Thermal anti-icing system for aircraft airframe exterior surface

An aircraft, comprising:

• an airframe including a body and a plurality of wings, the body extending longitudinally along a centerline, the plurality of wings disposed to opposing lateral sides of the body, and each of the plurality of wings projecting spanwise out from the body;
• a propulsion system connected to the airframe, the propulsion system including a propulsor rotor and a turbine engine core configured to drive rotation of the propulsor rotor, and the turbine engine core comprising a core flowpath;
• and
• a thermal anti-icing system including a heat exchanger and a fluid heating circuit, the heat exchanger including a combustion products passage and a working fluid passage, the combustion products passage fluidly couplable to the core flowpath, the working fluid passage fluidly couplable to the fluid heating circuit, the fluid heating circuit extending along a region of an exterior surface of the airframe longitudinally upstream of and laterally aligned with the propulsor rotor, and the fluid heating circuit in thermal communication with material of the airframe forming the region of the exterior surface of the airframe;
• wherein the thermal anti-icing system further comprises a flow regulator configured to selectively bleed combustion products directly from the core flowpath and direct the combustion products to the combustion products passage.

An aircraft, comprising:

• a blended wing body airframe;
• a propulsion system connected to the blended wing body airframe, the propulsion system including a propulsor rotor and a turbine engine core configured to drive rotation of the propulsor rotor, and the turbine engine core comprising a combustor section and a core flowpath;
• and
• a thermal anti-icing system including a heat exchanger and a fluid heating circuit, the heat exchanger including a combustion products passage and a working fluid passage, the combustion products passage fluidly couplable to the core flowpath downstream of the combustor section, the working fluid passage fluidly couplable to the fluid heating circuit, and the fluid heating circuit extending along, and in thermal communication with material of the blended wing body airframe forming, an exterior surface of the blended wing body airframe;
• wherein the thermal anti-icing system is configured to selectively bleed combustion products directly from the core flowpath and direct the combustion products to the combustion products passage.