A turbine engine fan rotor having a disk carrying blades, a substantially frustoconical cover mounted on the disk, and axial retention device for retaining the blades and including a ring mounted in an annular groove in the disk and forming a bearing surface for roots of the blades. The ring is festooned or crenellated and co-operates with a festooned radial annular lip of the disk. The rotor also has at least one axial tooth inserted in hollow portions of the ring and of the lip of the disk. Two coaxial parts arranged radially inside the disk have respective first and second fastener flanges for fastening to the disk, said flanges being axially interposed between the cover and the disk, being circumferentially offset relative to one another, and being fastened independently of one another to the disk.

A turbine engine fan rotor having a disk carrying blades, a substantially frustoconical cover mounted on the disk, and axial retention device for retaining the blades and including a ring mounted in an annular groove in the disk and forming a bearing surface for roots of the blades. The ring is festooned or crenellated and co-operates with a festooned radial annular lip of the disk. The rotor also has at least one axial tooth inserted in hollow portions of the ring and of the lip of the disk. Two coaxial parts arranged radially inside the disk have respective first and second fastener flanges for fastening to the disk, said flanges being axially interposed between the cover and the disk, being circumferentially offset relative to one another, and being fastened independently of one another to the disk.

A compartment based inlet particle separator system for an aircraft that includes an auxiliary power unit (APU) system compartment is provided. The system includes a separation barrier wall, a ram air inlet opening, a diffuser, and an inlet particle separator (IPS). The separation barrier wall is disposed within the APU system compartment and divides the APU system compartment into two compartments. The ram air inlet opening is formed one of the compartments. The diffuser receives ram air from a ram air inlet opening and discharges ram air into a compartment. The IPS is disposed within the a compartment between the diffuser outlet and the APU air inlet port.

A compartment based inlet particle separator system for an aircraft that includes an auxiliary power unit (APU) system compartment is provided. The system includes a separation barrier wall, a ram air inlet opening, a diffuser, and an inlet particle separator (IPS). The separation barrier wall is disposed within the APU system compartment and divides the APU system compartment into two compartments. The ram air inlet opening is formed one of the compartments. The diffuser receives ram air from a ram air inlet opening and discharges ram air into a compartment. The IPS is disposed within the a compartment between the diffuser outlet and the APU air inlet port.

A turbine with rotary blades includes a stator, a rotor rotational about an axis of the turbine and rotational blades evenly spaced around a circumference of the rotor. The turbine includes a pressure chamber circumscribed by a slot and a sealing chamber between which an inlet channel for a medium supply leads into the pressure chamber. The slot, the sealing chamber and the blades are adapted to permanently seal both the slot and the sealing chamber with at least one blade. The rotation of the blades can be ensured by a toothed gear, wherein angular speed of the blades is an integer multiple of the angular speed of the rotor. The blades may have a front wall and a rear wall of approximately conical or cylindrical shape.