F - Mech Eng,Light,Heat,Weapons – 02 – C
Patent
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)
Hausermann Alfred
Wettstein Hans
Asea Brown Boveri Ltd.
Swabey Ogilvy Renault
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