Abstract: An Environmental Control System (ECS) for an aircraft includes a ram air system having a ram inlet and a ram outlet. The ECS includes a cabin air compressor motor, a diverter valve, and a dedicated outlet. The cabin air compressor motor has a motor inlet passage and a motor outlet passage with the motor inlet passage being coupled to the ram inlet. The diverter valve includes a first diverter inlet, a first diverter outlet, and a second diverter outlet. The first diverter inlet is coupled to the motor outlet passage. The dedicated outlet is connected to the first diverter outlet in a flight mode of operation of the aircraft and the ram outlet is connected to the second diverter outlet in a ground mode of operation of the aircraft.

Abstract: An aircraft is provided. The aircraft includes a pressurized volume and an air conditioning system. The air conditioning system operates in a first mode when the aircraft is performing high altitude operations and a second mode when the aircraft is performing low altitude operations. The first mode includes when a first medium, a second medium, and a third medium are mixed by the air conditioning system to produce a chamber ready medium. The second mode comprises when only the first medium and the second medium are mixed by the air conditioning system to produce the chamber ready medium. The air conditioning system provides the chamber ready medium to the pressurized volume.

Abstract: An Environmental Control System (ECS) for an aircraft includes a ram air system having a ram inlet and a ram outlet. The ECS includes a cabin air compressor motor, a diverter valve, and a dedicated outlet. The cabin air compressor motor has a motor inlet passage and a motor outlet passage with the motor inlet passage being coupled to the ram inlet. The diverter valve includes a first diverter inlet, a first diverter outlet, and a second diverter outlet. The first diverter inlet is coupled to the motor outlet passage. The dedicated outlet is connected to the first diverter outlet in a flight mode of operation of the aircraft and the ram outlet is connected to the second diverter outlet in a ground mode of operation of the aircraft.

Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having a plurality of heat exchangers positioned therein, the plurality of heat exchangers including a first heat exchanger, a second heat exchanger, and a third heat exchanger. The ram air circuit is configured and arranged so that a first medium received at the first heat exchanger passes through the first heat exchanger and then through the third heat exchanger and so that a second medium received at the second heat exchanger passes through the second heat exchanger. A compressing device is arranged in fluid communication with the ram air circuit.

Abstract: An Environmental Control System (ECS) for an aircraft includes a ram air system having a ram inlet and a ram outlet. The ECS includes a cabin air compressor motor, a diverter valve, and a dedicated outlet. The cabin air compressor motor has a motor inlet passage and a motor outlet passage with the motor inlet passage being coupled to the ram inlet. The diverter valve includes a first diverter inlet, a first diverter outlet, and a second diverter outlet. The first diverter inlet is coupled to the motor outlet passage. The dedicated outlet is connected to the first diverter outlet in a flight mode of operation of the aircraft and the ram outlet is connected to the second diverter outlet in a ground mode of operation of the aircraft.

Abstract: An environmental control system of an aircraft includes a ram air circuit with a ram air shell having at least one heat exchanger positioned therein, a dehumidification system arranged in fluid communication with the ram air circuit, a compression device arranged in fluid communication with the ram air circuit and the at least one dehumidification system, and an expansion device arranged in fluid communication with the ram air circuit. At least one of the compression device and the expansion device is selectively operable to supplement the ram air within the ram air circuit to meet a demand of the aircraft.

Abstract: An Environmental Control System (ECS) for an aircraft includes a ram air system having a ram inlet and a ram outlet. The ECS includes a cabin air compressor motor, a diverter valve, and a dedicated outlet. The cabin air compressor motor has a motor inlet passage and a motor outlet passage with the motor inlet passage being coupled to the ram inlet. The diverter valve includes a first diverter inlet, a first diverter outlet, and a second diverter outlet. The first diverter inlet is coupled to the motor outlet passage. The dedicated outlet is connected to the first diverter outlet in a flight mode of operation of the aircraft and the ram outlet is connected to the second diverter outlet in a ground mode of operation of the aircraft.

Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having at least one heat exchanger positioned therein, at least one dehumidification system arranged in fluid communication with the ram air circuit, a compressing device arranged in fluid communication with the ram air circuit and the dehumidification system, and an expansion device separate from the compressing device and arranged in fluid communication with the ram air circuit and the at least one dehumidification system. The environmental control system receives a flow of a first medium and a flow of a second medium. The environmental control system is operable in a plurality of modes and in a first mode, a flow of the first medium is provided to the compressing device and the expansion device in series.

Abstract: A RAM inlet header (RIH) is provided and includes a body through which RAM air flows from an inlet toward a heat exchanger and a nozzle body arranged along a wall of the body to direct a curtain of cooled air into flows of the RAM air and toward the heat exchanger.

Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having at least one heat exchanger positioned therein, a dehumidification system arranged in fluid communication with the ram air circuit, and a compressing device arranged in fluid communication with the ram air circuit and the dehumidification system. The compression device includes a compressor and a first turbine coupled to one another via a shaft. During operation of the first turbine, work is extracted from a first medium within the first turbine to power the compressor. At an outlet of the first turbine, a temperature of the first medium is above freezing and at least a portion of the moisture within the first medium is condensed.

Abstract: A system and method that comprises an air cycle machine, a flow of bleed air, at least one heat exchanger, and an inlet configured to supply the flow of the bleed air is provided. The bleed air flows from a source to mix with recirculated air in accordance with a high pressure mode or a recirculation chilling mode. The system and method also can also utilize the recirculated air flowing from the chamber to drive or maintain the air cycle machine in accordance with the above modes.

Abstract: An engine compressor bleed system of an engine for an aircraft is provided including a plurality of compressor pressure ports configured to supply bleed air to satisfy a cooling load for at least a first stage of a flight profile of an aircraft. A first pressure port of the plurality of compressor pressure ports is configured to provide bleed air having a pressure at least equal to a cabin pressure of an aircraft and a temperature that does not exceed a predetermined threshold.

Abstract: A system is provided. The system includes a first environmental control sub-system, operating in a first mode, that receives a first medium at a first flow amount and a first pressure. The system also includes a second environmental control sub-system, operating in a second mode, that receives a second medium at a second flow amount and a second pressure. The first flow amount is greater than the second flow amount, and the second pressure is greater than the first pressure.

Abstract: A method of operating a RAM inlet header (RIH) is provided. The method includes determining a temperature of RAM air flows in a body through which RAM air flows from an inlet toward a heat exchanger, determining a temperature of excess air for use in an environmental control system (ECS) and, in an event the temperature of the excess air is less than the temperature of the RAM air flows, directing a curtain of the excess air from a nozzle body and along a wall of the body into flows of the RAM air and toward the heat exchanger.

Abstract: A system and method includes at least one heat exchanger, a ram fan, and a controller. The ram fan is driven by a motor. A motor control circuit is configured to provide power to the motor to drive the ram fan. The ram fan is configured to provide a ram flow through the at least one heat exchanger from a ram air inlet. The controller is configured to determine a blockage level of the at least one heat exchanger based on the power to the motor, a speed of the ram fan, and a temperature of the ram flow at the ram fan.

Abstract: An engine bleed air system having one or more taps in the compressor section of an aircraft engine, for example a low pressure tap and a high pressure tap. The low pressure tap is fluidly connected to the compressor of a turbo-compressor and the high pressure tap is fluidly connected to the turbine of the turbo-compressor. A bypass line connects the high pressure air to the outlet of the compressor, with a heat exchanger used to remove excess heat from the bypass line. An additional heat exchanger is used to remove any excess heat from the compressed air, dumping the heat to a fan stream or to the expanded air exiting the turbine. The system is controlled to minimize the amount of high pressure air extracted from the engine.

Abstract: A flow sensing ozone converter includes an inlet housing, an outlet housing, and an ozone converter core. The flow sensing ozone converter integrates flow sensing and oxygen removal components. The inlet housing is provided with an inlet housing flange. The outlet housing is provided with an outlet housing flange. The ozone converter core is at least partially received within the inlet housing. The ozone converter is provided with an ozone converter flange that abuts the inlet housing flange and the outlet housing flange.

Abstract: A system and method onboard an aircraft includes a ram air temperature sensor, a bleed air temperature sensor, a valve, and a controller. The ram air temperature sensor is positioned to sense a ram air temperature of a ram air flow. The bleed air temperature sensor is positioned to sense a bleed air temperature of a bleed air flow, wherein the bleed air flow is cooled by a heat exchanger using the ram air flow. The valve is configured to control the bleed air flow upstream of the heat exchanger. The controller is configured to determine a bleed air threshold based on the ram air temperature, and control the valve to reduce the bleed air flow in response to the bleed air temperature reaching the bleed air threshold.

Abstract: A system, which includes a plurality of heat exchangers and a compressing device, prepares a medium bled from a low-pressure location of an engine and flowing through a plurality of heat exchangers into a chamber. The compressing device is in communication with the plurality of heat exchangers and regulates a pressure of the medium flowing through the plurality of heat exchangers. The compressing device includes a turbine that provides supplemental power to the compressing device based on a pressure of the medium in the chamber.

Abstract: A RAM inlet header (RIH) is provided and includes a body through which RAM air flows from an inlet toward a heat exchanger and a nozzle body arranged along a wall of the body to direct a curtain of cooled air into flows of the RAM air and toward the heat exchanger.