A structure for a turbine, the structure comprising a body having a multi-layer construction including an interior layer with substantially uniform concentrations throughout of facultative anaerobic organisms (FAO) that have gene sets capable of producing the enzyme urease and/or the proteins purloin, lustre A and perlustrin, along with glucose, and non-uniform concentrations throughout of a structural composition, the structural composition including a chitin-based component with silk fibronectin and water; an exterior layer of urea, water, calcium ions and facultative anaerobic organisms (FAOs) including urease, aragonite; and a binding layer of conchiolin protein intermediate the interior layer and the exterior layer. The facultative anaeorobic organisms (FAOs) are organisms classified in one of the Saccharomyces, Escherichia and Bacillus genuses.

A device deices an aerodynamic profile that has a lower surface, a plurality of unitary cavities delimited by a lattice of partitions on the lower surface, and a barrier arranged on the lattice of partitions. The surface includes a first plurality of holes which connect the unitary cavities to a device for generating a negative pressure in the cavities simultaneously so as to press the barrier onto the lattice of partitions. A second plurality of holes connect the unitary cavities to a device for generating one or more pressure pulses in at least some of the selected unitary cavities. The barrier is equipped with one or more resistive networks positioned below the barrier in line with some of the cells in order to create localized electrothermal deicing zones in the device.

The present disclosure provides for methodologies for height measurement in pneumatic deicer boots for aircraft, and related models, systems and methods of use. More particularly, the present disclosure provides for methods, models, systems and applications to detect the life or failure of pneumatic deicer boots for aircraft. A method for detecting the life or failure of pneumatic deicer boots for aircraft is provided.

A method of operating a monitored deicing system may comprise attempting, by a health monitor, to pass an electrical current through a signal wire disposed along a boot seam of a pneumatic deicer, evaluating, by the health monitor, a continuity of the signal wire in response to the electrical current, identifying, by the health monitor, that the signal wire lacks continuity in response to the evaluating, and determining, by the health monitor, that the boot seam has broken in response to the identification that the signal wire lacks continuity.

A method includes receiving a plurality of temperature measurements from temperature sensors of an aircraft. The method includes determining whether a first count of one or more first temperature metrics that are within a temperature range is greater than a first threshold. The one or more temperature metrics are derived from the plurality of temperature measurements. The method includes initiating generating an icing output signal when the first count is greater than or equal to the first threshold.

A method of operating a monitored deicing system may comprise attempting, by a health monitor, to pass an electrical current through a signal wire disposed along a boot seam of a pneumatic deicer, evaluating, by the health monitor, a continuity of the signal wire in response to the electrical current, identifying, by the health monitor, that the signal wire lacks continuity in response to the evaluating, and determining, by the health monitor, that the boot seam has broken in response to the identification that the signal wire lacks continuity.

A monitored deicing system is disclosed. The monitored deicing system may have a pneumatic deicer and a signal wire running through the pneumatic deicer. The signal wire may break in response to a failure of the pneumatic deicer, such as a torn boot seam. A health monitor may check the continuity of the signal wire in order to provide an alert upon detecting such a failure.

A pneumatic de-icing system is provided. In some embodiments, the pneumatic de-icing system includes a de-icer flow valve, an accumulator, and a source control valve. The source control valve is configured to supply pressurized air to the at least one de-icer flow valve from either the accumulator or a pressurized cabin depending on a differential air pressure between an air pressure in the pressurized cabin and an ambient air pressure surrounding an aircraft. In some embodiments, pneumatic de-icing system includes a de-icing assembly, a pneumatic inlet valve, a de-icer flow valve, and an ejector. The de-icer flow valve is configured to supply pressurized air to the pneumatic inlet valve during an icing event. The ejector is configured to supply a vacuum to the pneumatic inlet valve.

The present disclosure provides for pneumatic deicer boot assemblies, and related methods of fabrication and use. More particularly, the present disclosure provides for bartack stitched pneumatic deicer boot assemblies for aircraft or the like, with the bartack stitched pneumatic deicer boot assemblies having an inflatable carcass formed by two layers (e.g., a stretchable layer and a non-stretchable layer) stitched together using bartack stitches.