Abstract: A system is provided for an aircraft. This aircraft system includes a gas turbine engine and a sensor system. The gas turbine engine includes an inlet and a compressor section. A flowpath projects radially inward into the gas turbine engine from the inlet and extends through the compressor section. The sensor system includes a plurality of static pressure sensors at least partially within the flowpath. The sensor system is configured to determine a total pressure characteristic within the flowpath using the plurality of static pressure sensors.

Abstract: A system is provided for an aircraft. This aircraft system includes a gas turbine engine and a sensor system. The gas turbine engine includes an inlet and a compressor section. A flowpath projects radially inward into the gas turbine engine from the inlet and extends through the compressor section. The sensor system includes a plurality of static pressure sensors at least partially within the flowpath. The sensor system is configured to determine a total pressure characteristic within the flowpath using the plurality of static pressure sensors.

Abstract: A system is provided for an aircraft. This aircraft system includes a gas turbine engine and a sensor system. The gas turbine engine includes an inlet and a compressor section. A flowpath projects radially inward into the gas turbine engine from the inlet and extends through the compressor section. The sensor system includes a plurality of static pressure sensors at least partially within the flowpath. The sensor system is configured to determine a total pressure characteristic within the flowpath using the plurality of static pressure sensors.

Abstract: An airflow profiled structure having a profiled leading edge. The profiled leading edge having, along a leading edge line, a serrated profile line with a succession of teeth and depressions. The airflow profiled structure also includes a porous acoustically absorbent region located towards the bottom of the depressions.

Abstract: Methods and systems for detecting an abnormal start of a gas turbine engine are described. Speed data points are sampled from a sensor associated with the engine in accordance with a sampling rate, the speed data points being indicative of a rotational speed of a gas generator of the engine during engine start. The speed data points are continuously stored during the engine start. Previously-obtained speed data points which are older than an abnormal start delay are discarded. An abnormal engine start event is detected by comparing a first one of the stored speed data points with a second one of the stored speed data points, the second one of the stored speed data points obtained before the first one.

Abstract: A sensorized roller for a bearing includes a bore that extends through the roller, a sensor for measuring at least one physical state of the roller bore and producing a first signal indicative of the measured physical state, a wireless transmitter for receiving the first signal from the sensor and wirelessly transmitting a second signal based on the first signal, and a generator configured to be rotated by a movement of the roller, the generator being electrically connected to the sensor. The measuring unit, the wireless transmitter and the generator are located inside the bore.

Abstract: A method for controlling a vapour compression system (1) is disclosed. A mass flow of refrigerant along a part of the refrigerant path is estimated, based on measurements performed by one or more pressure sensors (10, 12, 13) for measuring a refrigerant pressure at selected positions along the refrigerant path and one or more temperature sensors (11, 14) for measuring a refrigerant temperature at selected positions along the refrigerant path. A refrigerant pressure or a refrigerant temperature at a selected position a pressure sensor (10, 12, 13) or temperature sensor (11, 14) along the refrigerant path is derived, based on the estimated mass flow. The vapour compression system (1) is allowed to continue operating, even if a sensor (10, 11, 12, 13, 14) is malfunctioning or unreliable.

Abstract: A sensor device includes: a rod member including an axially extending gas passage into which fluid flows; a sheath pipe thinner than the gas passage, inserted in the gas passage with a distal end thereof being located inside the gas passage, and configured to detect a temperature of the fluid; an insert configured to fix a proximal end of the sheath pipe; and retention members configured to retain the distal end of the sheath pipe.

Abstract: A system and method for diagnosing load compressor health state for an auxiliary power unit that includes a power compressor, a combustor, a power turbine, and a load compressor is provided. The auxiliary power unit is operated and bleed air is discharged from the load compressor at a bleed air pressure. Using a pressure sensor, the bleed air pressure discharged from the load compressor is sensed and supplied to a processor. In the processor, power compressor health state is diagnosed based solely on the sensed bleed air pressure.

Abstract: Herein provided are methods and systems for detecting a high temperature condition of a gas turbine engine. A fuel flow to a combustor of the engine and a compressor outlet pressure of the engine are obtained. A ratio of the fuel flow to the compressor outlet pressure is determined. The ratio is compared to a threshold and a high temperature condition of the engine is detected when the ratio exceeds the threshold.

