Chevron film cooled wall
AssigneeGeneral Electric Company
InventorsChing-Pang Lee, Steven Robert Brassfield, Ronald Scott Bunker
Life of this patent
Estimating the term…
Abstract
A wall in a gas turbine engine includes inner and outer surfaces having a row of compound chevron film cooling holes extending therethrough. The chevron holes diverge both longitudinally and laterally between an inlet at the wall inner surface and a chevron outlet at the wall outer surface.
Claims31
A gas turbine engine wall comprising:
- opposite inner and outer surfaces having a row of compound chevron film cooling holes extending longitudinally therethrough and diverging both longitudinally and laterally between an inlet at said inner surface and a chevron outlet at said outer surface;
- and
- each of said chevron holes including a cylindrical inlet bore commencing at said inlet in said inner surface and terminating in a pair of wing troughs having a common ridge therebetween.
A gas turbine engine wall comprising opposite inner and outer surfaces having a plurality of film cooling holes inclined longitudinally therethrough from an inlet at said inner surface through a pair of triangular troughs increasing in lateral width and depth along a common ridge being inclined with decreasing depth to a chevron outlet at said outer surface.
A gas turbine engine wall comprising:
- opposite inner and outer surfaces having a row of compound chevron film cooling holes extending longitudinally therethrough and diverging both longitudinally and laterally between an inlet at said inner surface and a chevron outlet at said outer surface;
- each of said chevron holes includes an inlet bore commencing at said inlet in said inner surface and terminating in a pair of wing troughs having a common ridge therebetween;
- said inlet bore is inclined between said inner and outer surfaces;
- and
- said wing troughs diverge longitudinally between said bore and outer surface, and laterally along said ridge.
Dependencies are inferred from the claim text.