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Geared Turbofan Engine Having a Reduced Number of Fan Blades and Improved Acoustics (2019)

Baltas, Constantine ; Gilson, Jonathan

In: CASI

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Publication Date: 2019-07-20

Description: A rotor blade comprises an airfoil extending radially from a root section to a tip section and axially from a leading edge to a trailing edge, the leading and trailing edges defining a curvature therebetween. The curvature determines a relative exit angle at a relative span height between the root section and the tip section, based on an incident flow velocity at the leading edge of the airfoil and a rotational velocity at the relative span height. In operation of the rotor blade, the relative exit angle determines a substantially flat exit pressure ratio profile for relative span heights from 75% to 95%, wherein the exit pressure ratio profile is constant within a tolerance of 10% of a maximum value of the exit pressure ratio profile.

Keywords: Aircraft Propulsion and Power

Format: application/pdf

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