Gas turbine group

Details Gas turbine group Gas turbine group

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 6/00 (2006.01) F01D 1/18 (2006.01) F01D 9/02 (2006.01) F23R 3/00 (2006.01) F23R 3/02 (2006.01) F23R 3/42 (2006.01) F23R 3/58 (2006.01)

Patent

CA 2105692

ABSTRACT OF THE DISCLOSURE In a gas turbine group, the combustion chamber is placed embodied as an annular combustion chamber (1) between two fluid-flow engines (2, 3). In the normal case, the fluid-flow engine (2) located upstream of the annular combustion chamber (1) is a compressor (2b) and the fluid-flow engine (3) located downstream of the annular combustion chamber (1) is a turbine. The fluid- flow engine located downstream of the annular combus- tion chamber (1) in this case has no first row of guide blades, but its blading begins immediately with a row (6) of turbine blades. The latter is subjected to the swirl from the fluid-flow engine (2) located upstream of the annular combustion chamber (1). The swirl itself is conserved over the entire length of the annular combustion chamber (1), it being the case that owing to the swirl the gas flow executes a helical motion in the axial flow direction of the annular combustion chamber (1). (sole figure)

Affiliated with

Also associated with

Rating

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

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

Rate now

Comments { 0 }

Profile ID: LFCA-PAI-O-1555473