[특허]Method and apparatus for internal combustion engine system with improved turbocharging

[미국특허] Method and apparatus for internal combustion engine system with improved turbocharging 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02B-037/007 F02M-025/07 F02B-075/02 F02B-037/00 F02B-037/18 F02B-075/18
출원번호	US-0238991 (2016-08-17)
등록번호	US-9765685 (2017-09-19)
발명자 / 주소	Clarke, James R. Fotsch, Richard J.
출원인 / 주소	Bright Acceleration Technologies LLC
대리인 / 주소	Sylke, C. Thomas
인용정보	피인용 횟수 : 0 인용 특허 : 52

초록 ▼

Systems, methods, apparatus provide improved turbocharging of an internal combustion engine. A single, discrete turbocharger is affixed to each engine combustion cylinder. Turbochargers can be mounted to their associated cylinders in close proximity, thus harvesting higher energy exhaust gases from each combustion cylinder. Tip in and spool up responses can be further improved using low rotational inertia turbochargers that can operate effectively across a wide range of engine operational speeds. Controlled balancing valves between cylinder exhaust lines can deliver exhaust gases from a single cylinder selectively to multiple turbochargers in appropriate operational conditions. Moreover, multiple turbochargers' compressors can be configured in series to achieve pressurization compounding of combustion air for low RPM operation. Nesting of turbochargers relative to one another permits improved mounting of each turbocharger in close proximity to its corresponding combustion cylinder.

