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

Claim 0:
1. A method of determining an inlet total air pressure of air at an air inlet of an aircraft engine, the method comprising:
determining, at a computing device, a first parameter indicative of a first inlet total air pressure at the air inlet;
executing, at the computing device, a sequence that includes:
determining, at the computing device, a mass air flow passing through the air inlet based on the first parameter;
determining, at the computing device, a Mach number of air passing through the air inlet based on the mass air flow;
determining, at the computing device, a static air pressure at the air inlet;
determining, at the computing device, an air pressure ratio based on the Mach number, the air pressure ratio defined as a revised inlet total air pressure over an estimated static air pressure at the air inlet;
generating, at the computing device, a subsequent parameter indicative of the revised inlet total air pressure based on the air pressure ratio and the static air pressure; and

substituting, at the computing device, the subsequent parameter for the first parameter;
executing, at the computing device, at least one additional instance of the sequence with the subsequent parameter; and
outputting, at the computing device, the subsequent parameter as the inlet total air pressure.