.
4 more elements
A method of operating a turbine engine assembly comprising:
- tapping a bleed airflow from a location upstream of at least a portion of a main compressor section;
- compressing the bleed airflow in an auxiliary compressor section to generate a compressed bleed airflow;
- cooling the compressed bleed airflow in a bleed air heat exchanger with a second portion of bleed airflow direct from the main compressor section;
- heating the bleed airflow in an exhaust heat exchanger;
- driving the auxiliary compressor with a power turbine by expanding the heated bleed airflow through the power turbine;
- and
- supplying the compressed bleed airflow to an air cycle system after cooling in the bleed air heat exchanger.
4 more elements
Dependencies are inferred from the claim text.