Abstract: A system and method for using a fuel with an engine, an airframe having an aircraft heat load, a fuel tank, and a fuel oxygen reduction unit are provided. The method includes receiving an inlet fuel flow in the fuel oxygen reduction unit for reducing an amount of oxygen in the inlet fuel flow; separating a fuel/gas mixture within the fuel oxygen reduction unit into an outlet gas flow and an outlet fuel flow exiting the fuel oxygen reduction unit; controlling a first portion of the outlet fuel flow to the engine; and controlling a second portion of the outlet fuel flow to the airframe to transfer heat between the second portion of the outlet fuel flow and the aircraft heat load.

Abstract: An engine or engine casing having an inner annular case and an outer annular case. The engine casing is formed using an additive manufacturing technique such that the inner annular case and outer annular case is formed surrounding a hollow inner annular cavity. The annular cavity includes a pin bank connecting the inner annular case and outer annular case. The pin bank improves heat transfer between the inner and outer annular case and provide structural support to the inner and outer annular case. By providing fluid flow through the annular cavity, the turbine casing can be cooled and the radius of the casing can be controlled through the regulation of fluid travelling within the annular cavity. By controlling the fluid flow though the annular cavity, the engine case may be cooled to regulate its temperature in a wide variety of operating conditions.

Abstract: An engine or engine casing having an inner annular case and an outer annular case. The engine casing is formed using an additive manufacturing technique such that the inner annular case and outer annular case is formed surrounding a hollow inner annular cavity. The annular cavity includes a pin bank connecting the inner annular case and outer annular case. The pin bank improves heat transfer between the inner and outer annular case and provide structural support to the inner and outer annular case. By providing fluid flow through the annular cavity, the turbine casing can be cooled and the radius of the casing can be controlled through the regulation of fluid travelling within the annular cavity. By controlling the fluid flow though the annular cavity, the engine case may be cooled to regulate its temperature in a wide variety of operating conditions.