Abstract: A combustor for a gas turbine engine comprising: a combustion chamber; at least one fuel spray nozzle operable to deliver a fuel-air mixture into the combustion chamber, wherein during operation of the gas turbine engine the fuel-air mixture is combusted in the combustion chamber, thereby producing a combustion flame; a microwave generator coupled to a waveguide arranged to guide microwaves from the microwave generator into the combustion chamber such that the microwaves are incident on at least a portion of the combustion flame; and a detector operable to detect at least a portion of the microwaves reflected by the combustion flame and/or atomised fuel droplets.

Abstract: A system for rotating a turbomachine rotor relative to a stator casing, the rotor including an annular row of blades, the rotating system including a supporting arm including a first end arranged for gripping a leading edge of a first blade of the annular row and a second end arranged for gripping a trailing edge of the first blade; an electric motor including a shaft and a body attached to the supporting arm; and a wheel coupled to the shaft of the motor and provided with a rolling strip, the wheel, furthermore, being arranged so that the rolling strip can come into contact with an annular wall of the stator casing when the supporting arm is mounted on the first blade.

Abstract: Methods and systems for monitoring component integrity during operation of an engine are provided. Usage data associated with a period of operation of the engine is obtained at an engine controller. The engine controller has assigned thereto a first trust level. A first indication of the usage data is transmitted from the engine controller to a first presentation device forming part of a first communication path, which has assigned thereto a second trust level lower than the first trust level. A second indication of the usage data is transmitted from the engine controller to a second presentation device forming part of a second communication path, which is independent from the first communication path and has assigned thereto the second trust level. The trust level of the first and second communication paths is elevated by having the usage data transmitted through the first and second independent communication paths.

Abstract: An apparatus, system, and process for testing a gas turbine engine or other test object under a cold condition, such as a compressor of a gas turbine engine, a combustor of a gas turbine engine, or an afterburner of an aero gas turbine engine, using compressed air stored in an underground storage reservoir of a CAES system along with an air turbine or an air injector. High-pressure, but low-volume, compressed air from a CAES system can be converted into a low-pressure, but high-volume, flow of compressed air using an air injector to supply enough compressed air to test a combustor or an afterburner. High pressure compressed air from the CAES system can be used to drive an air turbine that then drives a compressor for testing.

Abstract: A method of assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, positioning an array of airfoils about an outer periphery of a hub, the hub being rotatable about an engine longitudinal axis of a gas turbine engine, the hub including a plurality of flanges, and each one of the airfoils including an airfoil section extending from a root section. An array of platforms are positioned about the outer periphery of the hub, each of the platforms including one or more slots defined by a plurality of platform flanges, and including the one or more slots receiving a respective one of the flanges of the hub. A plurality of retention pins are moved relative to the array of airfoils such each one of the retention pins extends through the flanges of the hub and through the plurality of platform flanges of a respective one of the platforms to mechanically attach a respective one of the platforms and the root section of a respective one of the airfoils to the hub.

Abstract: A system and method for determining particulate accumulation in a gas turbine engine includes sensing the number, size, and type of particulate at a first position on the gas turbine engine and supplying first data representative thereof, where the first position located at a first side of a gas turbine engine component; sensing the number, size, and type of particulate at a second position on the gas turbine engine and supplying first data representative thereof, where the second position located at a second side of the gas turbine engine component and downstream of the first position; and processing the first data and the second data to determine the mass of the particulate accumulated on the gas turbine engine component.

Abstract: Methods and systems for detecting a structural failure of a fan blade of a fan rotor of an engine are described herein. A fan rotor speed and an engine vibration parameter are obtained. A rate of change of the fan rotor speed is compared to a deceleration threshold and the engine vibration measurement is compared to a vibration threshold. Structural failure of the fan blade is detected when the engine vibration measurement exceeds the vibration threshold for a period of time and the rate of change of the fan rotor speed is below the deceleration threshold. In response to detecting the structural failure, an alert indicative of the structural failure is triggered.

Abstract: A method for predicting an anomaly in a combustor (16) is presented. The method includes receiving signals representative of parameters in one or more combustion cans (22, 24) of the combustor, generating a plurality of patterns based on a permutation entropy window and the signals, identifying a plurality of pattern categories in the plurality of patterns, determining a permutation entropy based on the plurality of patterns and the plurality of pattern categories, and predicting an anomaly in the combustor based on the permutation entropy. The method further includes comparing the plurality of pattern categories to determined permutations of pattern categories if the anomaly is present in the combustor, and predicting a category of the anomaly based on the comparison of the plurality of pattern categories to the determined permutations of pattern categories.

