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US 12,735,987 B2Granted
Turbofan engine having a low-pressure turbine
AssigneeMTU Aero Engines AG
InventorsMarkus Brettschneider, Roman Seiband, Petra Kufner, Jens Truebenbach
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Abstract
A turbofan engine having a low-pressure turbine that has at last four stages, at least one of the four stages having a transonic airfoil cascade is provided.
Claims21
A turbofan engine comprising:
- a low-pressure turbine having at least four stages, at least one of the four stages having a transonic airfoil cascade,
- wherein the last downstream airfoil cascade is a transonic airfoil cascade and at least one of the airfoil cascades upstream from the downstream airfoil cascades is not transonic.
A turbofan engine comprising:
- a low-pressure turbine having at least four stages, at least one of the four stages having a transonic airfoil cascade,
- a transonic airfoil of the transonic airfoil cascade having a suction side surface including a linear portion having a linear profile when viewed in a sectional plane of the airfoil,
- the linear profile in the sectional plane of the airfoil extending radially over at least 10% of a radial length of the transonic airfoil.
A turbofan engine comprising:
- a low-pressure turbine having at least four stages, at least one of the four stages having a transonic airfoil cascade,
- a transonic airfoil of the transonic airfoil cascade having a suction side surface including a linear portion having a linear profile when viewed in a sectional plane of the airfoil,
- the linear profile having a curvature when viewed in the sectional plane of the airfoil, the curvature deviating from a linear shape by at most 5%.
A turbofan engine comprising:
- a low-pressure turbine having at least four stages, at least one of the four stages having a transonic airfoil cascade,
- a transonic airfoil of the transonic airfoil cascade having a suction side surface including a linear portion having a linear profile when viewed in a sectional plane of the airfoil,
- a plurality of transonic airfoil cascades each having a respective transonic airfoil having a respective linear portion, wherein a respective total area of the respective linear portion increases from each of the plurality of airfoil cascades to a next airfoil cascade of the plurality of airfoil cascades in the downstream direction.
Dependencies are inferred from the claim text.