대표청구항 ▼

1. An internal combustion engine system comprising: an engine block and a cylinder head defining a plurality of combustion cylinders comprising a first combustion cylinder, a second combustion cylinder, and a third combustion cylinder, wherein each combustion cylinder comprises an exhaust valve through which exhaust gas is discharged during operation of the engine system;a first turbocharger assembly comprising a turbine inlet affixed in close proximity to the first combustion cylinder exhaust valve;a second turbocharger assembly comprising a turbine inlet affixed in close proximity to the second combustion cylinder exhaust valve; anda third turbocharger assembly comprising a turbine inlet affixed in close proximity to the third combustion cylinder exhaust valve. 2. The engine system of claim 1 wherein the first turbocharger assembly turbine inlet is connected to the second turbocharger assembly turbine inlet by a first balancing valve, wherein the first balancing valve controls exhaust gas flow between the first turbocharger assembly turbine inlet and the second turbocharger assembly turbine inlet; further wherein the second turbocharger assembly turbine inlet is connected to the third turbocharger assembly turbine inlet by a second balancing valve, wherein the second balancing valve controls exhaust gas flow between the second turbocharger assembly turbine inlet and the third turbocharger assembly turbine inlet. 3. The engine system of claim 2 further comprising an engine control unit coupled to control operation of the engine system. 4. The engine system of claim 1 wherein the first, second and third turbocharger assemblies are affixed in a nested configuration. 5. The engine system of claim 1 wherein each turbocharger assembly is mounted at an angular orientation between approximately 15° and 75°, wherein the angular orientation of each turbocharger assembly is an angle between a line connecting cylinder head exhaust port centers and a turbocharger shaft axis, in a plane parallel with a cylinder head exhaust face. 6. The engine system of claim 1 wherein each turbocharger assembly comprises a low-inertia turbocharger. 7. The engine system of claim 1 wherein the first turbocharger assembly comprises a low-inertia turbocharger having a turbine wheel diameter that is less than the diameter of the first combustion cylinder; further wherein the second turbocharger assembly comprises a low-inertia turbocharger having a turbine wheel diameter that is less than the diameter of the second combustion cylinder; andfurther wherein the third turbocharger assembly comprises a low-inertia turbocharger having a turbine wheel diameter that is less than the diameter of the third combustion cylinder. 8. The engine system of claim 1 wherein the first turbocharger assembly turbine inlet is affixed not more than 6 inches from the first combustion cylinder exhaust valve; further wherein the second turbocharger assembly turbine inlet is affixed not more than 6 inches from the second combustion cylinder exhaust valve;further wherein the third turbocharger assembly turbine inlet is affixed not more than 6 inches from the third combustion cylinder exhaust valve. 9. The engine system of claim 1 further comprising first means connecting the first turbocharger assembly turbine inlet and the second turbocharger assembly turbine inlet for balancing exhaust gas flow between the first turbocharger assembly turbine inlet and the second turbocharger assembly turbine inlet; and further comprising second means connecting the second turbocharger assembly turbine inlet and the third turbocharger assembly turbine inlet for balancing exhaust gas flow between the second turbocharger assembly turbine inlet and the third turbocharger assembly turbine inlet. 10. A spark-ignited, internal combustion, 3-cylinder engine system comprising: a first combustion cylinder assembly, a second combustion cylinder assembly, and a third combustion cylinder assembly, wherein each combustion cylinder assembly comprises: a combustion cylinder having an exhaust valve through which exhaust gas is discharged during operation of the engine system; anda turbocharger assembly comprising a turbine inlet affixed in close proximity to the exhaust valve of the combustion cylinder, wherein each turbine inlet receives pulse-characteristic-possessing exhaust gas from the combustion cylinder. 11. The engine system of claim 10 wherein the first combustion cylinder assembly turbine inlet is affixed not more than 6 inches from the first combustion cylinder assembly exhaust valve; further wherein the second combustion cylinder assembly turbine inlet is affixed not more than 6 inches from the second combustion cylinder assembly exhaust valve;further wherein the third combustion cylinder assembly turbine inlet is affixed not more than 6 inches from the third combustion cylinder assembly exhaust valve. 12. The engine system of claim 11 wherein each turbocharger assembly comprises a low-inertia turbocharger. 13. The engine system of claim 11 wherein each turbocharger assembly comprises a turbine wheel having a diameter that is less than 3 inches. 14. The engine system of claim 10 further comprising first means connecting the first combustion cylinder assembly turbocharger turbine inlet and the second combustion cylinder assembly turbocharger turbine inlet for balancing exhaust gas flow between the first combustion cylinder assembly turbocharger turbine inlet and the second combustion cylinder assembly turbocharger turbine inlet; and further comprising second means connecting the second combustion cylinder assembly turbocharger turbine inlet and the third combustion cylinder assembly turbocharger turbine inlet for balancing exhaust gas flow between the second combustion cylinder assembly turbocharger turbine inlet and the third combustion cylinder assembly turbocharger turbine inlet. 15. The engine system of claim 10 wherein the first combustion cylinder assembly turbine inlet is affixed not more than 10 inches from the first combustion cylinder assembly exhaust valve; further wherein the second combustion cylinder assembly turbine inlet is affixed not more than 10 inches from the second combustion cylinder assembly exhaust valve; andfurther wherein the third combustion cylinder assembly turbine inlet is affixed not more than 10 inches from the third combustion cylinder assembly exhaust valve. 16. The engine system of claim 10 wherein the first combustion cylinder assembly turbocharger turbine inlet and the second combustion cylinder assembly turbocharger turbine inlet are connected by a first balancing valve controlling cross-flow of exhaust gas between the first combustion cylinder assembly turbocharger turbine inlet and the second combustion cylinder assembly turbocharger turbine inlet; further wherein the second combustion cylinder assembly turbocharger turbine inlet and the third combustion cylinder assembly turbocharger turbine inlet are connected by a second balancing valve controlling cross-flow of exhaust gas between the second combustion cylinder assembly turbocharger turbine inlet and the third combustion cylinder assembly turbocharger turbine inlet;further wherein the first and second balancing valves are configured to reduce turbulence and improve stability at high loads at each turbine inlet. 17. An internal combustion engine system comprising: a plurality of combustion cylinders comprising a first combustion cylinder, a second combustion cylinder, and a third combustion cylinder, wherein each combustion cylinder comprises an exhaust valve through which exhaust gas is discharged during operation of the engine system;a first turbocharger assembly comprising a turbine inlet affixed not more than 6 inches from the first combustion cylinder exhaust valve;a second turbocharger assembly comprising a turbine inlet affixed not more than 6 inches from the second combustion cylinder exhaust valve; anda third turbocharger assembly comprising a turbine inlet affixed not more than 6 inches from the third combustion cylinder exhaust valve. 18. The engine system of claim 17 wherein each turbocharger assembly further comprises a low-inertia turbine wheel driven by exhaust gas. 19. The engine system of claim 18 further comprising first means connecting the first turbocharger assembly turbine inlet and the second turbocharger assembly turbine inlet for balancing exhaust gas flow between the first turbocharger assembly turbine inlet and the second turbocharger assembly turbine inlet; and further comprising second means connecting the second turbocharger assembly turbine inlet and the third turbocharger assembly turbine inlet for balancing exhaust gas flow between the second turbocharger assembly turbine inlet and the third turbocharger assembly turbine inlet. 20. The engine system of claim 19 wherein each turbocharger assembly is mounted to the cylinder head at an angular orientation between approximately 15° and 75°, wherein the angular orientation of each turbocharger assembly is the angle between a line connecting cylinder head exhaust port centers and a turbocharger shaft axis, in a plane parallel with a cylinder head exhaust face.

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[미국특허] Method and apparatus for internal combustion engine system with improved turbocharging 원문보기

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[미국특허] Method and apparatus for internal combustion engine system with improved turbocharging 원문보기

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