초록 ▼

A method for operating an internal combustion engine includes compressing intake air using a compressor, supplying the compressed intake air to at least one combustion chamber of the engine, operating the at least one combustion chamber to output exhaust gas, and directing the exhaust gas to an inle

A method for operating an internal combustion engine includes compressing intake air using a compressor, supplying the compressed intake air to at least one combustion chamber of the engine, operating the at least one combustion chamber to output exhaust gas, and directing the exhaust gas to an inlet of a turbine configured to drive the compressor. The method also includes directing the exhaust gas from an outlet of the turbine to an exhaust system, bypassing at least a portion of the compressed intake air around the at least one combustion chamber, and adjusting a geometry of the turbine from a first configuration to a second configuration. The turbine is in the second configuration when the at least the portion of the compressed intake air is bypassed around the at least one combustion chamber.

대표청구항 ▼

What is claimed is: 1. A method for operating an internal combustion engine, comprising: compressing intake air using a compressor; supplying the compressed intake air to at least one combustion chamber of the engine; operating the at least one combustion chamber to output exhaust gas; directing th

What is claimed is: 1. A method for operating an internal combustion engine, comprising: compressing intake air using a compressor; supplying the compressed intake air to at least one combustion chamber of the engine; operating the at least one combustion chamber to output exhaust gas; directing the exhaust gas to an inlet of a turbine configured to drive the compressor; directing the exhaust gas from an outlet of the turbine to an exhaust system; determining a speed of the engine; decreasing the speed of the engine by determining a desired second configuration of the turbine, adjusting a turbine geometry from a first configuration to the desired second configuration based on the determined engine speed, and bypassing at least a portion of the compressed intake air around the at least one combustion chamber when the turbine is in the desired second configuration; wherein the adjusting of the turbine geometry to the second configuration includes locking a plurality of vanes of the turbine at a restricted position and maintaining the plurality of vanes at the restricted position until a predetermined engine operating condition is fulfilled. 2. The method of claim 1, further including: determining an operating condition of the engine; and determining an amount of the compressed intake air bypassing the combustion chamber based on the operating condition of the engine. 3. The method of claim 1, wherein the bypassing of the at least the portion of the compressed intake air around the at least one combustion chamber includes directing the portion of the compressed intake air through a bypass flow path fluidly connecting an outlet of the compressor to the exhaust system. 4. The method of claim 3, wherein the bypassing of the at least the portion of the compressed intake air around the at least one combustion chamber includes controlling a bypass valve disposed in the bypass flow path, the bypass valve controlling an amount of the compressed intake air bypassing the at least one combustion chamber. 5. The method of claim 4, further including determining a position of the bypass valve based on the engine speed. 6. The method of claim 1, wherein the adjusting of the turbine geometry to the second configuration includes setting a plurality of vanes of the turbine at a restricted position when the at least the portion of the compressed intake air is bypassed around the at least one combustion chamber. 7. The method of claim 6, further including decreasing the amount of the compressed intake air bypassing the at least one combustion chamber when the turbine geometry is set at the restricted position. 8. The method of claim 6, wherein the adjusting of the turbine geometry is based on the engine speed and a desired pressure drop across the turbine. 9. The method of claim 1, wherein the predetermined condition is a signal from an operator input device. 10. The method of claim 1, further including permitting substantially all of the compressed intake air to flow to the at least one combustion chamber when the turbine is in the first configuration. 11. The method of claim 1, further including directing the compressed intake air bypassing the at least one combustion chamber to an aftertreatment system of the exhaust system. 12. The method of claim 11, further including mixing the compressed intake air directed to the aftertreatment system with fuel. 13. The method of claim 12, further including igniting the mixture of the compressed intake air and fuel. 14. The method of claim 1, further including: sensing an operating condition of the engine; and adjusting the amount of the compressed intake air bypassing the at least one combustion chamber based on the sensed condition when the turbine geometry is locked in the second configuration. 15. The method of claim 1, further including: determining whether a predetermined engine operating condition is fulfilled; and determining whether to initiate decreasing the engine speed of the engine in response to determining that the predetermined engine operating condition is fulfilled. 16. The method of claim 15, wherein the predetermined condition includes a signal from an operator input device. 17. The method of claim 1, wherein the determining the desired second configuration of the turbine is based on at least one of a determined engine operating condition and a parameter related to an amount of the compressed air bypassing the combustion chamber. 18. The method of claim 1, wherein the determining the desired second configuration of the turbine includes determining a degree to which a variable geometry unit of the turbine is opened. 19. A method for operating an internal combustion engine, comprising: compressing intake air using a compressor; supplying the compressed intake air to at least one combustion chamber of the engine; directing at least a portion of the compressed intake air through a bypass flow path toward an exhaust system; operating the at least one combustion chamber to output exhaust gas; directing the exhaust gas to a turbine configured to drive the compressor; directing the exhaust gas from the turbine to the exhaust system; and maintaining a desired characteristic of the turbine by controlling an amount of the compressed intake air directed to the at least one combustion chamber; wherein the maintaining of the desired turbine characteristic further includes adjusting of a turbine geometry, wherein the adjusting of the turbine geometry includes setting the turbine geometry at a restricted position when the at least a portion of the compressed intake air is directed through the bypass flow path, and wherein the maintaining of the desired turbine characteristic further includes decreasing an amount of the compressed intake air flowing through the bypass flow path while maintaining the turbine geometry at the restricted position. 20. The method of claim 19, wherein the desired turbine characteristic is a desired range of pressure drop. 21. The method of claim 19, wherein the maintaining of the desired turbine characteristic further includes: determining an engine speed; and determining an amount of the compressed intake air directed through the bypass flow path based on the determined engine speed and the desired turbine characteristic. 22. The method of claim 19, wherein the setting of the turbine at the restricted position includes determining the restricted position based on the desired turbine characteristic.