Aircraft system with heat exchanger for environmental control system

A system for an aircraft, comprising:

• a turbine engine comprising an air source and a plurality of engine components;
• an inner housing structure housing the plurality of engine components, the inner housing structure forming an inner peripheral boundary of the air source;
• an outer housing structure spaced radially outboard of the inner housing structure, the outer housing structure forming an outer peripheral boundary of the air source;
• an air system including an air circuit and an environmental control system, the air circuit configured to direct air received from the air source to the environmental control system, wherein a circuit inlet of the air circuit is disposed along the inner peripheral boundary of the air source;
• a working fluid system comprising a fluid circuit, the working fluid system configured to lubricate and/or cool the plurality of engine components using a working fluid directed through the fluid circuit;
• and
• a heat exchanger arranged along the air circuit between the air source and the environmental control system, the heat exchanger configured to transfer heat energy between the air in the air circuit and the working fluid in the fluid circuit to heat the air and cool the working fluid.

A system for an aircraft, comprising:

• an environmental control system;
• and
• a propulsion system including an inner housing structure, an outer housing structure, a vane structure, a compressor section, a combustor section, a turbine section, a bypass flowpath, an air circuit, a working fluid system and a heat exchanger;
• the inner housing structure housing the compressor section, the combustor section and the turbine section, the inner housing structure forming an inner peripheral boundary of the bypass flowpath;
• the outer housing structure spaced radially outboard of the inner housing structure, the outer housing structure forming an outer peripheral boundary of the bypass flowpath;
• the vane structure extending radially across the bypass flowpath from the inner housing structure to the outer housing structure;
• the bypass flowpath bypassing the compressor section, the combustor section and the turbine section;
• the air circuit comprising a circuit inlet fluidly coupled to the bypass flowpath, and the air circuit configured to direct air received from the bypass flowpath through the circuit inlet to the environmental control system, wherein the circuit inlet is arranged on the vane structure;
• the working fluid system comprising a fluid circuit, and the working fluid system configured to service one or more components of the propulsion system using a liquid working fluid directed through the fluid circuit;
• and
• the heat exchanger configured to transfer heat energy between the air in the air circuit and the liquid working fluid in the fluid circuit.