SYSTEM AND METHOD FOR MEASUREMENT OF FAN BLADE TIP CLEARANCE FOR A TURBINE ENGINE

SYSTEM AND METHOD FOR MEASUREMENT OF FAN BLADE TIP CLEARANCE FOR A TURBINE ENGINE

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 bla...

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Bibliographische Detailangaben
Hauptverfasser: Ganiger, Ravindra Shankar, P, Nagamohan G, Shankar, Subramanya, Petkar, Kirti Arvind
Format: Patent
Sprache:eng
Schlagworte:
MEASURING
MEASURING ANGLES
MEASURING AREAS
MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
MEASURING LENGTH, THICKNESS OR SIMILAR LINEARDIMENSIONS
PHYSICS
TESTING
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Beschreibung
Zusammenfassung: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.