Blade tip for ceramic matrix composite blade

A turbine blade adapted for use in a gas turbine engine, the turbine blade comprising

• an airfoil comprising ceramic matrix composite materials including ceramic-containing reinforcements suspended in ceramic-containing matrix material, the airfoil having a radially-inner end portion, a radially-outer end portion, and a body portion that extends from the radially-inner end portion to the radially-outer end portion,
• a protective crown comprising ceramic-containing materials mounted to the radially-outer end portion of the airfoil, the protective crown configured to provide a radially-outermost surface of the turbine blade such that the protective crown is positioned to engage a blade track or other structure radially outward of the airfoil upon use of the turbine blade in a gas turbine engine so that the ceramic matrix composite materials of the airfoil are protected from rub that could remove barrier coatings and expose the ceramic matrix materials of the airfoil to the environment which can damage the ceramic matrix materials of the airfoil, and
• a crown retainer configured to block motion of the protective crown in the radial direction relative to the airfoil, the crown retainer including a flange incorporated into either the airfoil or the protective crown that is received in a flange-receiving channel formed in the other of the airfoil or the protective crown.