Abstract: A method for processing a signal on board an aircraft. An electronic control unit receives an input signal including useful data in a first passband, implements a first operation of bandpass filtering the input signal with a first passband to obtain a useful signal containing the useful data, with detection of interference caused by a lightning strike. The electronic control unit implements a second operation of bandpass filtering the input signal to obtain a detection signal, the bandpass filter having a second passband that is distinct from the first passband, comparing a detection value derived from the detection signal with a detection threshold, and correcting the exploitation of the useful data if exceeded.

Abstract: The invention concerns a propulsion device (1) comprising a torque generator (2) driving an output shaft (3) via a power gearbox (4), the output shaft (3) being rotatably coupled to a thruster (5), said power gearbox (4) being fixed on a frame (7) by means of suspension means (8, 14, 15), said suspension means including hydraulic torque recovery means comprising at least a first hydraulic system (15) and a second hydraulic system (15) spaced from each other, each hydraulic system (15) having a pressure chamber whose volume varies according to the position of the housing (9) of the power gearbox (4) relative to the frame (7), the pressure chambers of the hydraulic systems (15) being connected by a capillary so that a hydraulic fluid is able to flow from one pressure chamber to another via the capillary.

Abstract: A measuring device, in particular for a flow inside a turbomachine, in particular in an aircraft engine. The measuring device includes at least one suction intake opening for fluid from an area of a mixed-out flow, wherein the at least one suction intake opening is arranged at a distance from a wall that delimits the flow, and fluid that is suctioned in through a fluid channel can be conducted to a sensor device.

Abstract: An indentation tester and indentation method for testing a sample heated at a temperature range from above 800° C. to 1200° C., and above, is disclosed. The indentation tester includes a stage having a metallic cylindrical base that houses an inner cylindrical base made of a temperature resistant material sufficient to maintain shape over the range of the heating temperature. A removable crown fastens to the cylindrical base and includes a ring that holds an axisymmetric pipe made of a temperature resistant material sufficient to maintain shape over the range of heated temperature. A nut is turned to tighten the pipe which secures the sample and guides an indenter to penetrate the sample. The indenter includes a rod made of temperature resistant material and a indenter tip.

Abstract: An active roll stabilizer includes a pair of stabilizer bars installed between left and right wheels of a vehicle and an actuator which connects the pair of stabilizer bars and transmits a rotational force to the pair of stabilizer bars, wherein the actuator includes a motor configured to generate the rotational force, a housing coupled to a portion between the pair of stabilizer bars and having the motor disposed inside the housing, a damping part disposed on an extension line of a rotational shaft of the motor inside the housing and configured to absorb vibrations generated at the motor and the pair of stabilizer bars, and a torque measurement sensing part configured to measure a torque transmitted by the rotational force inside the damping part.

Abstract: A system and method for determining performance of a turbine engine, and operation thereof. The system and method includes a plurality of sensors and one or more computing devices executing operations including acquiring a plurality of parameter sets each corresponding to a plurality of engine conditions in which each parameter set corresponding to each engine condition indicates a health condition at a plurality of locations at the engine; comparing the plurality of parameter sets to determine a health condition corresponding to a location at the engine; and generating a health condition prediction at the engine based on the compared parameters.

Abstract: A gas turbine engine generates noise during use, and one particularly important flight condition for noise generation is take-off. A gas turbine engine has high efficiency together with low noise, in particular from the turbine that drives the fan. The contribution of the turbine noise emanating from the rear of the engine to the Effective Perceived Noise Level (EPNL) is in the range of from 7 EPNdB and 30 EPNdB lower at a take-off lateral reference point than at an approach reference point.

Abstract: A gas turbine engine test assembly includes a test apparatus having a rotor and stator and a bearing assembly having a fluid circuit providing an adjustable fluid pressure interface between the rotor and stator.

