THROAT DISTRIBUTION FOR A ROTOR AND ROTOR BLADE HAVING CAMBER AND LOCATION OF LOCAL MAXIMUM THICKNESS DISTRIBUTION

A rotor blade for a compressor of a gas turbine engine includes an airfoil extending from a root to a tip and having a leading edge and a trailing edge. 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 the leading edge to the trailin...

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Bibliographic Details
Main Authors Nolcheff, Nick, Gebre-Giorgis, Yoseph, Gunaraj, John A, Hanson, David Richard, Hayes, Jeffrey, Repp, John
Format Patent
LanguageEnglish
Published 21.05.2020
Subjects
BLASTING
HEATING
LIGHTING
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT PUMPS
POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS
PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
WEAPONS
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Summary:A rotor blade for a compressor of a gas turbine engine includes an airfoil extending from a root to a tip and having a leading edge and a trailing edge. 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 the leading edge to the trailing edge. The airfoil has a total camber distribution that increases from the root to a maximum value of total camber between 5% of the span and 20% of the span.
Bibliography:Application Number: US201816198266