초록 ▼

A device and a method for closed-loop control of at least a first exhaust gas turbocharger with variable turbine geometry. In this regard, a first closed-loop control system is provided for automatically controlling the charge air pressure, and a second closed-loop control system is provided for aut

A device and a method for closed-loop control of at least a first exhaust gas turbocharger with variable turbine geometry. In this regard, a first closed-loop control system is provided for automatically controlling the charge air pressure, and a second closed-loop control system is provided for automatically controlling the turbine speed. The second closed-loop control system is subordinate to the first closed-loop control system. The correcting variable (SG1) of the first closed-loop control system corresponds to the reference input of the second closed-loop control system.

대표청구항 ▼

What is claimed is: 1. A method for closed-loop control of at least a first exhaust gas turbocharger with variable turbine geometry, comprising the steps of: automatically controlling charge air pressure by means of a first closed-loop control system, which has a charge air pressure controller that

What is claimed is: 1. A method for closed-loop control of at least a first exhaust gas turbocharger with variable turbine geometry, comprising the steps of: automatically controlling charge air pressure by means of a first closed-loop control system, which has a charge air pressure controller that determines a first correcting variable (SG1) for influencing a flow-through turbine cross section from a deviation (dpLL) of an actual charge air pressure value from a set charge air pressure value; and automatically controlling turbine speed by means of a second closed-loop control system, which has a turbine speed controller that determines a second correcting variable (SG2) for influencing the flow-through turbine cross section (AT) from a deviation (dnT) of an actual turbine speed value from a set turbine value, the second closed-loop control system being subordinate to the first closed-loop control system, and a reference input of the second closed-loop control system being determined from the first correcting variable (SG1), including computing a third correcting variable (SG3) for synchronizing the first exhaust gas turbocharger and a second exhaust gas turbocharger with variable turbine geometry from a difference (DIFF) of turbine speeds (nT1, nT2), by means of a first synchronization controller. 2. The method in accordance with claim 1, wherein the flow-through turbine cross section of the first exhaust gas turbocharger is substantially determined by the second correcting variable (SG2) and the third correcting variable (SG3). 3. The method in accordance with claim 1, including determining the turbine actual speed (nT(IST)) for the second closed-loop control system from a maximum turbine speed of the first exhaust gas turbocharger or the second exhaust gas turbocharger. 4. A method for closed-loop control of at least a first exhaust gas turbocharger with variable turbine geometry, comprising the steps of: automatically controlling charge air pressure by means of a first closed-loop control system, which has a charge air pressure controller that determines a first correcting variable (SG1) for influencing a flow-through turbine cross section from a deviation (dpLL) of an actual charge air pressure value from a set charge air pressure value; and automatically controlling turbine speed by means of a second closed-loop control system, which has a turbine speed controller that determines a second correcting variable (SG2) for influencing the flow-through turbine cross section (AT) from a deviation (dnT) of an actual turbine speed value from a set turbine value, the second closed-loop control system being subordinate to the first closed-loop control system, and a reference input of the second closed-loop control system being determined from the first correcting variable (SG1), including computing a third correcting variable (SG3) for synchronizing the first exhaust gas turbocharger and a second exhaust gas turbocharger from a difference (DIFF) of air masses (LM1, LM2) of the first exhaust gas turbocharger and the second exhaust gas turbocharger, by means of a second synchronization controller. 5. The method in accordance with claim 4, wherein the flow-through turbine cross section of the first exhaust gas turbocharger is substantially determined by the second correcting variable (SG2) and the third correcting variable (SG3). 6. The method in accordance with claim 1, including determining the turbine actual speed (nT(IST)) for the second closed-loop control system from a maximum turbine speed of the first exhaust gas turbocharger or the second exhaust gas turbocharger. 7. A method for closed-loop control of at least a first exhaust gas turbocharger with variable turbine geometry, comprising the steps of: automatically controlling charge air pressure by means of a first closed-loop control system, which has a charge air pressure controller that determines a first correcting variable (SG1) for influencing a flow-through turbine cross section from a deviation (dpLL) of an actual charge air pressure value from a set charge air pressure value; and automatically controlling turbine speed by means of a second closed-loop control system, which has a turbine speed controller that determines a second correcting variable (SG2) for influencing the flow-through turbine cross section (AT) from a deviation (dnT) of an actual turbine speed value from a set turbine value, the second closed-loop control system being subordinate to the first closed-loop control system, and a reference input of the second closed-loop control system being determined from the first correcting variable (SG1), including computing a third correcting variable (SG3) for synchronizing the first exhaust gas turbocharger and a second exhaust gas turbocharger, by means of an end of tape control block. 8. The method in accordance with claim 7, wherein the flow-through turbine cross section of the first exhaust gas turbocharger is substantially determined by the second correcting variable (SG2) and the third correcting variable (SG3). 