Patent ID: 11939876
Assignee: PRATT & WHITNEY CANADA CORP.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A system for an aircraft, comprising:
a gas turbine engine including an inlet and a compressor section, a flowpath projecting radially inward into the gas turbine engine from the inlet and extending through the compressor section; and
a sensor system comprising a plurality of static pressure sensors at least partially within the flowpath, the sensor system configured to determine a total pressure characteristic within the flowpath using the plurality of static pressure sensors;
wherein the sensor system is further configured to
determine a static pressure characteristic at a first location within the flowpath using the plurality of static pressure sensors; and
process the static pressure characteristic to determine the total pressure characteristic at a second location within the flowpath that is downstream of the first location.