Abstract: Fuel tank inerting systems for aircraft are described. The systems include a fuel tank, a first reactant source fluidly connected to the fuel tank, a second reactant source, a catalytic reactor arranged to receive a first reactant from the first source and a second reactant from the second source to generate an inert gas that is supplied to the fuel tank to fill a ullage space of the fuel tank, a heat exchanger arranged between the catalytic reactor and the fuel tank and configured to at least one of cool and condense an output from the catalytic reactor to separate out an inert gas and a byproduct, a reheater arranged between the catalytic reactor and the heat exchanger, and a recirculation loop configured to extract air from downstream of the heat exchanger, pass the extracted air through the reheater, and inject reheated air upstream of the catalytic reactor.

Abstract: Disclosed is an air cycle machine (ACM) having: a turbine; a compressor; a compressor shaft connected to the compressor and configured to receive rotational energy from a gearbox; and a turbine shaft connected to the turbine and configured to provide rotational energy to the gearbox; wherein the turbine shaft and the compressor shaft operate at different rotational speeds.

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: Disclosed is a cooling circuit for cooling a heat load in an aircraft system, having: a compressor; a turbine connected to the compressor by a shaft, the turbine configured to drive the compressor via the shaft when RAM air pressure into a turbine inlet is above a first threshold; and a motor connected to the shaft configured to drive the compressor when RAM air pressure at the turbine inlet is below the first threshold to cause the compressor to draw air into the turbine inlet, through the turbine, a heat exchanger in fluid communication with the heat load, the compressor, and out of a compressor outlet.

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 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: Disclosed is a cooling circuit for cooling a heat load in an aircraft system, having: a compressor; a turbine connected to the compressor by a shaft, the turbine configured to drive the compressor via the shaft when RAM air pressure into a turbine inlet is above a first threshold; and a motor connected to the shaft configured to drive the compressor when RAM air pressure at the turbine inlet is below the first threshold to cause the compressor to draw air into the turbine inlet, through the turbine, a heat exchanger in fluid communication with the heat load, the compressor, and out of a compressor outlet.

Abstract: Disclosed is a method of environmental control, comprising: passing a first air stream and a second air stream through a valve; wherein the valve directs the first air stream through a first adsorption bed and directs the second air stream through a second adsorption bed; wherein the first adsorption bed produces a dehumidified air stream, and wherein the second adsorption bed is purged of moisture by the second air stream, thus producing a purge stream; and using the valve to redirect the first air stream and the second air stream when the first adsorption bed reaches a moisture saturation point or a timed interval, wherein the first air stream passes through the second adsorption bed and the second air stream passes through the first adsorption bed.

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: Disclosed is an air cycle machine (ACM) having: a turbine; a compressor; a compressor shaft connected to the compressor and configured to receive rotational energy from a gearbox; and a turbine shaft connected to the turbine and configured to provide rotational energy to the gearbox; wherein the turbine shaft and the compressor shaft operate at different rotational speeds.

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: A dual concentric turbine system for use in an air cycle environmental control system including: a shaft configured to rotate around a rotational axis of the shaft; a first turbine attached to the shaft; a second turbine attached to the shaft and concentric to the first turbine; and an integral shroud attached to the shaft, the integral shroud being radially interposed between the first turbine and the second turbine, wherein the first turbine, the second turbine, and the integral shroud are configured to rotate with the shaft around the rotational axis of the shaft.

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: Fuel tank inerting systems for aircraft are described. The systems include a fuel tank, a first reactant source fluidly connected to the fuel tank, a second reactant source, a catalytic reactor arranged to receive a first reactant from the first source and a second reactant from the second source to generate an inert gas that is supplied to the fuel tank to fill a ullage space of the fuel tank, a heat exchanger arranged between the catalytic reactor and the fuel tank and configured to at least one of cool and condense an output from the catalytic reactor to separate out an inert gas and a byproduct, a reheater arranged between the catalytic reactor and the heat exchanger, and a recirculation loop configured to extract air from downstream of the heat exchanger, pass the extracted air through the reheater, and inject reheated air upstream of the catalytic reactor.

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: An environmental control system for an aircraft according to an example of the present disclosure includes a first turbine coupled to an engine and a second turbine coupled to a compressor. One or more ducts are configured to provide bleed air from the engine to the first and second turbines and the compressor such that the first and second turbines and the compressor condition the bleed air. A method of conditioning air is also disclosed.

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: 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: 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 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.