An engine bleed control system for a gas turbine engine of an aircraft is provided. The engine bleed control system includes a multi-tap bleed array including engine bleed taps coupled to a compressor source of a lower pressure compressor section before a highest pressure compressor section of the gas turbine engine. A highest stage of the engine bleed taps has a maximum bleed temperature below an auto-ignition point of a fuel-air mixture of the aircraft at idle engine power at a maximum aircraft altitude and a pressure suitable for pressurizing the aircraft at the maximum aircraft altitude. The engine bleed control system also includes a plurality of valves operable to extract bleed air from each of the engine bleed taps. A controller is operable to selectively open and close each of the valves based on a bleed air demand and control delivery of the bleed air to an aircraft use.

An apparatus comprises a leading edge of an inlet. The leading edge of the inlet is positioned relative to a direction of air flow such that a total pressure of air along the leading edge of the inlet is equalized within selected tolerances.

A gas turbine engine component includes a heat exchange structure having an upstream end and a downstream end. A diffusing duct is associated with the upstream end. A throttle member controls air flow through the heat exchange structure, wherein the throttle member: (a) has a non-circular cross section; and (b) is mounted to the downstream end of the heat exchange structure or is mounted between the upstream end and the diffusing duct.

A sanitizing system includes a dispensing unit having a fluid storage and a compressed air generator. The fluid storage stores one or more disinfecting fluids or other sanitizing agents. The sanitizing system has an interconnect configured as an adapter that defines a conduit or passageway in an airflow path between a low pressure ground air supply and a connection port on an aircraft. The dispensing unit is configured to dispense the one or more disinfecting fluids or other sanitizing agents into the airflow path via the interconnect.

An engine driven environmental control system (ECS) air circuit includes a gas turbine engine having a compressor section. The compressor section includes a plurality of compressor bleeds. A selection valve selectively connects each of said bleeds to an input of an intercooler. A second valve is configured to selectively connect an output of said intercooler to at least one auxiliary compressor. The output of each of the at least one auxiliary compressors is connected to an ECS air input.

A system includes a concentration sensor, a flow sensor, and a controller. The concentration sensor is configured to measure a concentration of a contaminant in a cabin of an aircraft. The flow sensor is configured to measure a flow rate of air into the cabin. The controller is configured to determine whether a concentration measurement of the contaminant in the cabin exceeds a first concentration threshold. The controller is configured to, in response to determining that the concentration measurement does not exceed the first concentration threshold, control the flow rate of air into the cabin based on a flow rate setpoint. The controller is configured to, in response to determining that the concentration measurement exceeds the first concentration threshold, control the flow rate of air into the cabin based on a flow rate setpoint and a correction factor that is based on a flow sensor tolerance.

A toilet arrangement for an aircraft cabin of an aircraft having a cabin ventilation system for supplying the aircraft cabin with cabin air, includes at least one standing surface for cladding the toilet arrangement. The standing surface is disposed within the toilet arrangement. A ventilator has an entry interface for connection to the cabin ventilation system for transfer of the cabin air. An outlet element is connected to the entry interface for take-over of the cabin air. The ventilator generates a surface-air stream from the cabin air. The surface-air stream flows over the standing surface from the outlet element to dry the standing surface. An aircraft having the toilet arrangement and a method for drying a standing surface of the toilet arrangement are also provided.

The present disclosure makes use of the fact that passengers have ways of adjusting the temperature in their immediate environment or indicating their level of comfort or discomfort and uses information about the passengers' use of the temperature control capabilities in their immediate environment and/or indications of their level of comfort/discomfort as an input to a controller of an environmental control system (ECS) to automatically adjust the ECS supply air temperature set point.

A system includes a primary heat exchanger with a first passage connected to a hot fluid source, a second passage connected to the first passage, and a third passage connected to the second passage and an outlet line. A compressor inlet is connected to the outlet line. A secondary heat exchanger is connected to a compressor outlet. First and second turbines are connected to an outlet of the secondary heat exchanger. A first load heat exchanger is connected to the first turbine. A second load heat exchanger is between the second turbine and a system outlet. A first valve connects the hot fluid source to the second and third passages. A second valve connects the first and second passages with the outlet line. A third valve is between the secondary heat exchanger and the second turbine. A fourth valve is between the first load heat exchanger and the system outlet.

A cabin air compressor assembly includes a cabin air compressor, and a cabin air compressor motor operably connected to the cabin air compressor. The cabin air compressor motor includes a rotor and a stator having a plurality of end windings. A cabin air compressor housing includes at least one cooling airflow hole formed therein. A motor cooling flow is movable across a portion of the cabin air compressor motor to cool the stator and the end windings. A duct extends from the cabin air compressor housing to an adjacent end winding such that a cooling outlet flow provided via the at least one cooling air flow hole is arranged in fluid communication with the end winding.