| 摘要 |
An air-guiding system between a compressor and a turbine of a gas turbine engine includes an air chamber ( 5 ) being delimited by the inner casing of the combustion chamber ( 4 ) and first and second seals ( 7, 8 ) towards the rotating compressor shaft cone ( 12 ). An axial thrust compensation chamber ( 6 ) is adjoined to said second seal ( 8 ) and respectively loaded with the turbine cooling air (B', C) branched-off from the compressor air. Due to the higher pressure in said axial thrust compensation chamber with respect to said air chamber, the high axial forces are compensated. The air flowing back into said air chamber through said second seal ( 8 ) is guided and separated from components ( 10 ) and flowing-off air masses by a flow-guiding means ( 16 ) in said air chamber. This results in a high rinsing effect, a reduced vortex formation and finally, a reduced thermal stress.
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