Patent ID: 11971052
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. A gas turbine engine comprising:
propulsor means for providing propulsion;
first compression means for compressing airflow from the propulsor means;
second compression means for compressing airflow from the first 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 in response to expanding airflow from the second compression means;
second expansion means for driving the input of the reduction means in response to expanding airflow from the first expansion means;
wherein 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, the first expansion means includes a plurality of arrays of rotor blades arranged in a plurality of expansion stages, and the first compression means includes a greater number of compression stages than a total number of the expansion stages of the first expansion means; and
wherein 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, and the factor (F) is between 1.19 and 1.55 for at least two of the arrays of the rotor blades of the first compression means.