This fin tip position measurement method comprises: a jig installation step for installing a jig having a flat measurement surface expanded in a circumferential direction and an axial direction to a tip of at least one among a plurality of seal fins that protrude in a radial direction with respect to an axial line, extend in the circumferential direction, and are arranged in a direction in which the axial line extends; a first measurement step for measuring a distance from the axial line to the measurement surface by scanning the measurement surface with a laser beam; and a first calculation step for calculating a distance from the axial line to the tip of the seal fin by adding a radial dimension of the jig to the distance to the measurement surface.

The disclosed technology concerns an aircraft turbomachine part comprising a part body drilled with at least one cavity open to the outside and at least one conduit joining the cavity on the one hand and leading to the outside on the other hand. Each cavity receives a pressure sensor, and the conduit corresponds to the cavity guides the cables connected to the sensor to the outside of the part body. The part is an aircraft turbomachine vane.

A depolluted test bench (I) for a turbomachine includes a channeled air duct with an air inlet and an air outlet to allow a flow of air between the air inlet and the air outlet. The channeled air duct includes a test chamber) for testing a turbomachine, the test chamber being located between the air inlet and the air outlet. A depolluting system is positioned in the air duct to depollute an air flow generated at least in part by a test of said turbomachine in the test bench. Control means control the depolluting system to allow the depolluting system to be switched on or off when a test of the turbomachine is started or stopped.

The present invention relates to a method for characterizing a coating, in which method a mass and/or a volume of a basic body is/are measured prior to coating; a mass and a volume of the basic body with the applied coating are measured; for characterizing the coating, a density of the coating is determined from the volume and mass measurements; wherein the volume is optically measured.

A method for testing platforms (e.g., live, virtual, and/or constructive platforms associated with autonomous aircraft systems and their component subsystems) in a live/virtual/constructive (LVC) environment. In embodiments, the method includes determining, via a testbed engine, the development state of a platform component under test. The method includes retrieving a test to be executed, the test including test conditions to be applied to the component. The method includes determining whether the component is enabled to respond to the test conditions. The method includes, if the component is enabled to respond to the test conditions, executing the test while monitoring the component to detect a first output response and a second output response. The method includes identifying, via the testbed engine, at least one change in the development state of the component by comparing the first and second output responses.

A condensation irradiation system is disclosed comprising an electromagnetic radiation emitter mounted on a locating structure, the locating structure being arranged in use to position the radiation emitter so as radiation emitted therefrom travels through a condensation detection region adjacent an upstream side of a gas turbine engine fan.

The method allows to control a test apparatus for a gas turbine engine; WI values of one or more tentative fuel gas mixtures are predicted by calculations and the predicted WI values are used for setting the composition of a fuel gas mixture to be supplied to a combustor of a gas turbine engine under test. The test apparatus comprises: a first supply flow line for fuel gas; a second supply flow line for inert gas; a mixer with a first inlet for fuel gas and a second inlet for inert gas, and with an outlet for supplying the mixture of fuel gas and inert gas to the combustor; a set of meters; and a flow control device for the inert gas.

A method of treating a component adapted for use in a gas turbine engine is described herein. The component may comprise ceramic matrix composite materials. The treatment to the ceramic matrix composite component may reduce or eliminate the wear or damage of crack propagation in the ceramic matrix composite component.

A resonant frequency testing system for airfoils comprises a broach block, a clamp, an acoustic speaker, a laser vibrometer, and a control processor assembly. The broach block has a slot disposed to receive the airfoil in an airfoil location. The clamp has a torque-actuated shutoff, and is disposed to lock the airfoil in the broach block slot under a fixed clamping force. The acoustic sensor is disposed adjacent the airfoil location to emit sonic pulses, and the laser vibrometer is oriented towards the airfoil location to sense vibration signatures of the airfoil when excited by the sonic pulses. The control processor assembly is configured to control the acoustic speaker and laser vibrometer, to decompose the sensed vibration signatures into resonant frequencies of the airfoil, and to store the resonant frequencies in a digital storage database, correlated with a unique ID corresponding to the airfoil.

A test cell for an aircraft turbojet, wherein the test cell comprises a U-shaped configuration, with a passageway in the form of an elongated corridor, an inlet chimney, and an outlet chimney. The corridor includes a securing area with a securing arm for holding the turbojet during its test. The passageway furthermore reveals an upstream shutter and a downstream shutter, the two shutters including one pivoting flap or a series of pivoting flaps. In the event of a fire, the shutters close due to autonomous return means. Gravity allows the flap(s) to come down to the closed position and to confine the turbojet in order to rapidly stifle the fire.