US 2026/0309082 A1 · GAS TURBINE ENGINE HAVING COOLING SYSTEMS

Abstract

A gas turbine engine includes a bifurcation and a turbomachine further including an engine cooling system, the engine cooling system having: a cold side bleed assembly defining an inlet positioned to be in fluid communication with an airflow over the bifurcation, a heat exchanger in thermal communication with the cold side bleed assembly downstream of the inlet of the cold side bleed assembly, and a hot side bleed assembly defining an inlet in fluid communication with a working gas flowpath through a compressor section, at a compressor discharge cavity, or both, the hot side bleed assembly in thermal communication with the heat exchanger to cool an airflow through the hot side bleed assembly, the hot side bleed assembly further in thermal communication with a hot component of the turbomachine to cool the hot component of the turbomachine.

Claims19

Dependent claims

A gas turbine engine, comprising:

an accessory system cooling system comprising a cooling system inlet and a duct in fluid communication with the cooling system inlet;
and
a turbomachine comprising a compressor section, a combustion section, and a turbine section, the turbomachine defining a working gas flowpath and further comprising a cold side bleed assembly and a heat exchanger in thermal communication with the cold side bleed assembly, wherein the cold side bleed assembly defines an inlet in fluid communication with the duct of the accessory system cooling system at a location downstream of the cooling system inlet, wherein the turbomachine defines an under-cowl cavity, the heat exchanger disposed in the under-cowl cavity of the turbomachine, and wherein the heat exchanger comprises an air cooled oil cooler, a sump cooler, a pre-cooler, or a combination thereof.

Dependencies are inferred from the claim text.

Gas turbine engine having cooling systems

Life of this patent

Gas turbine engine having cooling systems

Life of this patent

Abstract

Claims19