Platformless turbine blade

A turbine blade rotor assembly for a gas turbine engine comprising:

• a rotor;
• nickel alloy turbine blades each having a root and an airfoil, the roots supported by the rotor;
• and
• a ceramic platform supported between each pair of the turbine blades adjacent to the airfoils, wherein the platforms include a base having an aperture, and the rotor includes a hole, a pin received in the hole and the aperture securing each platform to the rotor.

A turbine vane assembly for a gas turbine engine comprising:

• a turbine vane including an airfoil extending from a root, the airfoil having a perimeter;
• a platform near the root;
• a shroud having an aperture receiving the airfoil, with a single shroud substantially surrounding the airfoil at the perimeter, the shroud constructed from a ceramic matrix composite material;
• wherein the perimeter includes pressure and suction sides and leading and trailing edges, the single shroud extending from the leading and trailing edges along and adjacent to both the high and low pressure sides;
• and
• wherein the shroud is an inner flowpath surface spaced from the tip and the platform.

A turbine vane assembly for a gas turbine engine comprising:

• a turbine vane including an airfoil extending from a root, the airfoil having a perimeter;
• a platform near the root;
• and
• a shroud having an aperture receiving the airfoil, with a single shroud substantially surrounding the airfoil at the perimeter, the shroud constructed from a ceramic matrix composite material;
• wherein the perimeter includes pressure and suction sides and leading and trailing edges, the single shroud extending from the leading and trailing edges along and adjacent to both the high and low pressure sides;
• and
• a case supporting the root, wherein the shroud is the platform, the platform secured to the vane and configured to be unsupported by a rotor, wherein the root includes legs axially spaced from one another, each leg including spaced apart feet supported on the case.