A method is provided including the steps: —first excitation of the object via a multifrequency signal; —detecting a first response signal of the object at one or multiple measuring points at the object; —transforming the first response signal from a time range into a frequency-dependent range; —selecting one or multiple frequencies, based on the frequency-dependent range; —second excitation of the object based on the selected frequencies; —detecting a second response signal of the object at one or multiple measuring points of the object; —ascertaining a mechanical parameter based on the second response signal.

A life consumption estimation device for estimating life consumption of at least one part of a gas turbine includes: a predicted air temperature information acquisition unit configured to acquire predicted air temperature information regarding a future air temperature; a predicted load information acquisition unit configured to acquire predicted load information regarding a future load of the gas turbine; a gas turbine state quantity estimation unit configured to estimate at least one gas turbine state quantity regarding a future state quantity of the gas turbine, on the basis of predicted air temperature information acquired by the predicted air temperature information acquisition unit and the predicted load information acquired by the predicted load information acquisition unit; and a life consumption estimation unit configured to estimate the life consumption of the at least one part, on the basis of the gas turbine state quantity estimated by the gas turbine state quantity estimation unit.

A life consumption estimation device for estimating life consumption of at least one part of a gas turbine includes: a predicted air temperature information acquisition unit configured to acquire predicted air temperature information regarding a future air temperature; a predicted load information acquisition unit configured to acquire predicted load information regarding a future load of the gas turbine; a gas turbine state quantity estimation unit configured to estimate at least one gas turbine state quantity regarding a future state quantity of the gas turbine, on the basis of predicted air temperature information acquired by the predicted air temperature information acquisition unit and the predicted load information acquired by the predicted load information acquisition unit; and a life consumption estimation unit configured to estimate the life consumption of the at least one part, on the basis of the gas turbine state quantity estimated by the gas turbine state quantity estimation unit.

A measuring device with at least one fluid channel for conveying a measuring fluid, wherein the fluid channel includes at least one inlet for the entry of the measuring fluid into the fluid channel and at least one outlet for the exit of the measuring fluid from the fluid channel. The fluid channel includes a diamond-shaped cross-section and includes a course from the at least one inlet to the at least one outlet over which the measuring fluid entering the fluid channel is deflected by at least 90° before the measuring fluid exits the fluid channel at the at least one outlet.

A sensor assembly includes a mounting portion arranged to support a sensing device, a thermal shunt portion extending from the mounting portion, and a housing portion. The housing portion extends from the thermal shunt portion and is arranged on a side of the thermal shunt portion opposite the mounting portion to limit temperature of a sensor connector fixed to the housing portion of the sensor assembly. Gas turbine engines having sensor assemblies and methods of making sensor assemblies are also described.

A sensor assembly includes a mounting portion arranged to support a sensing device, a thermal shunt portion extending from the mounting portion, and a housing portion. The housing portion extends from the thermal shunt portion and is arranged on a side of the thermal shunt portion opposite the mounting portion to limit temperature of a sensor connector fixed to the housing portion of the sensor assembly. Gas turbine engines having sensor assemblies and methods of making sensor assemblies are also described.

A method and system for diagnosing a condition of an air-breathing aircraft engine are described. The method comprises obtaining a sample of lubricating fluid from the engine, filtering the sample to obtain a plurality of particles from the lubricating fluid, obtaining chemical composition data for the plurality of particles, determining a quantity of volcanic ash in the lubricating fluid by considering each one of the particles as composed partially of volcanic ash and partially of at least one other material and determining a first percentage of surface area of the particles covered by the volcanic ash and a second percentage of the surface area of the particles covered by the at least one other material, the volcanic ash having associated thereto a predetermined chemical composition, and diagnosing a condition of the engine based on the quantity of volcanic ash found in the lubricating fluid.

A method and system for diagnosing a condition of an air-breathing aircraft engine are described. The method comprises obtaining a sample of lubricating fluid from the engine, filtering the sample to obtain a plurality of particles from the lubricating fluid, obtaining chemical composition data for the plurality of particles, determining a quantity of volcanic ash in the lubricating fluid by considering each one of the particles as composed partially of volcanic ash and partially of at least one other material and determining a first percentage of surface area of the particles covered by the volcanic ash and a second percentage of the surface area of the particles covered by the at least one other material, the volcanic ash having associated thereto a predetermined chemical composition, and diagnosing a condition of the engine based on the quantity of volcanic ash found in the lubricating fluid.

The invention relates to a method (1) for monitoring a rotating machine (100) of an aircraft, wherein a measurement signal is acquired from the rotating machine. According to the invention, instantaneous frequencies (f.sub.K(t)) of sinusoidal components of the measurement signal are estimated, and, using a computing module (12), a plurality of successive iterations are carried out in each of which: complex envelopes of the components are updated (C1), parameters of a model of a noise of the signal are updated (C21) on the basis of the envelopes, whether the model has converged from the preceding iteration to the present iteration is tested (C4), with a view to: o if not, carrying out a new iteration, o if so, performing a computation (D) of the complex envelopes on the basis of the iterations that have been carried out.

An instrumentation assembly configured to measure properties of an engine exhaust stream is disclosed in this paper. The instrumentation assembly may include an outer support ring that extends around a central axis, an inner support ring arranged radially inward of the outer support ring around the central axis, and a plurality of instrumentation rake assemblies. The plurality of instrumentation rake assemblies extends from the outer support ring to the inner support ring across an annular passageway defined between the outer support ring and the inner support ring configured to carry the engine exhaust stream.