POSITION DER LOKALEN MAXIMALEN DICKENVERTEILUNG EINES VERDICHTERROTORBLATTES

• Main Authors: VOGIATZIS, Constantinos, GEBRE-GIORGIS, Yoseph, HAYES, Jeffrey, MCNAMEE, Michael R, NOLCHEFF, Nick, GUNARAJ, John A
• Format: Patent
• Language: English; French; German
• Published: 11.10.2023
• Subjects: BLASTING; ENGINE PLANTS IN GENERAL; HEATING; LIGHTING; MACHINES OR ENGINES IN GENERAL; MECHANICAL ENGINEERING; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES; NON-POSITIVE DISPLACEMENT PUMPS; POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS; STEAM ENGINES; WEAPONS

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.