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US 2024/0102418 A1Published application
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.