US 11,939,876 B2
Gas turbine engine sensor system with static pressure sensors
Damien Le Pape, Montreal (CA); and Mark Cunningham, Montreal (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on Jul. 29, 2022, as Appl. No. 17/876,854.
Prior Publication US 2024/0035393 A1, Feb. 1, 2024
Int. Cl. F01D 21/00 (2006.01)
CPC F01D 21/003 (2013.01) [F05D 2220/323 (2013.01); F05D 2260/30 (2013.01); F05D 2270/3011 (2013.01)] 19 Claims
OG exemplary drawing
 
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.