Patent ID: 9243963
Filing Date: 2016-01-26
CPC Classification: G01K

Claim Text:
1. A gas turbine engine comprising a total temperature probe, the total temperature probe comprising: a hollow elongate shroud defined by a shroud wall that envelops a first cavity, the shroud wall comprising an inner skin and an outer skin which enclose a second cavity therebetween, the inner skin and the outer skin being separated by a constant distance; and a temperature sensor mounted in the first cavity, wherein the total temperature probe is disposed inside of the gas turbine engine and, in use, fluid flow for the gas turbine engine is received into the first cavity, passes through at least one aperture in the inner skin into the second cavity and thence passes out of the shroud through at least one aperture in the outer skin, such that heat conduction across the inner skin is minimal, the at least one aperture in the inner skin being axially and/or circumferentially displaced from the at least one aperture in the outer skin.