Patent ID: 11898503
Assignee: PRATT & WHITNEY CANADA CORP.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A method for determining an engine temperature for a gas turbine engine, comprising:
determining an inner-turbine temperature based on a low-pressure spool output power, an engine output power, an inlet mass flow and an exhaust temperature;
determining a vane mass flow and a compressor mass flow based on the inlet mass flow;
determining a high-pressure compressor load based on the compressor mass flow, a high-pressure compressor temperature and a high-pressure compressor delivery temperature;
determining an estimated combustor temperature based on the high-pressure compressor load, the inner-turbine temperature and the vane mass flow;
determining a corrected vane mass flow based on the estimated combustor temperature;
comparing the corrected vane mass flow to a reference vane mass flow to obtain a mass flow correction factor;
iteratively correcting the mass flow correction factor using an adjusted inlet mass flow until a mass flow correction condition is satisfied; and
when the mass flow correction factor satisfies the mass flow correction condition, outputting, via a controller associated with the gas turbine engine, a signal to assign the estimated combustor temperature as the engine temperature for assisting at least one of the controller and an operator of the gas turbine engine in modulating at least one of a fuel flow provided to the gas turbine engine, modulating a position and orientation of variable geometry mechanisms within the gas turbine engine, and modulating a bleed level of the gas turbine engine.