A system for de-icing an aircraft structure or surface comprises an inert gas generating system comprising a catalyst for receiving fuel and oxygen and converting the fuel and oxygen to CO.sub.2 and H.sub.2O in gaseous form, and a condenser for condensing the H.sub.2O to liquid form, the condenser providing heat to the aircraft structure or surface.

A method for anti-ice performance analysis may comprise cycling a flow of heating air through an aircraft structure, measuring a temperature of the aircraft structure to generating an oscillatory signal, measuring a minimum temperature value of the oscillatory signal, and calculating anti-ice conditions of the aircraft structure based on the minimum temperature value.

A method for anti-ice performance analysis may comprise cycling a flow of heating air through an aircraft structure, measuring a temperature of the aircraft structure to generating an oscillatory signal, measuring a minimum temperature value of the oscillatory signal, and calculating anti-ice conditions of the aircraft structure based on the minimum temperature value.

A method for anti-ice performance analysis may comprise cycling a flow of heating air through an aircraft structure, measuring a temperature of the aircraft structure to generating an oscillatory signal, measuring a minimum temperature value of the oscillatory signal, and calculating anti-ice conditions of the aircraft structure based on the minimum temperature value.

A method for anti-ice performance analysis may comprise cycling a flow of heating air through an aircraft structure, measuring a temperature of the aircraft structure to generating an oscillatory signal, measuring a minimum temperature value of the oscillatory signal, and calculating anti-ice conditions of the aircraft structure based on the minimum temperature value.

A water supply system for use in an aircraft, and a method for preventing blockages in a water supply system in an aircraft. The system comprises a central water tank comprising a fluid inlet and a fluid outlet, a supply conduit for permitting fluid flow from the outlet of the central water tank to a user equipment. At least a section of the supply conduit is connected and thermally coupled to an aircraft air duct so as to enable a transfer of thermal energy to the supply conduit therefrom to maintain the temperature of the water in the supply conduit above the freezing temperature thereof.

A system for controlling bleed air flow in an aircraft is described herein. High-pressure compressor bleed air is regulated in a stepped manner with a bleed full open/full closed valve and a second, bleed half open/full open valve, or with a complex multi-step valve. This mitigates severe pressure transient conditions and results in a less drastic pressure differential across a downstream pressure or flow control valve before the bleed air is repurposed for other uses in the aircraft. The system allows for better downstream system stability across the aircraft operational envelope.

A dual-flow turbomachine including a nacelle, compressors, turbines, a fuel supply line, a transfer line, a de-icing circuit, and a heat management system having: a first heat exchanger providing an exchange of heat between fuel in the supply line and oil in the transfer line, a loop comprising a main line and a pump which circulates a heat transfer fluid in the main line, where the main line is connected to an outlet of the pump and enters an inlet of a third heat exchanger, where at the outlet of the third heat exchanger the main line meets an inlet of the de-icing circuit, where at the outlet of the de-icing circuit the main line meets the inlet of the pump, and where the third heat exchanger transfers heat between the heat transfer fluid of the main line and the oil of the transfer line.

A dual-flow turbomachine including a nacelle, compressors, turbines, a fuel supply line, a transfer line, a de-icing circuit, and a heat management system having: a first heat exchanger providing an exchange of heat between fuel in the supply line and oil in the transfer line, a loop comprising a main line and a pump which circulates a heat transfer fluid in the main line, where the main line is connected to an outlet of the pump and enters an inlet of a third heat exchanger, where at the outlet of the third heat exchanger the main line meets an inlet of the de-icing circuit, where at the outlet of the de-icing circuit the main line meets the inlet of the pump, and where the third heat exchanger transfers heat between the heat transfer fluid of the main line and the oil of the transfer line.

A gas turbine engine comprises a fan rotor having fan blades received within an outer nacelle, and the outer nacelle having an inner surface. A distance is defined between an axial outer end of the nacelle, and a leading edge of the fan blade. An anti-icing treatment is provided to an inner periphery of the nacelle over at least 75% of the distance along the inner periphery of the nacelle.