US 12,326,091 B2
Guide vane arrangement for a turbomachine, compressor module, and turbomachine
Alexander Halcoussis, Munich (DE); and Harsimar Sahota, Munich (DE)
Assigned to MTU AERO ENGINES AG, Munich (DE)
Appl. No. 18/018,073
Filed by MTU AERO ENGINES AG, Munich (DE)
PCT Filed Jul. 29, 2021, PCT No. PCT/DE2021/100650
§ 371(c)(1), (2) Date Jan. 26, 2023,
PCT Pub. No. WO2022/022780, PCT Pub. Date Feb. 3, 2022.
Claims priority of application No. 10 2020 209 586.8 (DE), filed on Jul. 30, 2020.
Prior Publication US 2023/0265766 A1, Aug. 24, 2023
Int. Cl. F01D 17/16 (2006.01); F01D 5/14 (2006.01); F04D 29/56 (2006.01)
CPC F01D 17/162 (2013.01) [F01D 5/143 (2013.01); F04D 29/563 (2013.01); F05D 2250/713 (2013.01)] 16 Claims
OG exemplary drawing
 
1. A guide vane for arrangement in a gas duct of a turbomachine, comprising:
a guide vane blade; and
an outer platform which, relative to a longitudinal axis of the turbomachine, is arranged radially on an outside on the guide vane blade,
wherein the outer platform delimits the gas duct with an inner wall surface radially to the outside,
wherein the inner wall surface has a curved profile with an inflection point when viewed in an axial section, the inner wall surface having:
a concave curvature in a first axial section which is upstream from the inflection point with respect to a flow through the gas duct, and
a convex curvature in a second axial section which is arranged downstream from the inflection point with respect to the flow through the gas duct
wherein the guide vane is adjustable to set an inflow angle,
wherein the guide vane is configured to be rotatably mounted about a guide vane rotation axis passing through the outer platform,
wherein the inflection point is located upstream of the guide vane rotation axis, and
wherein the curved profile of the inner wall surface is characterized by a decreasing function, with respect to a radial distance to an axis of the turbomachine, between a leading edge of the blade and the inflection point.