Pressure measurement system and method for operating same

A gas turbine engine for an aircraft, the gas turbine engine comprising:

• a probe located within a fluid flow path of the gas turbine engine, the probe comprising:
• a probe body extending lengthwise along a probe axis, the probe body defining an internal cavity of the probe;
• a plurality of sensor inlet ports extending through the probe body and configured to receive a sensed fluid flow, the plurality of sensor inlet ports axially spaced along the probe axis;
• and
• a plurality of probe conduits, each probe conduit of the plurality of probe conduits coupled to a respective sensor inlet port of the plurality of sensor inlet ports and extending from the respective sensor inlet port to an exterior of the probe body;
• and
• a heated-gas source in fluid communication with the probe and configured to supply a heated gas flow to one or both of:
• the plurality of sensor inlet ports via the plurality of probe conduits;
• and
• an interior of the probe body outside of the plurality of probe conduits.

A method for operating a measurement system for an aircraft gas turbine engine, the method comprising:

• receiving a sensed fluid flow with a plurality of sensor inlet ports extending through a probe body of a probe, the probe body defining an internal cavity of the probe;
• and
• supplying a heated gas flow, with a heated-gas source in fluid communication with the probe, to one or both of:
• the plurality of sensor inlet ports via a plurality of probe conduits, each probe conduit of the plurality of probe conduits coupled to a respective sensor inlet port of the plurality of sensor inlet ports and extending from the respective sensor inlet port to an exterior of the probe body;
• and
• an interior of the probe body outside of the plurality of probe conduits.