Multi-stage blade system
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United States of America Patent
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Aug 11, 1998
Grant Date -
N/A
app pub date -
Mar 14, 1997
filing date -
Apr 1, 1996
priority date (Note) -
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status (Latency Note)
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Abstract
A multi-stage blade system of an axial flow turbo machine includes a wall (10, 11), which is on either the rotor side, the stator side, or both, which bounds the flow through the channel through which flow passes. The wall is provided, immediately at the outlet of the rotor blades (La1, La2, La3), with a kink angle (A, AA). This kink angle (A, AA) is dimensioned such that the outlet flow from the rotor blades is homogenized in terms of the total pressure and outlet flow angle. The wall (10, 11) is also provided with an opposing kink angle (B, BB) at least approximately in the inlet region of the stator blades (Le2, Le3) of the following stage. This allows the labyrinth mass flow to be reduced in blade systems having covering strip sealing.
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