Crossover cooling flow for multi-engine systems

A method of operating a multi-engine system in an aircraft, the method comprising:

• operating the multi-engine system in an asymmetric cruise mode during a cruise phase of flight of the aircraft, wherein the asymmetric cruise mode comprises operating a first gas turbine engine at a first power rating and a second gas turbine engine at a second power rating, wherein the first power rating is higher than the second power rating and wherein the second gas turbine engine comprises a second engine central longitudinal axis, a second compressor and a second turbine, the second compressor and the second turbine each rotating about the second engine central longitudinal axis;
• wherein in response to the multi-engine system operating in the asymmetric cruise mode, a portion of a total compressor flow of a first compressor of the first gas turbine engine is routed to a turbine component of the second turbine of the second gas turbine engine to cool the turbine component, the portion of the total compressor flow being routed through a crossover cooling network that extends from the first compressor of the first gas turbine engine to the turbine component of the second turbine of the second gas turbine engine.