Patent attributes
A gas turbine engine according to an aspect of the present disclosure includes, among other things, propulsor means, first compression means, second compression means, reduction means for reducing a rotational speed of an output that drives the propulsor means relative to an input, first expansion means for driving the second compression means, and second expansion means for driving the input of the reduction means. The first compression means includes a plurality of arrays of rotor blades and a plurality of arrays of stator vanes arranged in a plurality of compression stages. A factor (F) is defined as a total number of the rotor blades in an array of the plurality of arrays divided by a total number of the stator vanes in an adjacent array of the plurality of arrays. The factor (F) is between 1.19 and 1.55 for at least two of the arrays of the rotor blades.
