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

Claim 2:
3. A method of assembling a gas turbine engine, the method comprising:
providing an axial compressor including a predetermined number of axial compressor stages based on an engine performance capability for the gas turbine engine, the axial compressor having an exit corrected flow output,
providing a set of standard turbine stages whereby each standard turbine stage includes a single turbine rotor having a plurality of turbine blades configured to rotate about an axis and a subset of standard turbine vane rings associated with the single turbine rotor and including a plurality of turbine vanes, wherein the set of standard turbine stages ranges from a first turbine stage to an Mth turbine stage where M is a natural number greater than 1, and wherein each of the subset of standard turbine vane rings ranges from a first turbine vane ring to a Zth turbine vane ring where Z is a natural number greater than 1 and whereby a throat area of the plurality of turbine vanes of each turbine vane ring included in the subset of standard turbine vane rings gradually increases from the first turbine vane ring to the Zth turbine vane ring,
selecting an initial turbine stage from the set of standard turbine stages based on the exit corrected flow output of the axial compressor,
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,
locating the initial turbine vane ring downstream of the axial compressor, and
locating an initial turbine rotor associated with the initial turbine stage directly downstream of the initial turbine vane ring to provide a turbine for the gas turbine engine.