GAS TURBINE ENGINE SHROUDED BLADE

摘要

A gas turbine engine bladed component, such as a turbine blade, is shown as including a shroud located above a blade portion and a stiffener located above the shroud. The stiffener is generally located in a central interior region of the shroud and includes a raised portion that extends above a top surface of the shroud. In one non-limiting form the stiffener can have a central ridge that is oriented in an axial direction. Seal members can be included in the shroud that can be used to interact with corresponding seal members in static gas turbine engine structure to discourage a flow of fluid. In one form the shroud includes an upturned leading edge portion.

主权项

1. An apparatus comprising:
a gas turbine engine blade having a pressure side and a suction side that extend along a span to a radially outer portion; and a shroud connected with the radially outer portion of the gas turbine engine blade and extending beyond the gas turbine engine blade in a first direction to a first circumferential side and in a second direction to a second circumferential side, the shroud having a flow path side and a non-flow path side, the non-flow path side including a thickened stiffener placed in a central portion of the shroud and raised in elevation from the non-flow path side relative to an elevation of the first circumferential side and the second circumferential side, the thickened stiffener descending to an outer periphery that extends circumferentially short of both the first circumferential side and the second circumferential side.