A gas turbine engine for an aircraft comprises: an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan comprising a plurality of fan blades; a bypass ...

A fan blade (100) includes an aerofoil portion (110) including a leading edge (120) extending from a root (140) to a tip (150) and defining a blade span (145) therebetween. A leading edge thickness (TLE) is defined as a thickness of a cross-section at a gi...

A monitoring system (12) for use with a turbine engine (10) is described herein. The turbine engine includes a compressor (32) and at least one compressor bleed valve (42) coupled to the compressor. The monitoring system (12) includes at least one sensor (...

A vane includes a composite airfoil having one or more outer pockets and one or more outer spars received therein respectively. The outer spars extending radially inwardly from an outer bridge of the outer vane mount outwardly supporting airfoil. The spars...

The bypass duct has support struts, which are formed as guide vanes-support struts (3) with bigger thickness and chord length than the guide vanes (2) in an aligned aerodynamic form. A flow channel (4) existing between a suction side (7) of the guide vane-...

A fan system (50) is disclosed having a forward fan stage (52) configured to pressurize an airflow (1) and an aft fan stage (60) having a tip-fan (70) configured to pressurize a first portion (3) of a pressurized air flow (2) from the forward fan stage (52...

A gas turbine engine blade (11) has a relatively large fillet (18) to improve the characteristics of the air flow thereover. The fillet (18) has a thin wall which partially defines a fillet cavity (24) therebehind, and cooling air is provided to the fillet...