A method of tracking an engine cooler in an aircraft includes recording an orientation of the engine cooler as orientation N. Prognostic health management data of the aircraft is tracked. A maintenance check of the aircraft is performed based on the tracked prognostic health management data. Whether to rotate an orientation of the engine cooler is determined with an aircraft maintenance database based on the tracked prognostic health management data of the aircraft. A recommendation is provided by the aircraft maintenance database as to whether to rotate the engine cooler. The orientation of the engine cooler is recorded as orientation N+1.

A heat exchanger which may be used in an engine, such as a vehicle engine for an aircraft or orbital launch vehicle. is provided. The heat exchanger may be configured as generally drum-shaped with a multitude of spiral sections, each containing numerous small diameter tubes. The spiral sections may spiral inside one another. The heat exchanger may include a support structure with a plurality of mutually axially spaced hoop supports, and may incorporate an intermediate header. The heat exchanger may incorporate recycling of methanol or other antifreeze used to prevent blocking of the heat exchanger due to frost or ice formation.

Disclosed is a heat exchanger for a thermal management system of an aircraft assembly, the heat exchanger including: a core including a first side with a first core inlet, a second side opposing the first side and includes a first core outlet, the first core inlet is in fluid communication with the first core outlet, a third side having a second core inlet and a fourth side opposing the third side and includes a second core outlet, the second core inlet is in fluid communication with the second core outlet, and a screen wrapped around the core, the screen covering the first core inlet and the first core outlet, and a plurality of rollers disposed between the core and the screen for movably securing the screen to the core, the rollers engaging the screen and movement of at least one of the rollers moves the screen about the core.

Disclosed is a heat exchanger for a thermal management system of an aircraft assembly, the heat exchanger including: a core including a first side with a first core inlet, a second side opposing the first side and includes a first core outlet, the first core inlet is in fluid communication with the first core outlet, a third side having a second core inlet and a fourth side opposing the third side and includes a second core outlet, the second core inlet is in fluid communication with the second core outlet, and a screen wrapped around the core, the screen covering the first core inlet and the first core outlet, and a plurality of rollers disposed between the core and the screen for movably securing the screen to the core, the rollers engaging the screen and movement of at least one of the rollers moves the screen about the core.

The present invention relates to an aircraft comprising at least one wing, at least one flight propulsion drive, and a retainer, particularly an engine pylon, which interconnects the wing and the flight propulsion drive. The aircraft comprises at least one heat exchanger for cooling exhaust gas of the fight propulsion drive and/or at least one water removal channel having at least one removal apparatus for removing water from exhaust gas of the flight propulsion drive, especially after the exhaust gas has flowed through the heat exchanger. The removal apparatus is disposed on, more particularly in, the retainer or is connected to the wing by means of the retainer, and/or the flight propulsion drive is fastened to the retainer by means of at least one flight propulsion drive suspension means, and the heat exchanger is fastened, independently thereof, to the retainer by means of at least one heat exchanger suspension means.

The present invention relates to an aircraft comprising at least one wing, at least one flight propulsion drive, and a retainer, particularly an engine pylon, which interconnects the wing and the flight propulsion drive. The aircraft comprises at least one heat exchanger for cooling exhaust gas of the fight propulsion drive and/or at least one water removal channel having at least one removal apparatus for removing water from exhaust gas of the flight propulsion drive, especially after the exhaust gas has flowed through the heat exchanger. The removal apparatus is disposed on, more particularly in, the retainer or is connected to the wing by means of the retainer, and/or the flight propulsion drive is fastened to the retainer by means of at least one flight propulsion drive suspension means, and the heat exchanger is fastened, independently thereof, to the retainer by means of at least one heat exchanger suspension means.

An aircraft includes a fuselage disposed in a longitudinal plane and two propulsion units disposed in a plane transverse to the longitudinal plane, on either side of the fuselage. A nacelle for use in the aircraft includes a proximal upper dial, a distal upper dial, a proximal lower dial, a distal lower dial, an upstream section, a middle section, a downstream section having a trailing edge, and at least one surface heat exchanger, called a cold source exchanger, between a heat transfer fluid and a cold air flow, integrated into a closed circuit in which the heat transfer fluid circulates, and disposed in any one of the proximal upper, distal upper and/or distal lower dials, and in the middle and/or downstream section(s).

An aircraft includes a fuselage disposed in a longitudinal plane and two propulsion units disposed in a plane transverse to the longitudinal plane, on either side of the fuselage. A nacelle for use in the aircraft includes a proximal upper dial, a distal upper dial, a proximal lower dial, a distal lower dial, an upstream section, a middle section, a downstream section having a trailing edge, and at least one surface heat exchanger, called a cold source exchanger, between a heat transfer fluid and a cold air flow, integrated into a closed circuit in which the heat transfer fluid circulates, and disposed in any one of the proximal upper, distal upper and/or distal lower dials, and in the middle and/or downstream section(s).

A propeller system for a tail section of an aircraft includes a propeller hub located at the tail section of the aircraft, a plurality of propeller blades mounted to and extending outwardly from the propeller hub, a propeller shaft coupled to the propeller hub and operable to rotate the propeller hub about an axis of rotation, and a propeller gearbox connected to the propeller shaft. The propeller gearbox is fluidly cooled by an airflow within the tail section. A spinner assembly surrounds the propeller hub. The spinner assembly includes at least one outlet opening formed therein downstream from the propeller hub relative to the airflow. The spinner assembly is rotatable to draw the airflow into at least one cooling flow inlet formed in the tail section and across the propeller gearbox to cool the propeller gearbox and out the at least one outlet opening.

An aircraft includes an aircraft heat source; a propulsion system including an electric propulsion engine, the electric propulsion engine including an electric motor and a fan rotatable by the electric motor, the electric propulsion engine further defining a fan air flowpath; a thermal management system including a heat source exchanger in thermal communication with the aircraft heat source, a heat sink exchanger in thermal communication with the fan air flowpath of the electric propulsion engine, and a thermal distribution bus extending from the heat source exchanger to the heat sink exchanger; and a control system operably connected to the thermal management system for selectively thermally coupling the heat sink exchanger with the heat source exchanger.