초록 ▼

To minimize secondary losses and flow maldistribution, an aerofoil such as a gas turbine nozzle guide vane, is designed so that in the throat defined by the trailing edge of one aerofoil and the flank of the adjacent aerofoil, the local gas flow streamlines are normal to the trailing edge of the aer

To minimize secondary losses and flow maldistribution, an aerofoil such as a gas turbine nozzle guide vane, is designed so that in the throat defined by the trailing edge of one aerofoil and the flank of the adjacent aerofoil, the local gas flow streamlines are normal to the trailing edge of the aerofoil at the point of intersection.

대표청구항 ▼

An aerofoil for a gas turbine engine, the aerofoil having an aerodynamic profile defined by a number of elemental aerofoil sections stacked relatively to one another, the elements of the aerofoil trailing edge between the elemental aerofoil sections being arranged to define at least partially, the t

An aerofoil for a gas turbine engine, the aerofoil having an aerodynamic profile defined by a number of elemental aerofoil sections stacked relatively to one another, the elements of the aerofoil trailing edge between the elemental aerofoil sections being arranged to define at least partially, the trailing edge of the aerofoil, the aerofoil trailing edge forming one boundary of the geometric throat window between adjacent aerofoils in an array of aerofoils, an elemental length of said trailing edge extending perpendicular to the local streamlines of the gas flow passing through said throat window.