Patent ID: 9316104
Filing Date: 2016-04-19
CPC Classification: F01D,F05D,F23R,Y02T

Claim Text:
1. A cooling channel array carried by a component wall of a gas turbine engine having a first surface and a second surface, the cooling channel array comprising: a diffusion cavity defined by a face carried by the component wall and having an outlet on the second surface, the diffusion cavity having two or more lobes, each lobe partly defined by a raised, contoured section on the face and each lobe defining a lobe axis diverging from a central axis of the diffusion cavity; and a metering section comprising a main hole and two or more side holes, the main hole having an inlet on the first surface and an outlet located on the face of the diffusion cavity, each side hole having an inlet and having an outlet located on the lobe axis of the face of the diffusion cavity.