POSITION DER LOKALEN MAXIMALEN DICKENVERTEILUNG EINES VERDICHTERROTORBLATTES

A rotor blade (500) for a compressor of a gas turbine engine includes an airfoil. The airfoil has a span that extends from 0% at the root to 100% at the tip and a mean camber line that extends from a leading edge to a trailing edge. The airfoil has a location of local maximum thickness defined as a...

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Bibliographic Details
Main Authors VOGIATZIS, Constantinos, GEBRE-GIORGIS, Yoseph, HAYES, Jeffrey, MCNAMEE, Michael R, NOLCHEFF, Nick, GUNARAJ, John A
Format Patent
LanguageEnglish
French
German
Published 11.10.2023
Subjects
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Summary:A rotor blade (500) for a compressor of a gas turbine engine includes an airfoil. The airfoil has a span that extends from 0% at the root to 100% at the tip and a mean camber line that extends from a leading edge to a trailing edge. The airfoil has a location of local maximum thickness defined as a ratio of a first arc distance along the mean camber line between the leading edge and a position of the local maximum thickness to a total arc distance along the mean camber line from the leading edge to the trailing edge. A value of the ratio increases from the root to a first position value (542), decreases from the first position value to a second position value and increases from the second position value (544) to the tip (546). The first position value (542) is at a spanwise location within 20% to 50% of the span.
Bibliography:Application Number: EP20190210489