Patent ID: 9382806
Filing Date: 2016-07-05
CPC Classification: F01D,F05D

Claim Text:
1. A housing comprising: a radially inner bounding wall; a radially outer bounding wall; a plurality of supporting ribs within a crossflow channel defined by the radially inner and outer bounding walls, the supporting ribs having a leading edge, a trailing edge, and side walls extending between the leading edge and the trailing edge, the side walls directing gas flow traversing the crossflow channel; the radially outer bounding wall having a contour changing in a circumferential direction at least in one section upstream of the supporting ribs; the housing being an intermediate housing of two turbines of a gas engine; wherein an axial position of the bounding wall section or of a bounding wall point of minimal radius of curvature changes in the circumferential direction in such a way that the bounding wall point is positioned maximally upstream at a circumferential position of the leading edge of the supporting ribs, and maximally downstream at a circumferential position of one half pitch between two adjacent supporting ribs of the plurality of supporting ribs; or wherein a radial position of the bounding wall section or of the bounding wall point of minimal radius of curvature changes in the circumferential direction in such a way that the bounding wall point is positioned maximally radially outwardly at a circumferential position of the leading edge of the supporting ribs, and maximally radially inwardly at a circumferential position of one half pitch between two adjacent supporting ribs of the plurality of supporting ribs.