Patent ID: 9458720
Filing Date: 2016-10-04
CPC Classification: F01D,F05D,G06F,Y02T

Claim Text:
1. An assembly comprising: an airfoil for a turbine engine bladed wheel and a platform on which the airfoil is configured to be mounted: a plurality of the airfoils configured to be fastened to the platform or to a plurality of the platforms assembled together so as to form a bladed wheel including a wheel axis and defining upstream and downstream directions along the wheel axis, the airfoils being arranged radially in the wheel; in the wheel, the platform or the assembled-together platforms present a platform surface between the airfoils and that radially defines an inside of gas-passing passages formed between the airfoils; and the platform surface presenting a circumferential depression extending axially substantially between a leading edge and a trailing edge of an airfoil, a deepest section of the depression being situated axially in an upstream half of the airfoil; wherein: a skeleton curve is a curve representing variations of a skeleton angle of the airfoil in a section plane substantially parallel to the platform surface, as a function of position along the wheel axis; a linearized skeleton curve is a curve representing variations of an angle as a function of position along the wheel axis, which linearized skeleton curve is a straight line connecting together points representing the skeleton angle respectively at 10% and at 90% of the axial extent of the airfoil from the leading edge, in a vicinity of the platform, the skeleton curve presents a raised portion lying above the linearized skeleton curve, and a plane in which an offset between the skeleton curve and the linearized skeleton curve is at a maximum is situated axially between a position at 0.5×N % of the deepest section and 1.5×N %, the value N being a percentage expressed relative to axial extent of the airfoil from the leading edge.