Abstract: There is disclosed a blade for a gas turbine engine comprising an asymmetrical blade root.

Abstract: The thermal shrinkage of a casing (2) to regulate as best as possible the internal play between the rotor and the stator is carried out by a ring (4) fixed onto the skin (2) rather than by a circular ramp at a distance therefrom. The ring (4) comprises, between a collection box (8) and the skin (2), a foraminous plate (7), placed on an opening of the box (8) parallel to the skin (2) and at a short distance, in order to impose invariable and known ventilation conditions.

Abstract: Cross-port air flow that improves engine fuel economy and reduces pumping losses during part-throttle operation can be implemented in various types of internal combustion engine systems using ports that interconnect the intake ports of different cylinders, thus allowing different cylinders to share combustion air. Cross-port air flow is commenced during part-throttle engine operation to disrupt the primary combustion air flow from each throttle to its associated cylinder, which reduces charge density and engine power. The engine compensates for the reduced power by incrementally opening the throttles, thus increasing the primary combustion air flow, reducing pumping losses and improving fuel economy.

Abstract: A gas turbine engine includes a fan mounted to rotate about a main longitudinal axis; an engine core, including a compressor, a combustor, and turbine coupled to the compressor through a shaft; and reduction gearbox; wherein the compressor includes a plurality of stages, each stage including a respective rotor and stator, a first stage of the plurality of stages being arranged at an inlet and including a first rotor with a plurality of blades; each blade extending chordwise from a leading edge to a trailing edge, and from root to tip for a span height, wherein 0% of the span height corresponds to the root and 100% of span height corresponds to tip; wherein the ratio of a maximum leading edge radius of the first rotor blades to a minimum leading edge radius of the first rotor blades is included between 2.2 and 3.5.