FIELD OF DISCLOSURE

The present invention generally relates to gas turbine engine airfoil shaped components such as vanes and rotatable blades, and more particularly, but not exclusively, to compressor blades and vanes.

BACKGROUND

Improving the performance of gas turbine engines remains an area of interest. Some existing systems have various shortcomings relative to certain applications. Accordingly, there remains a need for further contributions in this area of technology.

SUMMARY

According to one aspect, an apparatus comprises a gas turbine engine including 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<∫01⁢[∫0x⁢β′⁢dx]⁢dx∫01⁢β′⁢dx≤0.5
where x is chord location,

β′=βi-ββi-βe,
βiis inlet metal angle, βeis exit metal angle, and β is a camber angle at a given chord location.

Other aspects and advantages will become apparent upon consideration of the following detailed description and the attached drawings wherein like numerals designate like structures throughout the specification.

