Internally cooled gas turbine airfoil and method

Details Internally cooled gas turbine airfoil and method Internally cooled gas turbine airfoil and method

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/18 (2006.01) F02C 7/12 (2006.01)

Patent

CA 2528693

An internally cooled airfoil for a gas turbine engine, wherein a plurality of elongated cooling fins are provided inside the concave sidewall.

Profil aérodynamique de turbine à gaz refroidi par l'intérieur qui comprend plusieurs ailettes de refroidissement allongées situées à l'intérieur de sa paroi concave.

Affiliated with

Also associated with

Rating

Internally cooled gas turbine airfoil and method does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Internally cooled gas turbine airfoil and method, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Internally cooled gas turbine airfoil and method will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFCA-PAI-O-1434469