Aircraft exhaust waste heat recovery for icing mitigation

A gas turbine engine for an aircraft, the gas turbine engine comprising:

• a thermal bus including a plumbing system having a cold leg and a hot leg;
• a cryogenic fuel source comprising hydrogen in a liquid phase and in fluid communication with the cold leg of the plumbing system;
• a compressor section;
• a combustion section configured to receive vaporized hydrogen from the plumbing system;
• a waste heat recovery (WHR) heat exchanger (HX) thermally coupled to a core airflow path downstream of a turbine section and configured to transfer heat to the plumbing system to vaporize the hydrogen prior to delivery to the combustion section, wherein the WHR HX uses a heat transfer medium to vaporize the hydrogen;
• and
• a drainage system configured to remove water resulting from melted ice on the plumbing system, the drainage system including at least one drain guide configured to direct the water resulting from the melted ice into a discharger tube.