FIELD: machine building.
SUBSTANCE: diffuser-distributor assembly intended to be installed at a compressor output in a turbine comprises a distributor. The distributor includes two, in essence, cylindrical walls: a radial inner one and a radial outer one. The walls are connected by radial blades. The distributor walls are extended to the downstream part beyond the radial blades. Radial clearance between the walls is circumferentially variable downstream the blades so that in essence to be minimal in the blades extension and maximal between the blades. The clearance is circumferentially variable up to the downstream end of the downstream walls of the distributor. Subject of the invention is also a turbomachine such as turbojet engine, turboprop engine or helicopter engine comprising the assembly described above.
EFFECT: invention allows for the decrease of inhomogenity of air flow at the inlet of a combustion chamber.
11 cl, 13 dwg
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| TURBOMACHINE | 2011 |
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