Airbus Helicopters

Snecma

Eurocopter

Emmanuel Camhi

Jean Pierre Mareix

Didier Pasquiet

Regis Rossotto

Jean-Pierre Mareix

Laurent Crouilbois

Guido Borchers

Southdary Beaud

A checking method for checking a power plant of an aircraft, the power plant comprising at least one engine and an air inlet for feeding said at least one engine with air, the power plant including a cloggable filter filtering the air upstream from the engine. An aircraft power check is performed by: determining, in flight or on the ground, the current power actually being developed by the engine without making any allowance for any power losses resulting from the engine being installed in the aircraft or from a level of clogging of the filter, the aircraft power check being considered as being successful when the current power is greater than or equal to a guaranteed minimum power.

Method and a device for estimating the health of a power plant of an aircraft having at least one engine and a cloggable filter filtering air upstream from the engine

A method of detecting that an aircraft is flying in icing conditions. A processor unit determines a real power developed by the turboshaft engine and a theoretical power that the engine can develop in theory, the theoretical power being determined using a theoretical model supplying a power as a function at least of a speed of rotation of a gas generator of the engine. The processor unit determines a difference between the real power and the theoretical power. The processor unit generates a warning to indicate the presence of icing conditions when the power difference is greater than a predetermined power threshold for a length of time longer than a time threshold, and when a temperature outside the aircraft lies between a low temperature threshold and a high temperature threshold.

Method and a device for detecting icing at an air inlet of a turboshaft engine

A method of failure simulation for an aircraft () having a power plant () with at least two turbine engines (), together the two engines develop an overall power, each engine () being capable of delivering at least one contingency power in order to compensate for a total failure of other engines (). The device serves during a failure simulation to modify the overall power delivered by the power plant, with this modification being performed with the help of first adjustment means (). Second adjustment means () serve to modify also the difference between the minimum power obtained during the simulated failure and the stabilized overall power, and also the time between said failure stabilizing on said overall power.

Method of simulating a failure on an aircraft

A method of automatically performing an engine health check for checking the health of at least one turbine engine of an aircraft. During flight, the stability of at least one monitoring parameter is verified by acquiring a measurement signal, by performing first filtering of each signal by a high-pass filter over a long first duration (TPS) and by verifying that a first amplitude (A) of the signal filtered in this way does not exceed a first threshold defined by the manufacturer, by performing second filtering of each signal by a high-pass filter over a short second duration (TPS) in parallel with said first filtering by a high-pass filter, and by verifying that a second amplitude (A) of the signal filtered in this way does not exceed a second threshold defined by the manufacturer, the second duration (TPS) being less than the first duration (TPS), and the second amplitude (A) being less than the first amplitude (A).

Method and a device for performing a check of the health of a turbine engine of an aircraft provided with at least one turbine engine

A wall in which there is formed at least one cooling channel, said wall being cooled by cool air flowing in the channel, the channel comprising a hole and a diffusion portion, the hole opening out at one end into the inside surface of the wall, and at its other end into the diffusion portion where it forms an orifice, the diffusion portion flaring around said orifice and opening out into the outside surface of the wall, the diffusion portion having a bottom whose front end is substantially plane, sloping, and extending in front of the orifice, and also having a margin extending behind, round the sides, and in front of the orifice, said margin joining the sides of the front end. A method and an electrode for making such a cooling channel. A turbomachine blade presenting such a wall.

Electrode for forming a cooling channel in a wall

A method for forming at least one cooling channel in a wall which is cooled by cool air flowing in the channel is provided. The channel includes a hole and a diffusion portion, the hole opening out at one end into the inside surface of the wall, and at its other end into the diffusion portion where it forms an orifice. The diffusion portion flares around the orifice and opens out into the outside surface of the wall. The diffusion portion has a bottom whose front end is substantially plane, sloping, and extending in front of the orifice, and also has a margin extending behind, round the sides, and in front of the orifice, the margin joining the sides of the front end.

Cooling channel formed in a wall

A power plant () having at least one engine () and control means () for controlling said engine (). The control means () include a memory (), said memory () containing information for operating said engine () in accordance with at least two distinct utilization envelopes during a maximum number of flying hours, the two envelopes comprising an envelope enabling takeoff from a platform and another envelope enabling takeoff from takeoff zones not including platforms, each utilization envelope comprising at least two distinct utilization ratings each defined by a developed power and by a utilization duration for said developed power.

Aircraft power plant, an aircraft, and a method of piloting said aircraft

A method of performing a health check of at least one turbine engine (). During a development step (STP), the installation losses () are quantified for a plurality of test values for a reduced speed of rotation (Ng') of a gas generator () of the engine. During an acquisition step (STP), the speed of rotation of said gas generator () is increased until said engine develops a maximum power, and then the speed of rotation of the gas generator () is decreased until the reduced speed of rotation (Ng&#x2032;) reaches a test value. The aircraft is stabilized and at least one monitoring value is acquired. During an evaluation step (STP) of evaluating the health check, at least one operating margin is determined by using a monitoring value and the effects of mounting the engine in an airplane.

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Fuveau, France

Emmanuel Camhi