Abstract: An air-cooled chiller system includes a heat exchanger including a first tube bank including at least a first and a second flattened tube segments extending longitudinally in spaced parallel relationship; a second tube bank including at least a first and a second flattened tube segments extending longitudinally in spaced parallel relationship, the second tube bank disposed behind the first tube bank with a leading edge of the second tube bank spaced from a trailing edge of the first tube bank; a fan creating an airflow across the first heat exchanger, the airflow flowing over the first tube bank prior to flowing over the second tube bank, wherein refrigerant flows in the heat exchanger in a cross-counterflow direction opposite that of the airflow direction.

Abstract: An air-cooled chiller system includes a heat exchanger including a first tube bank including at least a first and a second flattened tube segments extending longitudinally in spaced parallel relationship; a second tube bank including at least a first and a second flattened tube segments extending longitudinally in spaced parallel relationship, the second tube bank disposed behind the first tube bank with a leading edge of the second tube bank spaced from a trailing edge of the first tube bank; a fan creating an airflow across the first heat exchanger, the airflow flowing over the first tube bank prior to flowing over the second tube bank, wherein refrigerant flows in the heat exchanger in a cross-counterflow direction opposite that of the airflow direction.

Abstract: A multi-pass heat exchanger having a return manifold with a partition, a front wall, and a rear wall is provided. The partition separates the return manifold into a collection chamber and a distribution chamber. The front and rear walls define a fluid channel. The front wall has a plurality of perforations placing the fluid channel in separate fluid communication with the collection chamber and the distribution chamber.

Abstract: An absorption chiller assembly (20) includes a low-stage generator (42) that utilizes heat from vapor resulting from operation of a high-stage generator (26) and heat from another hot liquid such as coolant fluid associated with a prime mover (22). An example low-stage generator (42) includes an arrangement of conduits for directing flow of the two heat sources through the low-stage generator in a manner that both sources simultaneously interact with a refrigerant solution within the low-stage generator. A disclosed example includes an integrated diverter valve that is preassembled and packaged within an absorption chiller assembly. A disclosed heating mode in one example includes using an absorber (60) and a condenser (56) for heating fluid useful for heating operations.

Abstract: A heat exchanger for a fluid having a vapor-phase and a liquid-phase is provided. The heat exchanger includes a first manifold, a second manifold, a plurality of parallel channels, a mixing device, and one or more baffles. The parallel channels are in fluid communication with the first and second manifolds. The mixing device mixes the fluid flowing into the first manifold so that the fluid is a substantially homogeneous two-phase mixture of the vapor and liquid phases. The baffles are within the first manifold and ensure that the fluid enters the parallel channels as the substantially homogeneous two-phase mixture.

Abstract: A multi-pass heat exchanger having a return manifold with a partition, a front wall, and a rear wall is provided. The partition separates the return manifold into a collection chamber and a distribution chamber. The front and rear walls define a fluid channel. The front wall has a plurality of perforations placing the fluid channel in separate fluid communication with the collection chamber and the distribution chamber.

Abstract: An absorption chiller assembly (20) includes a low-stage generator (42) that utilizes heat from vapor resulting from operation of a high-stage generator (26) and heat from another hot liquid such as coolant fluid associated with a prime mover (22). An example low-stage generator (42) includes an arrangement of conduits for directing flow of the two heat sources through the low-stage generator in a manner that both sources simultaneously interact with a refrigerant solution within the low-stage generator. A disclosed example includes an integrated diverter valve that is preassembled and packaged within an absorption chiller assembly. A disclosed heating mode in one example includes using an absorber (60) and a condenser (56) for heating fluid useful for heating operations.

Abstract: The present invention relates to A reduced bleed vapor compression cycle environmental control system for an aircraft. The environmental control system provides conditioned external ram air to compartments such as the cabin, the flight deck, avionics compartment, and other equipment compartments, where conditioned air is needed. The system includes a first compressor for compressing the external ram air to cabin pressure and an evaporator for cooling the external ram air to a desired temperature. The system further includes a low-pressure water separator for removing moisture from the ram air prior to the external ram air being delivered to the compartment(s). The ram air compressor as well as a compressor for a refrigerant loop are driven by a turbine that expands a minimal amount of bleed air from an engine.

Abstract: The present invention relates to an integrated enviromental control system for an aircraft. The system uses bleed air from a propulsion engine to drive an air turbine which provides power to at least one aircraft component such as an aircraft mounted accessory drive. The system uses the bleed air exiting the air turbine as an air source for the cabin and/or flight deck enviromental control system.

Abstract: The present invention relates to an integrated air turbine driving system for providing aircraft environmental control. The system has at least one air driven turbine for providing power to an aircraft mounted accessory drive and for providing heated air to an aircraft anti-ice system. The system further has a subsystem for supplying cooled pressurized air to a flight deck and/or cabin and to aircraft avionics. Still further, the subsystem provides cooling air to other aircraft components such as a generator and/or an aircraft mounted accessory drive.

Abstract: The present invention relates to a reduced bleed vapor compression cycle environmental control system for an aircraft. The environmental control system provides conditioned external ram air to compartments such as the cabin, the flight deck, avionics compartment, and other equipment compartments, where conditioned air is needed. The system includes a first compressor for compressing the external ram air to cabin pressure and an evaporator for cooling the external ram air to a desired temperature. The system further includes a low-pressure water separator for removing moisture from the ram air prior to the external ram air being delivered to the compartment(s). The ram air compressor as well as a compressor for a refrigerant loop are driven by a turbine that expands a minimal amount of bleed air from an engine.

Abstract: The present invention relates to a vapor compression cycle environmental control system for use on aircraft. The system includes an environmental control subsystem which supplies pressurized ram air at a desired temperature to the aircraft's flight deck and/or cabin. The environmental control subsystem uses a vapor compression cycle subsystem to provide the ram air at the desired temperature. The system further includes an air turbine driven by engine bleed air to provide power to an aircraft mounted accessory drive and to provide heated air to an anti-ice system. The aircraft mounted accessory drive provides power to an air compressor which forms part of the environmental control subsystem and to a working fluid compressor which forms part of the vapor compression cycle subsystem.

Abstract: The present invention relates to a reduced bleed vapor compression cycle environmental control system for an aircraft. The environmental control system provides conditioned external ram air to compartments such as the cabin, the flight deck, avionics compartment, and other equipment compartments, where conditioned air is needed. The system includes a first compressor for compressing the external ram air to cabin pressure and an evaporator for cooling the external ram air to a desired temperature. The system further includes a low-pressure water separator for removing moisture from the ram air prior to the external ram air being delivered to the compartment(s). The ram air compressor as well as a compressor for a refrigerant loop are driven by a turbine that expands a minimal amount of bleed air from an engine.