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: A bleed valve control system for mounting to a support structure adjacent to a fan air plenum within an aircraft includes a bleed valve module, a pneumatic valve controller, and a fan air duct. The bleed valve module includes a pipe, a plurality of bleed valves connected to the pipe, and a plurality of pneumatic actuators connected to the bleed valves. The pneumatic valve controller includes a plurality of electrical control elements and a cooling shroud. The cooling shroud is attached to the pipe and at least partially surrounds the plurality of electrical control elements. The fan air duct connects the cooling shroud to the fan air plenum such that fan air flows through the cooling shroud to cool the plurality of electrical control elements.

Abstract: An airplane is provided. The airplane includes a motor-driven compressor assembly. The motor-driven compressor assembly includes a shaft, a motor, a compressor, and a turbine coupled to the compressor via the shaft. The motor provides a first power to the compressor via the shaft. The turbine receives and expands a second medium to provide a second power to the compressor via the shaft. The compressor receives and compresses a first medium in accordance with the first power provided by the turbine and the second power provided by the motor.

Abstract: An airplane is provided. The airplane includes a pack. The pack includes a shaft, a compressor, a turbine coupled to the compressor via the shaft; and a heat exchanger. The compressor receives and compresses a first medium in accordance with power provided by the turbine via the shaft. The turbine receives and expands a second medium to provide the power to the compressor via the shaft. The heat exchanger is configured to cool the first medium.

Abstract: An airplane is provided. The airplane includes a pack. The pack includes a shaft, a compressor, a turbine coupled to the compressor via the shaft; and a heat exchanger. The compressor receives and compresses a first medium in accordance with power provided by the turbine via the shaft. The turbine receives and expands a second medium to provide the power to the compressor via the shaft. The heat exchanger is configured to cool the first medium.

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 is arranged in fluid communication with the ram air circuit and at least one compressing device is arranged in fluid communication with the ram air circuit and the dehumidification system. The at least one compressing device includes a turbine and a compressor operably coupled via a shaft. A fan is operably coupled to the ram air circuit. At least one compressing device is arranged non-linearly with the ram air circuit such that an axis of rotation of the fan is offset from the axis of the shaft.

Abstract: An environmental control system for providing conditioned air to a volume of an aircraft includes a ram air circuit including a ram air shell with at least one heat exchanger positioned therein. A dehumidification system is arranged in fluid communication with the ram air circuit and at least one compressing device is arranged in fluid communication with the ram air circuit and the dehumidification system. A plurality of mediums is receivable within the environmental control system. A first medium of the plurality of mediums is provided from the volume of the aircraft via at least one valve.

Abstract: An environmental control system of an aircraft includes a ram air circuit having a ram air shell with at least one heat exchanger positioned therein. A dehumidification system is arranged in fluid communication with the ram air circuit and a plurality of compressing devices is arranged in fluid communication with the ram air circuit and the dehumidification system.

Abstract: A flow sensing ozone converter includes an inlet housing, an outlet housing, and a central housing. The inlet housing defines a first pressure port. The outlet housing defines a second pressure port. The central housing extends between a second end of the inlet housing and a first end of the outlet housing.

Abstract: An air compressing system is provided that includes a compressor configured to compressor air. An engine is operatively connected to the compressor. Further, an infinitely variable transmission is operatively connected between the engine and the compressor. A first shaft operatively connects the engine to the infinitely variable transmission and is configured to rotate at a first speed and a second shaft operatively connects the infinitely variable transmission to the compressor and is configured to rotate at a second speed.

Abstract: A bleed valve control system for mounting to a support structure adjacent to a fan air plenum within an aircraft includes a bleed valve module, a pneumatic valve controller, and a fan air duct. The bleed valve module includes a pipe, a plurality of bleed valves connected to the pipe, and a plurality of pneumatic actuators connected to the bleed valves. The pneumatic valve controller includes a plurality of electrical control elements and a cooling shroud. The cooling shroud is attached to the pipe and at least partially surrounds the plurality of electrical control elements. The fan air duct connects the cooling shroud to the fan air plenum such that fan air flows through the cooling shroud to cool the plurality of electrical control elements.

