COMPRESSOR BLADE FOR GAS TURBINE ENGINE

摘要

A compressor blade for a gas turbine engine is disclosed. The compressor blade may have a root configured to engage a hub of the gas turbine engine, and an airfoil radially extending a distance from the root to a tip. The airfoil may have a suction side, a pressure side, a leading edge connecting the suction and pressure sides, and a trailing edge connecting the suction and pressure sides opposite the leading edge. The distance that the airfoil extends from the root to the tip may be divided into a plurality of radially adjacent regions. At least one, but not all, of the plurality of radially adjacent regions away from the base and the tip may have a substantially constant thickness.

主权项

1. A compressor blade for a gas turbine engine, comprising:
a root configured to engage a hub of the gas turbine engine; and an airfoil having a suction side, a pressure side, a leading edge connecting the suction and pressure sides, and a trailing edge connecting the suction and pressure sides opposite the leading edge, the airfoil radially extending a distance from the root to a tip, wherein:
the distance that the airfoil extends from the root to the tip is divided into a plurality of radially adjacent regions; and at least one, but not all, of the plurality of radially adjacent regions away from the base and away from the tip have a substantially constant thickness.