Buffer cooling system providing gas turbine engine architecture cooling

摘要

A gas turbine engine includes a buffer cooling system having a first heat exchanger, a first passageway, a second passageway and a third passageway. The first heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The first passageway communicates a first portion of the conditioned airflow to a high pressure compressor of the gas turbine engine, the second passageway communicates a second portion of the conditioned airflow to a high pressure turbine of the gas turbine engine, and the third passageway communicates a third portion of the conditioned airflow to a low pressure turbine of the gas turbine engine.

主权项

1. A gas turbine engine, comprising:
a buffer cooling system including: a first heat exchanger that exchanges heat with a bleed airflow to provide a conditioned airflow; a first passageway that communicates a first portion of said conditioned airflow to a high pressure compressor of said gas turbine engine; a second passageway that communicates a second portion of said conditioned airflow to a high pressure turbine of said gas turbine engine; a third passageway that communicates a third portion of said conditioned airflow to a low pressure turbine of said gas turbine engine, wherein each of said first passageway, said second passageway and said third passageway is in fluid communication with a tangential onboard injection nozzle, wherein said second passageway is in fluid communication with a second nozzle assembly, and said second portion of said conditioned airflow is communicated through an opening in said second nozzle assembly to condition hardware of said high pressure turbine; and wherein said second portion of said conditioned airflow is communicated through a bearing compartment of said gas turbine engine prior to entering said second passageway.