Patent ID: 9464526
Filing Date: 2016-10-11
CPC Classification: F01D,F04D,F05D,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 that 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; the platform surface presenting a circumferential depression extending axially substantially between a leading edge of an airfoil at its upstream end and up to no more than 60% of an axial extent of the airfoil at its downstream end; 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 axis of the wheel, a linearized skeleton curve is a curve representing variations of an angle as a function of position along the axis of the wheel that connects together in a straight line 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, a lowered portion of the skeleton curve which lies under the linearized skeleton curve extends axially over at least half of the axial extent of the depression.