초록 ▼

A life consumption of a component in a machine may be predicted. Load data may be received from a load session of the machine. A plurality of parameter sets may be accessed, each associated with a critical point of the component, which point is considered to have critical life consumption. For each

A life consumption of a component in a machine may be predicted. Load data may be received from a load session of the machine. A plurality of parameter sets may be accessed, each associated with a critical point of the component, which point is considered to have critical life consumption. For each critical point, life consumption may be calculated using a life consumption calculation model receiving the load data and the parameter sets as input. By selecting a plurality of critical points on the component, a more complete view is presented of how the different parts of the component are affected by the load session.

대표청구항 ▼

1. A method for operating an engine, comprising: receiving load data from a predetermined load session of an engine, accessing a plurality of parameter sets, each associated with a respective critical point of a component in said engine, whereby a plurality of critical points are accessed, each of w

1. A method for operating an engine, comprising: receiving load data from a predetermined load session of an engine, accessing a plurality of parameter sets, each associated with a respective critical point of a component in said engine, whereby a plurality of critical points are accessed, each of which points has a respective critical life consumption,for each critical point, calculating a life consumption using one of a plurality of life consumption calculation models receiving said load data and said parameter sets as input,wherein a selection of the life consumption calculation model is based, at least in part, on the parameter sets associated with each critical point,wherein said critical points considered to have critical life consumption are selected by:applying a mesh to a geometric model of a component, said mesh comprising a plurality of nodes, wherein at least each corner of the component is a node;calculating at least one of a stress pattern and a temperature pattern of said mesh for at least one predetermined load session by at least one of a scaling method, mesh based numerical method, or a simplified calculation method that includes at least one of a usage count and a set of linear differential equations;calculating a predicted life consumption for each of the plurality of nodes based on said at least one of said stress pattern and said temperature pattern for each predetermined load session using the life consumption calculation model;selecting, based on said predicted life consumption, a plurality of nodes considered to have a critical life consumption, said plurality of selected nodes forming said critical points; andaltering, during a further load session, at least one operational setting of the engine including at least one of power level angle, altitude, aircraft speed, ambient temperature, inlet temperature, low pressure rotor speed, high pressure rotor speed, combustion pressure, turbine temperature, turbine outlet pressure, and a control mode of the engine such that at least one of a more evenly distributed life consumption is accumulated for the selected critical points on the component in said engine compared to a distributed life consumption for the selected critical points on the component as predicted in the predetermined load session or such that more damage is accumulated in components in said engine with selected critical points which are cheaper to replace or have a low accumulated life consumption compared to other components in said engine. 2. The method according to claim 1, further comprising: performing the method of claim 1 for a plurality of load sessions, andfor each load session, accumulating respective life consumptions in each critical point. 3. The method according to claim 1, wherein said critical points considered to have critical life consumption are selected by: applying a mesh to a geometric model of said component, said mesh comprising a plurality of nodes;calculating at least one of a stress pattern, and a temperature pattern, of said mesh for at least one predetermined load session by means of a mesh based numerical method;calculating a predicted life consumption for each of the plurality of nodes based on said at least one of said stress pattern, and said temperature pattern, for each predetermined load session using the life consumption calculation model; andselecting, based on said predicted life consumption, a plurality of selected nodes considered to have a critical life consumption, said plurality of selected nodes forming said critical points. 4. The method according to claim 3, wherein the mesh based numerical method includes a finite element analysis. 5. The method according to claim 1, further comprising: determining a critical limit of the life consumption; anddetermining a maintenance action for the component, when the life consumption in one of said critical points on the component has reached the critical limit. 6. The method according to claim 1, further comprising: modifying the parameter sets for a critical point to modified parameter sets; andrecalculating the predicted life consumption for said critical point using the life consumption calculation model with the respective modified parameter sets for a set of previously calculated load sessions. 7. The method according to claim 1, wherein said life consumption calculation model comprises a mesh based numerical model. 8. The method according to claim 7, wherein said mesh based numerical model is used for at least one of training, and validating, a simplified calculation model. 9. The method according to claim 8, wherein said simplified calculation model comprises a set of linear difference equations defining a relationship between load data and at least one of stress, strain, and temperature. 10. The method according to claim 1, wherein said life consumption calculation model comprises a set of linear difference equations defining a relationship between load data and at least one of stress, strain, and temperature. 11. The method according to claim 1, wherein the load data includes at least one of time, altitude, aircraft speed, ambient temperature, inlet temperature, low pressure rotor speed, high pressure rotor speed, combustion pressure, turbine outlet temperature, turbine outlet pressure, power lever angle, and control mode. 12. The method according to claim 1, wherein the load data for a particular load session is formed by a time sequence of machine conditions representative of data measured during said load session. 13. The method according to claim 1, wherein at least one of the parameter sets comprises at least one of: part number, safety factor, material data, filter settings, thermal model settings, stress model settings, and failure mode settings. 14. A system for operating an engine, comprising: a load creation unit programmed to receive load data from a predetermined load session of an engine;a model unit programmed to access a plurality of parameter sets, each associated with a respective critical point of a component in said engine, whereby a plurality of critical points are accessed, each of which points has a respective critical life consumption; anda calculation unit programmed to calculate a life consumption in each critical point using a life consumption calculation model receiving said load data and said parameter sets as input, wherein a selection of the life consumption calculation model is based, at least in part, on the parameter sets associated with each critical point,wherein the calculation unit is further programmed to select said critical points considered to have critical life consumption by:applying a mesh to a geometric model of a component, said mesh comprising a plurality of nodes, wherein at least each corner of the component is a node;calculating at least one of a stress pattern and a temperature pattern of said mesh for at least one predetermined load session by at least one of a scaling method, mesh based numerical method, or a simplified calculation method that includes at least one of a usage count and a set of linear differential equations:calculating a predicted life consumption for each of the plurality of nodes based on said at least one of said stress pattern and said temperature pattern for each predetermined load session using the life consumption calculation model;selecting, based on said predicted life consumption, a plurality of nodes considered to have a critical life consumption, said plurality of selected nodes forming said critical points; andaltering, during a further load session, at least one operational setting of the engine including at least one of power level angle, altitude, aircraft speed, ambient temperature, inlet temperature, low pressure rotor speed, high pressure rotor speed, combustion pressure, turbine temperature, turbine outlet pressure, and a control mode of the engine such that at least one of a more evenly distributed life consumption is accumulated for the selected critical points on the component in said engine compared to a distributed life consumption for the selected critical points on the component as predicted in the predetermined load session or such that more damage is accumulated in components in said engine with selected critical points which are cheaper to replace or have a low accumulated life consumption compared to other components in said engine. 15. The system according to claim 14, further comprising a life consumption calculation unit that is programmed to, for a plurality of load sessions, accumulate life consumption for each load session in each critical point. 16. The system according to claim 15, wherein the life consumption calculation unit is further programmed to determine a critical limit of the life consumption and to determine a maintenance action for the component, when the life consumption in one of said critical points on the component has reached the critical limit. 17. The system according to claim 14, wherein the calculation unit is further programmed to calculate the life consumption in each critical point using a set of linear difference equations defining a relationship between load data and at least one of stress, strain, and temperature. 18. The system according to claim 14, wherein the load creation unit is further programmed to receive load data including at least one of time, altitude, aircraft speed, ambient temperature, inlet temperature, low pressure rotor speed, high pressure rotor speed, combustion pressure, turbine outlet temperature, turbine outlet pressure, power lever angle, and control mode. 19. The system according to claim 14, wherein the load creation unit is further programmed to form load data for the load session by a time sequence of machine conditions representative of data measured during the load session.