An example system for determining a performance status of an environmental control system (ECS) in a vehicle includes memory and processing circuitry. The processing circuitry is configured to determine, based on one or more of the aircraft data, the weather data, or the trending data, an estimated compressor exit temperature. The processing circuitry is configured to determine a current residual compressor exit temperature based on the estimated compressor exit temperature and a current compressor exit temperature. The processing circuitry is configured to determine whether a residual condition is met based at least in part on the residual compressor exit temperature and whether a pack condition is met based at least in part on a pack temperature. The processing circuitry is configured to provide an indication of the performance status of the ECS based on at least one of the residual condition or the pack condition being met.

A duct includes a rigid air-permeable tube of composite material. The duct also includes a layer of insulation coupled to an exterior surface of the rigid air-permeable tube. The duct further includes a non-rigid insulation layer in contact with the layer of insulation. The non-rigid insulation layer forms an air-impermeable duct wall.

An aircraft environmental control system includes a bleed air input and a RAM air input, heat exchanger means for receiving bleed air from the bleed air input and RAM air from the RAM air input and using the RAM air to cool the bleed air, and ejector arranged to receive bleed air from the bleed air input at a nozzle shaped to reduce the pressure of the received bleed air such as to create a low pressure area in the ejector. The ejector has a port arranged such that ambient air is drawn into the ejector due to the low pressure area in the ejector. The ambient air is mixed with bleed air to provide mixed air that is further pressurised and conditioned and combined with the cooled bleed air provided to the aircraft.

An air management system with a set of compressed air sources for selectively supplying pressurized air to air consumer equipment according to an aircraft operation condition. Low pressure air, high pressure air, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition.

A system for collecting a biological sample from a passenger cabin includes a collector for collecting particulate samples positioned within at least one of an outlet flow path or a recirculation flow path. The system includes at least one of an outflow valve positioned in the outlet flow path downstream from the collector or a HEPA (high efficiency particulate air) filter positioned in the recirculation flow path downstream from the collector. A method for collecting particulates from cabin air includes capturing particulates in at least one of an outlet flow path or a recirculation flow path with a collector for a period of time, removing the collector from at least one of the outlet flow path or the recirculation flow path for testing, and inserting a clean collector into at least one of the outlet flow path or the recirculation flow path for use during another period of time.

A vehicle cabin air temperature controller includes a two-position three-way solenoid valve with one inlet to take in coolant supplied by a pump, a first outlet to supply a cooling leg, and a second outlet to supply a bypass leg. The vehicle cabin air temperature controller also includes a controller to control flow of the coolant via the first outlet and the second outlet of the solenoid valve, and a cabin air heat exchanger to obtain an input coolant based on the control of the flow via the first outlet and the second outlet and to provide cooled cabin air to the vehicle cabin. The control of the flow of the coolant via the first outlet and the second outlet controls a flow rate of the input coolant.

A gas turbine engine for mounting to an airframe of an aircraft comprises an engine core; a fan located upstream of the engine core; a bifurcation spanning a bypass duct defined between the engine core and a nacelle surrounding the gas turbine engine, the bifurcation comprising aerodynamically shaped fairings defining an interior space therebetween; and a cabin blower system arranged in the interior space of the upper bifurcation.

There is provided a blower system for providing air to an airframe system, comprising a rotor configured to be mechanically coupled to a spool 440 of a gas turbine engine, wherein the rotor is configured to: in a blower mode, be driven to rotate by the spool to discharge air to an airframe discharge port for supply to an airframe system; and, in an engine drive mode, receive air from an external air source via an impingement port that is configured to direct the received air onto the rotor and thereby drive the rotor to rotate to drive the spool to.

A thermal disinfecting tool for disinfecting surfaces bounding or located within a fixed volume of air is disclosed and includes a housing and a heater. The housing defines one or more inlets and one or more outlets. Air is drawn from the fixed volume of air through the one or more inlets and exits the housing through the one or more outlets. The heater is disposed within the housing downstream of the one or more inlets and upstream of the one or more outlets. The thermal disinfecting tool also includes one or more processors in electronic communication with the heater and a memory coupled to the one or more processors, where the memory stores a time to inactivation plot for a specific pathogen that indicates a deactivation time for the specific pathogen over a range of temperatures.

An environmental control system includes a refrigerant circuit with a pump segment and an evaporator segment, an evaporator arranged along the evaporator segment and in fluid communication with of the refrigerant circuit, and a coolant circuit. The coolant circuit extends through the evaporator and is thermally coupled to refrigerant circuit by the evaporator, the coolant circuit including a first segment and a second segment arranged in parallel with one another to transfer heat from a first zone to a first portion of liquid coolant traversing the coolant circuit and transfer additional heat from a second zone to a second portion of coolant traversing the coolant circuit. Aircraft and environmental control systems are also described.