公开(公告)号：US20240377193A1

公开(公告)日：2024-11-14

申请号：US18339370

申请日：2023-06-22

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Subramanya Shankar ,  Kirti Arvind Petkar ,  Nagamohan G P ,  Ravindra Shankar Ganiger

IPC: G01B21/16

Abstract: A gas turbine engine includes a fan assembly, a compressor section, a combustor section, and a turbine section in serial flow arrangement, and defining an engine centerline. Sets of fan blades within the fan assembly can be rotatably driven about the engine centerline within a casing wall. A fan blade tip clearance is defined as a gap between the set of fan blades and the fan casing assembly. A clearance measurement system including a pad with one or more integrated sensors provides for measuring the gap.