9. The method in accordance with claim 7, including determining the turbine actual speed (nT(IST)) for the second closed-loop control system from a maximum turbine speed of the first exhaust gas turbocharger or the second exhaust gas turbocharger. 10. A device for closed-loop control of at least a first exhaust gas turbocharger with variable turbine geometry, comprising: a first closed-loop control system for automatically controlling charge air pressure by means of a charge air pressure controller, which determines a first correcting variable (SG1) for influencing a flow-through turbine cross section from a deviation (dpLL) of an actual charge air pressure value from a set charge air pressure value; and a second closed-loop control system for automatically controlling turbine speed by means of a turbine speed controller, which determines a second correcting variable (SG2) for influencing the flow-through turbine cross section from a deviation (dnT) of an actual turbine speed from a set turbine speed, the second closed-loop control system being subordinate to the first closed-loop control system, and the first correcting variable (SG1) corresponding to a reference input of the second closed-loop control system, and further comprising a first input-output map (KF1) for computing a first set charge air pressure, a second input-output map (KF2) for computing a second set charge air pressure, and a switch for selecting the first input-output map (KF1) or the second input-output map (KF2) for determining the reference input of the first closed-loop control system. 11. A device for closed-loop control of at least a first exhaust gas turbocharger with variable turbine geometry, comprising: a first closed-loop control system for automatically controlling charge air pressure by means of a charge air pressure controller, which determines a first correcting variable (SG1) for influencing a flow-through turbine cross section from a deviation (dpLL) of an actual charge air pressure value from a set charge air pressure value; and a second closed-loop control system for automatically controlling turbine speed by means of a turbine speed controller, which determines a second correcting variable (SG2) for influencing the flow-through turbine cross section from a deviation (dnT) of an actual turbine speed from a set turbine speed, the second closed-loop control system being subordinate to the first closed-loop control system, and the first correcting variable (SG1) corresponding to a reference input of the second closed-loop control system, and further comprising a first synchronization controller for synchronizing the first exhaust gas turbocharger and a second exhaust gas turbocharger with variable turbine geometry by means of a third correcting variable (SG3). 12. The device in accordance with claim 11, wherein an input variable of the first synchronization controller corresponds to a difference (DIFF) between turbine speeds (nT1, nT2) of the first exhaust gas turbocharger and the second exhaust gas turbocharger. 13. The device in accordance with claim 11, wherein the third correcting variable (SG3) and the second correcting variable (SG2) are the input variables of the first exhaust gas turbocharger. 14. The device in accordance with claim 11, and further comprising a maximum value selector (MAX) for determining turbine actual speed (nT(IST)) from turbine speeds (nT1, nT2) of the first exhaust gas turbocharger and the second exhaust gas turbocharger. 15. A device for closed-loop control of at least a first exhaust gas turbocharger with variable turbine geometry, comprising: a first closed-loop control system for automatically controlling charge air pressure by means of a charge air pressure controller, which determines a first correcting variable (SG1) for influencing a flow-through turbine cross section from a deviation (dpLL) of an actual charge air pressure value from a set charge air pressure value; and a second closed-loop control system for automatically controlling turbine speed by means of a turbine speed controller, which determines a second correcting variable (SG2) for influencing the flow-through turbine cross section from a deviation (dnT) of an actual turbine speed from a set turbine speed, the second closed-loop control system being subordinate to the first closed-loop control system, and the first correcting variable (SG1) corresponding to a reference input of the second closed-loop control system, and further comprising a second synchronization controller for synchronizing the first exhaust gas turbocharger and a second exhaust gas turbocharger with variable turbine geometry by means of a third correcting variable (SG3). 16. The device in accordance with claim 15, wherein an input variable of the second synchronization controller corresponds to a difference (DIFF) between the air masses (LM1, LM2) of the first exhaust gas turbocharger and the second exhaust gas turbocharger. 17. The device in accordance with claim 15, wherein the third correcting variable (SG3) and the second correcting variable (SG2) are the input variables of the first exhaust gas turbocharger. 18. The device in accordance with claim 15, and further comprising a maximum value selector (MAX) for determining turbine actual speed (nT(IST)) from turbine speeds (nT1, nT2) of the first exhaust gas turbocharger and the second exhaust gas turbocharger. 19. A device for closed-loop control of at least a first exhaust gas turbocharger with variable turbine geometry, comprising: a first closed-loop control system for automatically controlling charge air pressure by means of a charge air pressure controller, which determines a first correcting variable (SG1) for influencing a flow-through turbine cross section from a deviation (dpLL) of an actual charge air pressure value from a set charge air pressure value; and a second closed-loop control system for automatically controlling turbine speed by means of a turbine speed controller, which determines a second correcting variable (SG2) for influencing the flow-through turbine cross section from a deviation (dnT) of an actual turbine speed from a set turbine speed, the second closed-loop control system being subordinate to the first closed-loop control system, and the first correcting variable (SG1) corresponding to a reference input of the second closed-loop control system, and further comprising an end of tape control block for synchronizing the first exhaust gas turbocharger and a second exhaust gas turbocharger with variable turbine geometry by means of a third correcting variable (SG3). 