Patent ID: 8806924

Claim:
A sealing head for an installation configured to perform fluid tests on an aircraft turbine engine part including a circuit for flowing of a gas flow, the sealing head comprising: a sealing element following a closed line and interiorly crossed by a passage for letting through a gas flow, the sealing element including a sealing surface configured to come into contact with a part to be tested, at an aperture of the part to be tested configured to be fed with the gas flow; means for centering the sealing element with respect to the aperture of the part to be tested, the centering means being firmly attached to the sealing element and protruding towards a front of a sealing surface having an outer portion surrounding the centering means, and a base including holes and connecting means laid out between the base with holes and the sealing element, the head configured to allow circulation of the air flow, from the rear to the front, successively through the base with holes, the connecting means and the passage defined by the sealing element, wherein the connecting means is configured to allow a displacement of the centering means with respect to the perforated base.