Compound turbine cooled engine

Details Compound turbine cooled engine Compound turbine cooled engine

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 7/16 (2006.01) F01D 25/12 (2006.01) F02C 9/18 (2006.01)

Patent

CA 2607675

A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a row of nozzle vanes followed by a row of rotor blades. The vanes and blades have corresponding forward and aft internal cooling channels. First, second, third, and fourth bleed circuits are joined in flow communication with different stages of the compressor for bleeding pressurized air therefrom at different pressures to provide coolant to the forward and aft channels of the turbine vanes and blades.

Affiliated with

Also associated with

Rating

Compound turbine cooled engine does not yet have a rating. At this time, there are no reviews or comments for this patent.

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

Rate now

Comments { 0 }

Profile ID: LFCA-PAI-O-2068974