20. The device in accordance with claim 19, wherein the third correcting variable (SG3) and the second correcting variable (SG2) are the input variables of the first exhaust gas turbocharger. 21. The device in accordance with claim 19, and further comprising a maximum value selector (MAX) for determining turbine actual speed (nT(IST)) from turbine speeds (nT1, nT2) of the first exhaust gas turbocharger and the second exhaust gas turbocharger. 22. A device for closed-loop control of at least a first exhaust gas turbocharger with variable turbine geometry, comprising: a first closed-loop control system for automatically controlling charge air pressure by means of a charge air pressure controller, which determines a first correcting variable (SG1) for influencing a flow-through turbine cross section from a deviation (dpLL) of an actual charge air pressure value from a set charge air pressure value; and a second closed-loop control system for automatically controlling turbine speed by means of a turbine speed controller, which determines a second correcting variable (SG2) for influencing the flow-through turbine cross section from a deviation (dnT) of an actual turbine speed from a set turbine speed, the second closed-loop control system being subordinate to the first closed-loop control system, and the first correcting variable (SG1) corresponding to a reference input of the second closed-loop control system, wherein the charge air pressure controller comprises a PI controller, an input-output map input control, a functional block for computing a maximum turbine speed (nTMAX), a functional block for determining a maximum amplitude (AMP), a minimum value selector (MIN), and a functional block for limiting an I component. 23. A method for closed-loop control of at least a first exhaust gas turbocharger with variable turbine geometry, comprising the steps of: automatically controlling charge air pressure by means of a first closed-loop control system, which has a charge air pressure controller that determines a first correcting variable (SG1) for influencing a flow-through turbine cross section from a deviation (dpLL) of an actual charge air pressure value from a set charge air pressure value; and automatically controlling turbine speed by means of a second closed-loop control system, which has a turbine speed controller that determines a second correcting variable (SG2) for influencing the flow-through turbine cross section (AT) from a deviation (dnT) of an actual turbine speed value from a set turbine value, the second closed-loop control system being subordinate to the first closed-loop control system, and a reference input of the second closed-loop control system being determined from the first correcting variable (SG1), including determining a reference input of the first closed-loop control system by means of a first input-output map (KF1) or a second input-output map (KF2), including computing the first correcting variable (SG1) by means of a device in accordance with claim 22. 24. A device for closed-loop control of at least a first exhaust gas turbocharger with variable turbine geometry, comprising: a first closed-loop control system for automatically controlling charge air pressure by means of a charge air pressure controller, which determines a first correcting variable (SG1) for influencing a flow-through turbine cross section from a deviation (dpLL) of an actual charge air pressure value from a set charge air pressure value; and a second closed-loop control system for automatically controlling turbine speed by means of a turbine speed controller, which determines a second correcting variable (SG2) for influencing the flow-through turbine cross section from a deviation (dnT) of an actual turbine speed from a set turbine speed, the second closed-loop control system being subordinate to the first closed-loop control system, and the first correcting variable (SG1) corresponding to a reference input of the second closed-loop control system, wherein the turbine speed controller comprises a PI controller, a functional block for limiting the I component, a DT1 input control, a charge air pressure input control, a surge protection input-output map, and a functional block for determining a maximum flow-through turbine cross section (ATMAX). 25. A method for closed-loop control of at least a first exhaust gas turbocharger with variable turbine geometry, comprising the steps of: automatically controlling charge air pressure by means of a first closed-loop control system, which has a charge air pressure controller that determines a first correcting variable (SG1) for influencing a flow-through turbine cross section from a deviation (dpLL) of an actual charge air pressure value from a set charge air pressure value; and automatically controlling turbine speed by means of a second closed-loop control system, which has a turbine speed controller that determines a second correcting variable (SG2) for influencing the flow-through turbine cross section (AT) from a deviation (dnT) of an actual turbine speed value from a set turbine value, the second closed-loop control system being subordinate to the first closed-loop control system, and a reference input of the second closed-loop control system being determined from the first correcting variable (SG1), including determining a reference input of the first closed-loop control system by means of a first input-output map (KF1) or a second input-output map (KF2), including computing the second correcting variable (SG2) by means of a device in accordance with claim 24.