Abstract: A bleed valve control system for mounting to a support structure adjacent to a fan air plenum within an aircraft includes a bleed valve module, a pneumatic valve controller, and a fan air duct. The bleed valve module includes a pipe, a plurality of bleed valves connected to the pipe, and a plurality of pneumatic actuators connected to the bleed valves. The pneumatic valve controller includes a plurality of electrical control elements and a cooling shroud. The cooling shroud is attached to the pipe and at least partially surrounds the plurality of electrical control elements. The fan air duct connects the cooling shroud to the fan air plenum such that fan air flows through the cooling shroud to cool the plurality of electrical control elements.

Abstract: A method for decreasing a throttle setting at which a gas turbine-powered aircraft must switch from low-pressure bleed air to a high-pressure bleed air. The method includes flowing low-pressure bleed air from a compressor at a first pressure. A first portion of the low-pressure bleed air is directed to an air-to-air heat exchanger and cooled in the air-to-air heat exchanger. The first portion of the low-pressure bleed air is flowed from the air-to air heat exchanger into a cooled bleed air line. A second portion of the low-pressure bleed air is directed to a low-pressure bypass line. The second portion of the low-pressure bleed air is flowed from the low-pressure bypass line into the cooled bleed air line upstream of an environmental control system.

Abstract: An air compressing system is provided that includes a compressor configured to compressor air. An engine is operatively connected to the compressor. Further, an infinitely variable transmission is operatively connected between the engine and the compressor. A first shaft operatively connects the engine to the infinitely variable transmission and is configured to rotate at a first speed and a second shaft operatively connects the infinitely variable transmission to the compressor and is configured to rotate at a second speed.

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 method for decreasing a throttle setting at which a gas turbine-powered aircraft must switch from low-pressure bleed air to a high-pressure bleed air. The method includes flowing low-pressure bleed air from a compressor at a first pressure. A first portion of the low-pressure bleed air is directed to an air-to-air heat exchanger and cooled in the air-to-air heat exchanger. The first portion of the low-pressure bleed air is flowed from the air-to air heat exchanger into a cooled bleed air line. A second portion of the low-pressure bleed air is directed to a low-pressure bypass line. The second portion of the low-pressure bleed air is flowed from the low-pressure bypass line into the cooled bleed air line upstream of an environmental control system.

Abstract: A bleed air conditioning system within an aircraft including a low-pressure bleed air line and a high-pressure bleed air line. The system includes an air-to-air heat exchanger and an un-cooled bleed air line to connect the air-to-air heat exchanger to the low-pressure bleed air line and the high-pressure bleed air line. The un-cooled bleed air line carries a flow of un-cooled bleed air from at least one of the low-pressure bleed air line and the high-pressure bleed air line to the air-to-air heat exchanger. The system also includes a cooled bleed air line connected to the air-to-air heat exchanger for carrying cooled bleed air from the air-to-air heat exchanger and a low-pressure bypass line connecting the low-pressure bleed air line to the cooled bleed air line, bypassing un-cooled bleed air from the low-pressure line around the air-to-air heat exchanger to the cooled bleed air line.

Abstract: A hybrid power distribution system for an aircraft generates hydraulic power from one of a plurality of power sources based on which power source provides energy most efficiently. Power sources includes an electric power distribution bus that distributes electrical energy onboard the aircraft, a pneumatic distribution channel that distributes pneumatic energy onboard the aircraft, and mechanical power provided by one or more engines associated with the aircraft.

Abstract: A hybrid power distribution system for an aircraft generates hydraulic power from one of a plurality of power sources based on which power source provides energy most efficiently. Power sources includes an electric power distribution bus that distributes electrical energy onboard the aircraft, a pneumatic distribution channel that distributes pneumatic energy onboard the aircraft, and mechanical power provided by one or more engines associated with the aircraft.

Abstract: A hybrid power distribution system for an aircraft generates hydraulic power from one of a plurality of power sources based on which power source provides energy most efficiently. Power sources includes an electric power distribution bus that distributes electrical energy onboard the aircraft, a pneumatic distribution channel that distributes pneumatic energy onboard the aircraft, and mechanical power provided by one or more engines associated with the aircraft.