Abstract: An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil that has an airfoil section extending from a root section. The airfoil section extends between a leading edge and a trailing edge in a chordwise direction and extending between a tip portion and the root section in a radial direction. The airfoil section defines a pressure side and a suction side separated in a thickness direction. A platform is dimensioned to receive a retention pin to mount the platform to a rotatable hub. At least one of the airfoil and the platform includes a plurality of composite layers that define an internal cavity. A lattice structure in the internal cavity extends between the plurality of composite layers. The lattice structure has a plurality of branches that extend from a plurality of nodes.

Abstract: A pressure sensor device with good temperature characteristics. An auxiliary fluid introduction path is provided in a bottom wall portion of a first case to introduce a fluid to the vicinity of a recessed portion of the bottom wall portion where an integrated circuit with a large change in temperature characteristics is mounted such that the temperature of the integrated circuit becomes the same as or close to the temperature of the fluid.

Abstract: A torque indicator for an aircraft having a main rotor system and a translational thrust system driven by at least one engine includes a first indicator operable to display an actual torque of an engine of the aircraft relative to an engine torque limit, a second indicator operable to display an actual torque of the translational thrust system of the aircraft relative to a translational thrust system torque limit, and a third indicator operable to display an actual torque of the main rotor system of the aircraft relative to a main rotor system torque limit.

Abstract: A method for actively calculating a capability of an electronically controlled valve is provided. The method including the steps of: a) operating the electronically controlled valve in accordance with a task; b) testing the electronically controlled valve in order to determine a range of movement of the electronically controlled valve in accordance with an initial gain, wherein the testing of the electronically controlled valve occurs after the valve has been operated in accordance with the task; c) determining a new gain required for providing a predetermined range of movement of the electronically controlled valve; and d) repeating steps a-c at least once, wherein the new gain is used to operate the valve in accordance with the task.

Abstract: A method to repair a turbomachine including: assign blades and a shroud in a row of the turbomachine to a group; measure, for each blade in the group, a clearance between a tip surface of the blade and a surface of the shroud facing the tip surface; remove the blades and shroud from the row; calculate a difference between the clearance of associated each blade and a design clearance; determine, for each blade, if the difference may be minimized by adding material to the surface of the shroud; adding material to the surface of the shroud, wherein the addition of material to the facing surfaces results in the shroud having at least one dimension that exceeds an original design dimension of the shroud sections, and installing the group of the blades and the shroud with the added material to a row of a turbomachine, wherein at least one of the blades has at least one dimension that does not conform to an original design specification for the blade.

Abstract: Methods and systems for improving vacuum generation for an engine that may be operated at higher altitudes are presented. In one non-limiting example, a transmission that is mechanically coupled to the engine may be shifted from a gear to neutral in response to an actual total number of times a vehicle brake pedal is applied and partially released while the vehicle is stopped and the brake pedal is applied.

Abstract: A system includes one or more processors configured to analyze obtained image data representing a rotor blade to detect a candidate feature on the rotor blade and determine changes in the size or position of the candidate feature over time. The one or more processors are configured to identify the candidate feature on the rotor blade as a defect feature responsive to the changes in the candidate feature being the same or similar to a predicted progression of the defect feature over time. The predicted progression of the defect feature is determined according to an action-guidance function generated by an artificial neural network via a machine learning algorithm. Responsive to identifying the candidate feature on the rotor blade as the defect feature, the one or more processors are configured to automatically schedule maintenance for the rotor blade, alert an operator, or stop movement of the rotor blade.

Abstract: Inspection apparatus for a gas turbine engine, the inspection apparatus comprising: a sensor configured to generate data; a housing having an exterior surface and configured to house the sensor therein; and one or more foam members coupled to the exterior surface of the housing, the one or more foam members being resilient to enable the inspection apparatus to be inserted into a gas turbine engine and secured between at least two surfaces of the gas turbine engine.

Abstract: Embodiments of the disclosure can relate to quantification of gas turbine inlet filter blockage. In one embodiment, a method can include receiving data associated with an inlet flow conditioning system associated with a turbine in a power plant. The method may further include determining an inlet flow associated with the turbine, based at least in part on operational data from the turbine. The method may further include determining an effective area of the inlet flow conditioning system, based at least in part on the inlet flow associated with the turbine. The method can further include determining a fouling rate of the inlet flow conditioning system, based at least in part on a difference between the effective area of the inlet flow conditioning system and a corresponding effective area of the inlet flow conditioning system determined at a prior operation.

