Flow channel for a turbomachine
AssigneeMTU Aero Engines AG
InventorGuenter Ramm
Life of this patent
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Abstract
The present invention relates to a method for designing a flow channel for a turbomachine, in particular a gas turbine that comprises a guide vane cascade having a plurality of guide vanes, which are distributed in the peripheral direction, and flow passages, each of which is bounded by two successive guide vanes, and a support rib arrangement having at least one support rib, wherein a design of one of the flow passages is adapted to this support rib, that it is situated downstream of, in order to reduce a pressure loss and/or a vibrational stimulation.
Claims8
A method for designing a flow channel for a turbomachine that includes a guide vane cascade having a plurality of guide vanes, which are distributed in the peripheral direction, and flow passages, each of which is bounded by two successive guide vanes, and a support rib arrangement having at least one support rib, wherein a layout of one of the flow passages, which is situated downstream of this support rib, is adapted to reduce a pressure loss and/or a vibrational stimulation.
Dependencies are inferred from the claim text.