Patent ID: 11891902
Assignee: PRATT & WHITNEY CANADA CORP.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 13:
14. A gas turbine engine for an aircraft, the gas turbine engine comprising:
an annular fluid flow path disposed about a longitudinal centerline of the gas turbine engine; and
a measurement system comprising:
an instrumentation hub disposed about the longitudinal centerline, the instrumentation hub including at least one probe positioned within the annular fluid flow path; and
a shield hub disposed about the longitudinal centerline and positioned axially adjacent the instrumentation hub, the shield hub including at least one shield configured to be radially aligned with the at least one probe of the instrumentation hub, the shield hub rotatable about the longitudinal centerline independent of the instrumentation hub, the at least one shield axially translatable between a first axial position and a second axial position, the at least one shield in the first axial position axially aligned with the at least one probe and the at least one shield in the second axial position axially separated from the at least one probe.