Abstract: An aircraft system includes a housing having an outer surface and an inner surface defining a cavity. A motor is arranged in the cavity. The motor includes a heat producing component mounted to the inner surface. A first cooling system is configured to direct a first heat exchange fluid in a first thermal exchange relationship with the heat producing component and a second cooling system is configured to direct a second heat exchange fluid in a second thermal exchange relationship with the heat producing component. The second heat exchange fluid is distinct from the first heat exchange fluid and the second thermal exchange relationship is distinct from the first thermal exchange relationship.

Abstract: An environmental control system of an aircraft including a compression device including a compressor having a compressor inlet and a compressor outlet, a primary inlet for supplying a first medium to the compressor inlet, and a secondary inlet for supplying a second medium to the compressor inlet.

Abstract: An aqueous based drilling fluid that exhibits improved lubricity, containing a phospholipid lubricant component and methods of improving the lubricity of an aqueous based drilling fluids. The methods include improving the lubricity of an aqueous based drilling fluid composed of an aqueous base fluid, and a weighting agent, with the addition of an effective amount of a phospholipid to substantially reduce the coefficient of friction when compared to the fluid absent the phospholipids.

Abstract: An environmental control system of an aircraft including a compression device including a compressor having a compressor inlet and a compressor outlet, a primary inlet for supplying a first medium to the compressor inlet, and a secondary inlet for supplying a second medium to the compressor inlet.

Abstract: A motor housing assembly for a cabin air compressor assembly is provided that includes a central body portion, a first end portion, and a second end portion. The central body portion has an internal cavity configured to receive an electric motor. The first end portion includes a first and second motor cooling inlet duct. The second end portion includes a flange configured to couple with an outlet housing of the cabin air compressor assembly. A motor cooling duct centerline is defined between the first and second motor cooling inlet duct and is perpendicular to a central body portion centerline. A first distance is defined between an outer edge of the first and second motor cooling inlet duct. A second distance is defined between an outer face of the flange and an intersection of the centerlines. A ratio of the first distance to the second distance is between 1.29 and 1.3.

Abstract: An aircraft is provided including an environmental control system (ECS) having a first ECS pack and a second ECS pack. A duct couples the first ECS pack to the second ECS pack. The duct includes a first bypass conduit configured to form a bypass around a first primary heat exchanger of the first ECS pack. A second bypass conduit configured to form a bypass around a second primary heat exchanger of the second ECS pack. The duct includes a crossover conduit extending between the first bypass conduit and the second bypass conduit. The duct includes a plurality of valves for selectively controlling a flow between the first bypass conduit and the second bypass conduit.

Abstract: A motor housing assembly for a cabin air compressor assembly is provided that includes a central body portion, a first end portion, and a second end portion. The central body portion has an internal cavity configured to receive an electric motor. The first end portion includes a first and second motor cooling inlet duct. The second end portion includes a flange configured to couple with an outlet housing of the cabin air compressor assembly. A motor cooling duct centerline is defined between the first and second motor cooling inlet duct and is perpendicular to a central body portion centerline. A first distance is defined between an outer edge of the first and second motor cooling inlet duct. A second distance is defined between an outer face of the flange and an intersection of the centerlines. A ratio of the first distance to the second distance is between 1.29 and 1.3.

Abstract: A galley chiller system configured to operate in a defrost mode is provided including a cooling module, a heating element, and a fan module. The cooling module is configured to provide cool air to at least one galley monument. The cooling module includes a heat exchanger configured to have both air and a liquid coolant flow there through in a heat transfer relationship. The heating element is arranged generally adjacent a coolant inlet of the heat exchanger. The fan module is configured to circulate warm return air from the at least galley monument to the cooling module. When the galley chiller system is in the defrost mode, only liquid coolant flows through the heat exchanger. The liquid coolant is locally heated by the heating element.

Abstract: An aircraft is provided including an environmental control system (ECS) having a first ECS pack and a second ECS pack. A duct couples the first ECS pack to the second ECS pack. The duct includes a first bypass conduit configured to form a bypass around a first primary heat exchanger of the first ECS pack. A second bypass conduit configured to form a bypass around a second primary heat exchanger of the second ECS pack. The duct includes a crossover conduit extending between the first bypass conduit and the second bypass conduit. The duct includes a plurality of valves for selectively controlling a flow between the first bypass conduit and the second bypass conduit.