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

Claim 0:
1. A method comprising:
selecting an initial turbine stage from a set of standard turbine stages based on an exit corrected flow output of an axial compressor, wherein each standard turbine stage includes a single turbine rotor having a plurality of turbine blades and a subset of standard turbine vane rings associated with the single turbine rotor,
selecting an initial turbine vane ring from the subset of standard turbine vane rings included in the initial turbine stage based on the exit corrected flow output of the axial compressor,
selecting a second turbine stage from the set of standard turbine stages based on a predetermined power demand, wherein the second turbine stage is any turbine stage from the set of standard turbine stages that is greater in size than the selected initial turbine stage,
selecting a second turbine vane ring from the subset of standard turbine vane rings included in the second turbine stage based on exit conditions of the initial turbine stage, and
locating the initial turbine vane ring downstream of the axial compressor, locating an initial turbine rotor associated with the initial turbine stage directly downstream of the initial turbine vane ring, locating the second turbine vane ring directly downstream of the initial turbine rotor, and locating a second turbine rotor associated with the second turbine stage directly downstream of the second turbine vane ring to provide a turbine for a gas turbine engine.