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US 6,910,856 B2Granted
Run-in coating for axial-flow compressor of gas turbine engines and method of using and making same
AssigneeMTU Aero Engines AG
InventorKai Ruelke
Life of this patent
Estimating the term…
Abstract
Metal wire bundles are combined into brushes as a run-in coating for the axial-flow compressor stage of a gas turbine engine. The metal wire bundles are inserted into the basic material or are combined into brush segments that are inserted into corresponding recesses of the rotor housing.
Claims20
A run-in coating with metal wire bundles combined into brushes for an axial-flow compressor stage of a gas turbine, particularly a gas turbine engine,
- wherein the brushes are strip-shaped, oriented at least predominantly in the axial direction and distributed uniformly spaced apart over the circumference of a rotating blade area of the axial-flow compressor stage so as to form a zebra-striped brush field.
A gas turbine engine axial flow compressor assembly comprising:
- a compressor stator housing which in use surrounds a rotor with rotating blade tips facing a section of the stator housing wall, and
- a run-in coating provided at the section of the stator housing wall and including metal wire bundles anchored at the stator housing wall and forming brushes with free ends of the wires facing the rotating blade tips,
- wherein the brushes are strip shaped and extend in a longitudinal direction of the stator housing, said strip shaped brushes being distributed over the interior circumference of the stator housing with circumferential spacing between adjacent ones of said brushes.
Dependencies are inferred from the claim text.