Combustion chamber of a gas turbine

Details Combustion chamber of a gas turbine Combustion chamber of a gas turbine

F - Mech Eng,Light,Heat,Weapons

23

R

60/174

F23R 3/58 (2006.01) F23C 7/00 (2006.01) F23D 11/40 (2006.01) F23R 3/12 (2006.01) F23R 3/30 (2006.01) F23R 3/34 (2006.01) F23R 3/50 (2006.01)

Patent

CA 2011545

12 ABSTRACT OF THE DISCLOSURE In an annular combustion chamber (A), a row of premixed burners (B, C) are located in the peripheral direction at the inlet end. The large premixed burners (B), which are the main burners of the annular combus- tion chamber (A), and the small premixed burners (C), which are the pilot burners of the annular combustion chamber, are located alternately relative to one another and at a uniform distance apart. Both the main burners (s) and the pilot burners (C) enter into a sin- gle annular front wall (10). (Fig. 6)

Affiliated with

Also associated with

Rating

Combustion chamber of a gas turbine does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Combustion chamber of a gas turbine, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Combustion chamber of a gas turbine will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFCA-PAI-O-1873987