Gas turbine engine airfoil shaped component

Abstract

An apparatus comprises a gas turbine engine having a compressor for increasing a total pressure of a working fluid prior to delivery to a combustor for mixing with fuel. The compressor has a plurality of airfoil members that extend between a first flow surface and a second flow surface. The plurality of airfoil members have a first camber shape at a tip portion that provides a cumulative integral according to the relationship 0.4 < ∫ 0 1 ⁢ [ ∫ 0 x ⁢ β ′ ⁢ dx ] ⁢ dx ∫ 0 1 ⁢ β ′ ⁢ dx ≤ 0.5 where x is chord location, β ′ = β i - β β i - β e , βi is inlet metal angle, βe is exit metal angle, and β is a camber angle at a given chord location.

Dependencies are inferred from the claim text.