US 11,773,745 B2
Pressure and temperature sensors and methods of controlling ice accretion on pressure and temperature sensors
Andrew Holl, Lakeville, MN (US); Scott Wigen, Eagan, MN (US); Scott D. Isebrand, Minneapolis, MN (US); Robert Edward Sable, Lakeville, MN (US); and Brian Boyd, Burnsville, MN (US)
Assigned to ROSEMOUNT AEROSPACE INC., Burnsville, MN (US)
Filed by Rosemount Aerospace Inc., Burnsville, MN (US)
Filed on Feb. 28, 2020, as Appl. No. 16/805,468.
Prior Publication US 2021/0270146 A1, Sep. 2, 2021
Int. Cl. F01D 21/00 (2006.01); F01D 25/02 (2006.01); G01K 1/08 (2021.01); G01K 1/20 (2006.01); G01K 13/02 (2021.01); B33Y 80/00 (2015.01)
CPC F01D 21/003 (2013.01) [F01D 25/02 (2013.01); G01K 1/08 (2013.01); G01K 1/20 (2013.01); G01K 13/02 (2013.01); B33Y 80/00 (2014.12); F05D 2220/323 (2013.01); F05D 2220/3217 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A sensor, comprising:
an airfoil body defining a sensor axis and having a leading edge, a trailing edge, an ice accretion feature and a tip surface extending from the ice accretion feature to the trailing edge;
a heater element extending axially through the airfoil body between the leading edge and the trailing edge of the airfoil body; and
a temperature probe extending axially through the airfoil body between the heater element and the trailing edge of the airfoil body, wherein the heater element is axially overlapped by the ice accretion feature to accrete ice chordwise forward of the tip surface;
wherein the ice accretion feature extends from the leading edge of the airfoil body to an ice accretion feature terminus that is located chordwise between the heater element and the temperature probe.