GAS TURBINE ENGINE BLADE PLATFORM MODIFICATION

摘要

A gas turbine engine compressor blade includes an airfoil and a root section connected to a blade platform therebetween and an at least partially curved cropped corner of the blade platform. The corner shape and size may avoid resonance of blade during engine operation. Corner may be J-shaped including a straight section extending from pressure side edge towards suction side edge of platform and curved section extending from straight section to uncropped portion of platform trailing edge of the platform. A method of designing the cropped corner includes choosing shapes sizes of the cropped corner for numerically analyzing and determining shape and size for cropped corner using numerical model to iteratively numerically analyze aerodynamically cropped platform with different shapes and sizes of cropped corner. Numerical model may be validated with engine or component testing of blade having a cropped platform with at least one of the shapes and sizes.

主权项

1. A gas turbine engine compressor blade comprising:
an airfoil and a root section connected to a blade platform therebetween, the airfoil extending in a chordwise direction between airfoil leading and trailing edges, and an at least partially curved cropped corner of the blade platform.