Back to results
US 10,202,854 B2Granted
Abrasive tips for ceramic matrix composite blades and methods for making the same
AssigneesRolls-Royce North America Technologies, Inc., ROLLS-ROYCE plc
InventorsRichard C. Uskert, Kang N. Lee, Ted J. Freeman
Life of this patent
Estimating the term…
Abstract
A blade and method for producing the blade for a gas turbine engine are described herein. The blade may include a composite airfoil. The airfoil may comprise a ceramic material, and a distal end. A tip may extend from the distal end of the airfoil. The tip of the airfoil may comprise a substantially porous structure and may comprise infiltrated material extending from an airfoil preform to a tip preform to join the airfoil preform and the tip preform.
Claims14
A method of making a blade for a gas turbine engine, the method comprising
- forming a tip preform having continuous porosity substantially throughout the tip preform,
- positioning the tip preform relative to an airfoil preform so that the tip preform extends beyond a distal end of the airfoil preform, the airfoil preform including ceramic material and having continuous porosity substantially throughout the airfoil preform, and
- co-infiltrating, after the positioning the tip preform, the tip preform and the airfoil preform to densify the tip preform and the airfoil preform thereby joining the tip preform and the airfoil preform to form the blade.
A method comprising:
- forming a tip preform having continuous porosity substantially throughout the tip preform by at least:
- suspending tip particles in a substrate or material comprising at least one of chopped fibers, continuous fibers, woven fabrics, or ceramic foam;
- positioning the tip preform relative to an airfoil preform so that the tip preform extends beyond a distal end of the airfoil preform, the airfoil preform including ceramic material and having continuous porosity substantially throughout the airfoil preform, and
- co-infiltrating, after the positioning the tip preform, the tip preform and the airfoil preform to densify the tip preform and the airfoil preform thereby joining the tip preform and the airfoil preform to form the blade, wherein the infiltrated tip preform defines a distal-most surface of the blade, and wherein the distal-most surface of the blade comprises the tip particles.
1 more element
Dependencies are inferred from the claim text.