US 12,286,886 B2
Turbine assembly with spring biased clearance sensor mount
Brett Hartnagel, Indianapolis, IN (US); and Brandon R. Snyder, Indianapolis, IN (US)
Assigned to Rolls-Royce North American Technologies Inc., Indianapolis, IN (US)
Filed by Rolls-Royce North American Technologies Inc., Indianapolis, IN (US)
Filed on Sep. 25, 2023, as Appl. No. 18/372,437.
Prior Publication US 2025/0101875 A1, Mar. 27, 2025
Int. Cl. F01D 11/20 (2006.01); F01D 11/00 (2006.01)
CPC F01D 11/20 (2013.01) [F01D 11/001 (2013.01); F01D 11/005 (2013.01); F05D 2270/821 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A turbine assembly adapted for use in a gas turbine engine, the turbine assembly comprising
a bladed rotor mounted for rotation about an axis of the gas turbine engine,
a case assembly including an inner case that extends circumferentially around the bladed rotor to define an outer boundary of a gas path of the turbine assembly to block combustion products from moving through the gas path of the turbine assembly without interaction with blades included in the bladed rotor and an outer case that extends circumferentially around the inner case and is spaced radially outward of the inner case to define an annular plenum therebetween, and
a tip clearance system including a tip clearance sensor located in the annular plenum to engage the inner case radially outward of the gas path of the turbine assembly and configured to monitor a tip clearance formed between the bladed rotor and the inner case during operation of the gas turbine engine and a sensor mount that extends between the outer case and the tip clearance sensor to apply a bias force to the tip clearance sensor to urge the tip clearance sensor radially inward into engagement with the inner case and maintain the engagement between the tip clearance sensor and the inner case,
wherein the inner case is located radially between a terminal end of the tip clearance sensor and the blades of the bladed rotor.