| 主权项 |
1. A turbine engine airfoil structure comprising:
an airfoil adapted to be supported to extend across a gas passage for a hot working gas in a turbine engine, the airfoil including sidewalls comprising radially extending pressure and suction sides; a platform structure located at one end of the airfoil and positioned at a location forming a boundary of the gas passage, and including:
a platform member including a gas side surface extending generally perpendicular from the airfoil at a junction with the airfoil, and providing a structural connection to the airfoil; anda separately formed platform cover attached to the platform member at the gas side surface, the platform cover including an outer surface located for contact with the hot working gas passing through the gas path, the outer surface comprising a contoured endwall surface having a first edge located adjacent to one of the sidewalls, wherein the platform cover includes a cooling fluid channel defined between the gas side surface of the platform member and a channel wall formed on the platform cover, the channel wall facing toward the gas side surface, wherein the channel wall comprises a plurality of support members extending from the channel wall and having distal end portions engaged on the platform member for retaining the platform cover to the platform member,wherein the platform cover further comprises a second edge opposite the first edge and located generally aligned with a mateface of the platform member, the second edge being spaced from the mateface of the platform member to define a seal slot therebetween for receiving a mateface seal. |
