Gas turbine engine having cooling systems
A gas turbine engine, including 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 cooled cooling air (CCA) system, the CCA system comprising a cold side bleed assembly and a CCA 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.
1 . A gas turbine engine, comprising:
an accessory system cooling system comprising a cooling system inlet, a duct defining a first flowpath in fluid communication with the cooling system inlet, and a heat exchanger in fluid communication with the first flowpath downstream of 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 cooled cooling air (CCA) system, the CCA system comprising a cold side bleed assembly and a CCA heat exchanger in thermal communication with the cold side bleed assembly, wherein the cold side bleed assembly defines a second flowpath having 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 CCA system further comprises a flow control valve in fluid communication with the first flowpath and the second flowpath, wherein the flow control valve is located downstream of the inlet and upstream of the CCA heat exchanger to control an airflow split between the duct defining the first flowpath of the accessory system cooling system and the second flowpath of the cold side bleed assembly,
wherein the turbomachine defines an under-cowl cavity, and wherein the CCA heat exchanger is located in the under-cowl cavity of the turbomachine.
2 . The gas turbine engine of claim 1 , further comprising a bifurcation, and wherein the cooling system inlet is located on the bifurcation.
3 . The gas turbine engine of claim 2 , wherein the cooling system inlet is located on a flowpath surface of the bifurcation.
4 . The gas turbine engine of claim 2 , wherein the cold side bleed assembly comprises a scoop at the inlet.
5 . The gas turbine engine of claim 2 , wherein the cold side bleed assembly comprises a variable geometry component at the inlet.
6 . The gas turbine engine of claim 2 , wherein the bifurcation is an upper bifurcation of the gas turbine engine.
7 . The gas turbine engine of claim 6 , wherein the gas turbine engine is a turbofan engine comprising a fan driven by the turbomachine and an outer nacelle surrounding the fan and defining a bypass passage with the turbomachine, wherein the upper bifurcation extends between the turbomachine and the outer nacelle.
8 . The gas turbine engine of claim 1 , wherein the combustion section defines a compressor discharge cavity, wherein the CCA system further comprises a hot side bleed assembly defining an inlet in fluid communication with the working gas flowpath through the compressor section, at the compressor discharge cavity, or both, wherein the hot side bleed assembly is in thermal communication with the CCA heat exchanger to cool an airflow through the hot side bleed assembly, and wherein the hot side bleed assembly is further in thermal communication with a hot component of the turbomachine to cool the hot component of the turbomachine.
9 . The gas turbine engine of claim 8 , wherein the turbine section comprises a high pressure turbine, and wherein the hot component is the high pressure turbine.
10 . The gas turbine engine of claim 8 , wherein the hot component is a rotor bore of a turbine of the turbine section, an airfoil of the turbine, a rotor bore of the compressor section, an airfoil of the compressor section, a sump within the turbine section, a turbine mid-frame, a turbine rear frame, or a combination thereof.
11 . The gas turbine engine of claim 1 , wherein the accessory system cooling system is an environmental control system.
12 . The gas turbine engine of claim 1 , wherein the inlet is configured to indirectly receive a portion of airflow from the cooling system inlet via the duct.
13 . The gas turbine engine of claim 1 , wherein the CCA heat exchanger is a first CCA heat exchanger, wherein the CCA system further comprises a second CCA heat exchanger, wherein the cold side bleed assembly comprises a first portion and a second portion arranged in parallel flow, wherein the first portion is in thermal communication with the first CCA heat exchanger and the second portion is in thermal communication with the second CCA heat exchanger.