Patent ID: 11859561
Assignee: PRATT & WHITNEY CANADA CORP.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 3:
4. The method of claim 1, comprising:
receiving, at the computing device, a power of an output shaft of the aircraft engine; and
determining, at the computing device, a discharge pressure of air discharged from a compressor of the aircraft engine;
wherein determining the mass air flow includes:
determining the mass airflow based on an overall pressure ratio defined as the discharge pressure over the first inlet total air pressure;
concurrently with determining the mass air flow based on the overall pressure ratio, determining the mass air flow based on the power of the output shaft; and
using the mass air flow from the power of the output shaft to determine the Mach number if the mass air flow based on the overall pressure ratio is unavailable.