Effusion cooling for gas turbine combustors

Details Effusion cooling for gas turbine combustors Effusion cooling for gas turbine combustors

F - Mech Eng,Light,Heat,Weapons

23

R

F23R 3/42 (2006.01) F02C 7/12 (2006.01)

Patent

CA 2644383

A combustor for a turbine engine includes an outer liner and an inner liner circumscribed by the outer liner to form a combustion chamber therewith in which an air and fuel mixture is combusted to form streamlines of combustion gases. A first plurality of effusion cooling holes is formed in at least one of the inner or outer liners, with the first plurality of effusion cooling holes being oriented as a function of the streamlines.

Affiliated with

Also associated with

Rating

Effusion cooling for gas turbine combustors does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Effusion cooling for gas turbine combustors, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Effusion cooling for gas turbine combustors will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFCA-PAI-O-1993593