Abstract: A controller for a gas turbine engine is disclosed. The controller is configured to measure a first rotational speed of a shaft of the engine at a first end of the shaft and to measure a second rotational speed of the shaft at a second end. The first end may be coupled to a turbine of the engine and the second end may be coupled to a compressor of the engine. The controller is further configured to determine a shaft twist angle as a function of the first rotational speed and the second rotational speed, determine whether the shaft twist angle is within a predetermined shaft health monitoring range, and record the shaft twist angle. The controller may be configured to generate a maintenance alert in response to determining that the shaft twist angle is within the predetermined shaft health monitoring range.

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion, a cooling circuit disposed within the body portion and including at least a first cavity, a core in fluid communication with the first cavity, and an exit surface that extends through an exterior surface of the body portion. At least one surface indicator is visible near the exit surface.

Abstract: Internal components of power generation machinery, such as gas turbine engines, are inspected with a spherical, optical-camera inspection system, mounted within a camera housing on a distal end of a compact diameter, single-axis inspection scope. The inspection scope includes nested, non-rotatable telescoping tubes, which define an extension axis. Circumscribing, telescoping tubes have anti-rotation collars, which are in sliding engagement with extension tracks on a circumferential surface of an opposing, nested tube, for ease of extension and retraction of the camera during visual inspections of power generation machinery. The camera is advanced and/or retracted along a scope extension axis by nested, drive tubes, which incorporate at least one external drive screw on a circumscribed drive tube and corresponding female threads formed in a circumscribing drive tube. The spherical camera has a 360-degree field of view, and captures images without rotation about the scope extension axis.

Abstract: A device for integrity testing a system for rapid reactivation of a turboshaft engine of a helicopter, includes a pneumatic turbine that is mechanically connected to the turboshaft engine and is supplied with gas, upon a command, by a pneumatic supply circuit such that it is possible to rotate the turboshaft engine and ensure that it is reactivated. The testing device has an apparatus configured to withdraw pressurized air from the turboshaft engine and a duct for conveying the withdrawn air to the pneumatic circuit for supplying the pneumatic turbine with gas. The device further includes a sensor for determining the rotational speed of the pneumatic turbine.

Abstract: A system for use in inspecting a component having flow openings defined therein. The system includes a fluid injector in flow communication with the component, wherein the fluid injector provides fluid to the component such that the fluid is discharged from the flow openings. A sensing sheet is coupled to or positioned proximate to the component such that the fluid discharged from the flow openings is received at the sensing sheet, wherein the sensing sheet is formed from pressure-sensitive material. A light source emits light towards the sensing sheet such that the pressure-sensitive material is excited to an energy level. The system further includes an imaging device that captures images of a change in color of the pressure-sensitive material as a function of a pressure of the fluid received at the sensing sheet, wherein the change in color represents a pressure distribution across the sensing sheet based on a flow profile of the fluid discharged from the flow openings.

Abstract: Systems and methods for controlling a fluid based engineering system are disclosed. The systems and methods may include a model processor for generating a model output, the model processor including a set state module for setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode. The system may include a control law for directing the actuator as a function of a model output and for determining if the control device is operating with deteriorated conditions. The model processor may further include an estimate state module for determining an estimated state of the model based on a prior state model output and the current state model of an open loop model.

Abstract: A measuring comb for temperature and/or pressure and/or chemical composition of the gases flowing at the outlet of a turbine engine flow path, in which the flow path extends around an axis of revolution of the flow path, is provided. The measuring comb includes: a comb body with an elongated shape, intended to face the outlet of the flow path, the comb body including at least one measuring opening arranged along an axis, the measuring opening being configured to tap gases flowing at the outlet of the flow path; and an adjusting system configured to adjust an angle between the axis of the at least one measuring opening and the axis of revolution, so as to allow orientation of the at least one measuring opening in the flow direction of the gases at the outlet of the flow path.

Abstract: The present invention relates to a horizontal-shaft/vertical-transmission wind turbine for generating electricity, which may be on-shore or off-shore, with reduced materials and structures in the nacelle, mast and foundation, which moves much of the equipment to the base of the mast, thereby reducing capex, enabling significant reductions in the operation and maintenance costs of the turbines, and reducing the cost of the installed power (installed MW) in a wind farm. The mechanical energy coming from the rotor is transmitted by a vertical shaft system (6) along the mast, which incorporates naval technology, and which is based on platforms (1) to neutralize harmonics and is connected to H/Vst (3) and V/Hmvst (4) transmissions, coupled using contraction and expansion joints (2). In addition to this, the rotor orientation system (YAW control) (29), which is connected to the torque control of the transmissions, the brake control and the blade pitch control, enables the rotor to be properly positioned.

