US 12,332,125 B2
Method and apparatus to measure gas turbine compressor exit temperature
Martin Drolet, Saint-Amable (CA); and Sebastien Lortie, Montreal (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on Jul. 11, 2023, as Appl. No. 18/350,378.
Prior Publication US 2025/0020521 A1, Jan. 16, 2025
Int. Cl. G01K 13/024 (2021.01); F02C 7/32 (2006.01); G01K 1/14 (2021.01); G01K 7/02 (2021.01)
CPC G01K 13/024 (2021.01) [F02C 7/32 (2013.01); G01K 1/14 (2013.01); G01K 7/02 (2013.01); F05D 2260/83 (2013.01)] 14 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a compressor section, a combustor and a turbine section;
the compressor section having a compressor section exit upstream of the combustor; and
a probe extending through a compressor exit housing surrounding said compressor section exit, said probe tapping air downstream of said compressor section exit into a probe body having a passage leading to a temperature sensor, and comprising a controlled leakage also allowing air from within the compressor exit housing to leak;
wherein said passage extending to a pressure sensor, and said temperature sensor sensing the temperature of the air upstream of the pressure sensor, the controlled leakage being delivered away from the probe prior to the air reaching the pressure sensor.