Patent ID: 11879386
Assignee: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES, INC.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 6:
7. The method of claim 5, wherein providing the axial compressor includes
providing a set of standard axial compressor stages that each include a rotor having a plurality of blades configured to rotate about the axis and a stator having a plurality of stator vanes, wherein the set of standard axial compressor stages ranges from a first compressor stage to an Nth compressor stage where N is a natural number greater than 1 and whereby a radial length of the plurality of blades and a radial length of the stator vanes on each compressor stage included in the standard compressor stages gradually decreases in size from the first compressor stage to the Nth compressor stage,
selecting an initial axial compressor stage from the set of standard axial compressor stages for the gas turbine engine based on the predetermined inlet corrected flow, and
adding any number of sequential axial compressor stages from the set of standard axial compressor stages downstream of the initial axial compressor stage based on the predetermined pressure ratio.