Abstract: Various methods and systems are provided for controlling a tip clearance between a shroud and blade of a turbocharger turbine. In one embodiment, a method for an engine including a turbocharger comprises, selectively adjusting a flow of coolant from one or more engine coolant sources through a shroud of a turbine based on a tip clearance between the shroud and a blade of the turbine.

Abstract: A method for controlling wind alignment correction of a wind turbine comprises: acquiring environmental wind speed values, wind alignment angle measured values, and generated power values of the wind turbine in real time; dividing each acquired environmental wind speed value into multiple wind speed sections according to the magnitude of the environmental wind speed value, and extracting wind alignment angle measured values and generated power values in at least one wind speed section; determining a maximum value of extracted generated power values in each wind speed section; calculating a wind alignment correction deviation of the wind turbine according to a wind alignment angle measured value corresponding to the maximum value; and performing correction processing on a subsequently acquired wind alignment angle measured value by using the wind alignment correction deviation.

Abstract: Assemblies and methods for monitoring turbine component deformation are provided. An assembly includes a first strain sensor configurable on the turbine component, the first strain sensor including at least two reference points and having a first dimension. The assembly further includes a second strain sensor configurable on the turbine component, the second strain sensor including at least two reference points and having a first dimension which corresponds to the first dimension of the first strain sensor. An initial value of the first dimension of the second strain sensor is different from an initial value of the first dimension of the first strain sensor. In accordance with another embodiment of the present disclosure, a method for monitoring turbine component deformation is provided.

Abstract: A method for monitoring and diagnosing anomalies in auxiliary systems of a gas turbine implemented using a computer device coupled to a user interface and a memory device, the method including storing a plurality rule sets in the memory device, the rule sets relative to the auxiliary systems of the gas turbine, the rule sets including at least one rule expressed as a relational expression of a real-time data output relative to a real-time data input, the relational expression being specific to parameters associated with the auxiliary systems of the gas turbine, receiving real-time and historical data inputs from a condition monitoring system associated with the gas turbine, the data inputs relating to process parameters associated with the auxiliary systems of the gas turbine, and estimating values for at least some of the parameters associated with the auxiliary systems of the gas turbine using the received inputs.

Abstract: A method for thermally imaging a moving workpiece of a gas turbine engine comprises identifying a plurality of geometric features to construct a composite image. The geometric features include at least one integral thermal feature of the moving workpiece, and at least one artificial feature applied to the workpiece for diagnostic purposes. One of the plurality of geometric features is identified as a master feature, and the remainder of the plurality of geometric features are located relative to the master feature with relative actual coordinates. A pixel location of the master feature is identified or each image, and the remainder of the plurality of geometric features are located relative to the master feature with relative pixel coordinates. Offset, rotation, and scaling of the secondary images are varied to minimize a relative difference between the relative pixel coordinates and the relative actual coordinates.

Abstract: System and methods for detecting anomalies and identifying faults of a gas turbine engine may include a recorder in communication with a processor. The recorder may be configured to capture archival data of the gas turbine engine. A flight normalizer module may be configured to produce normalized results based on the archival data. A flight parameter features module may be configured to generate flight parameter features based on the normalized results. A data warehouse module may be configured to determine suspected fault classes by comparing the flight parameter features against training parameter features stored in the data warehouse module based on queries from the flight parameter features module. A majority vote module may be configured to determine a diagnosed fault class based on the suspected fault classes.

Abstract: A method for measuring an engine load of a drive motor in a vehicle. Here, at least one parameter which characterizes the engine load is allocated a driving distance equivalent. This driving distance equivalent is then incremented by a driving distance counter. If the vehicle is equipped with a sailing functionality, the driven distance is counted only if the vehicle is moving and the drive train is coupled to the drive motor without slip. A rate of rotation sensor, a clutch sensor and a driving distance counter able to be switched on and off are required for running the method of the present invention. A computer program is used in addition.