Flow duct structure for reducing secondary flow losses in a blad

Fluid reaction surfaces (i.e. – impellers) – Specific blade structure – Radial flow devices

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Details

415DIG1, 415181, 416193A, 416244A, F01D 502

Patent

active

044654332

ABSTRACT:
A bladed flow duct, for example in an axial flow turbo engine, is defined between two adjacent blades and the respective duct floor. In order to reduce secondary flow losses, the flow duct is provided with an arched zone (13, 13') projecting from the duct floor (10, 10') and extending along a portion of the suction side of the adjacent blade wall for producing a pressure rise or a reduction in the transverse pressure gradient over a relatively long forward and/or central portion of the duct as viewed in the flow direction (17) from the entrance end (21) to the exit end (22) of the duct. For this purpose the arched zone (13, 13') has a number of sections in the flow direction (17). A first section (23) starting in the entrance side of the duct is substantially or completely concave for causing said pressure rise. A second or central section (24) forms a convex peak and particularly a duct throat near the exit side of the duct. A third section (25) slopes down to the exit end (22). The sections (23, 24, 25) fall off or drop continuously or smoothly in the direction (16) across the flow direction (17) from the suction side of a blade (11)toward the pressure side of the respective opposite blade (12) but spaced from the opposite blade. This teaching is equally useful in rotor wheels as well as in stator guide rings.

REFERENCES:
patent: 2735612 (1956-02-01), Hausmann
patent: 2918254 (1959-12-01), Hausammann
patent: 2920864 (1960-01-01), Lee
patent: 3529631 (1970-09-01), Riollet
patent: 4135857 (1979-01-01), Pannone et al.
patent: 4208167 (1980-06-01), Yasugahira et al.
patent: 4420288 (1983-12-01), Bischoff

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