IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0799182
(2010-04-19)
|
등록번호 |
US-8453448
(2013-06-04)
|
발명자
/ 주소 |
- Lotterman, Jeffrey A.
- Kares, Vaclav
|
출원인 / 주소 |
- Honeywell International Inc.
|
대리인 / 주소 |
The Law Office of John A. Griecci
|
인용정보 |
피인용 횟수 :
4 인용 특허 :
7 |
초록
▼
A turbocharger including a turbine wheel having a hub-to-tip ratio of no more than 60% and blades with a high turning angle, a turbine housing forming an inwardly spiraling primary-scroll passageway that significantly converges to produce highly accelerated airflow into the turbine at high circumfer
A turbocharger including a turbine wheel having a hub-to-tip ratio of no more than 60% and blades with a high turning angle, a turbine housing forming an inwardly spiraling primary-scroll passageway that significantly converges to produce highly accelerated airflow into the turbine at high circumferential angles, and a two-sided parallel compressor. The compressor and turbine each produce substantially no axial force, allowing the use of minimal axial thrust bearings.
대표청구항
▼
1. A turbocharger configured to receive an exhaust gas stream from an engine configured to operate over a range of standard operating conditions, and to compress input air into a pressurized air stream, comprising: a housing including a turbine housing; anda rotor configured to rotate within the hou
1. A turbocharger configured to receive an exhaust gas stream from an engine configured to operate over a range of standard operating conditions, and to compress input air into a pressurized air stream, comprising: a housing including a turbine housing; anda rotor configured to rotate within the housing along an axis of rotor rotation, the rotor including an axial turbine wheel, a compressor wheel, and a shaft extending along the axis of rotor rotation and connecting the turbine wheel to the compressor wheel;wherein the turbine wheel is configured with a hub, and with a plurality of axial turbine blades configured to drive the rotor in rotation around the axis of rotor rotation when the turbocharger receives the exhaust gas stream from the engine, the blades having an axially upstream edge, an axially downstream edge, a hub end, and a tip end opposite the hub end;wherein the compressor wheel is configured to compress the input air into the pressurized air stream when the rotor is driven in rotation around the axis of rotor rotation by the turbine wheel; andwherein the turbine housing forms an inwardly spiraling turbine primary-scroll passageway characterized by a primary-scroll inlet port characterized by a centroid that is radially external to the axially upstream ends of the blades. 2. The turbocharger of claim 1, the engine exhaust gas stream being characterized by gas-specific attributes including a specific gas constant Rsp and a Boltzmann constant k, wherein: the primary-scroll inlet port is further characterized by an area;the axially upstream edges of the turbine wheel blades define a turbine wheel inlet, the turbine wheel inlet being characterized by an area;the combined turbine housing and turbine wheel are characterized by a primary-scroll radius ratio rr defined as a radius of the hub at the axially upstream edge of the blade, divided by a radius of the centroid of the primary-scroll inlet port;the combined turbine housing and turbine wheel are further characterized by a corrected mass flow rate surface density at the primary-scroll inlet port when driven at a critical expansion ratio Ecr;the primary-scroll radius ratio rr and the primary-scroll inlet port area are sized such that the corrected mass flow rate surface density at the primary-scroll inlet port when driven at the critical expansion ratio Ecr is greater than a critical corrected mass flow rate surface density Dcr; andthe values of Dcr and Ecr are determined by the equations Dcr=rr101325288Rsp(1-(k-1)(rr)2(k+1))(1k-1)2kk+1andEcr=(k+12)(kk-1). 3. The turbocharger of claim 2, wherein the radius at the hub end of each turbine wheel trailing edge is no more than 60% of the radius of the tip end of each turbine wheel trailing edge. 4. The turbocharger of claim 3, wherein the turbine blades are each characterized by a blade turning angle at the hub that is greater than or equal to 45 degrees. 5. The turbocharger of claim 4, wherein the turbine blades are each characterized by a blade turning angle at an intermediate radius between the hub and the tip that is greater than or equal to 80 degrees. 6. The turbocharger of claim 3, wherein the turbine blades are each characterized by a blade turning angle at an intermediate radius between the hub and the tip that is greater than or equal to 80 degrees. 7. The turbocharger of claim 2, wherein the inwardly spiraling turbine primary-scroll passageway is a vaneless passageway. 8. A turbocharged internal combustion engine system, comprising: an engine configured to receive a pressurized air stream and to produce an exhaust gas stream, the engine being configured to operate over the range of standard operating conditions; andthe turbocharger of claim 2, the turbocharger being configured to receive the exhaust gas stream from the engine when operating in the standard operating conditions, and to compress input air into the pressurized air stream received by the engine. 9. The turbocharged internal combustion engine system of claim 8, wherein the inwardly spiraling primary-scroll passageway substantially forms a convergent passageway that turns axially downstream and spirals inward enough to cause the input air to achieve supersonic speeds when reaching the upstream edges of the turbine wheel blades for at least some operating conditions of the range of standard operating conditions. 10. A turbocharger configured to receive an exhaust gas stream from an engine configured to operate over a range of standard operating conditions, and to compress input air into a pressurized air stream, comprising: a housing including a turbine housing; anda rotor configured to rotate within the housing along an axis of rotor rotation, the rotor including an axial turbine wheel, a compressor wheel, and a shaft extending along the axis of rotor rotation and connecting the turbine wheel to the compressor wheel;wherein the turbine wheel is configured with a hub, and with a plurality of axial turbine blades configured to drive the rotor in rotation around the axis of rotor rotation when the turbocharger receives the exhaust gas stream from the engine, the blades having an axially upstream edge, an axially downstream edge, a hub end, and a tip end opposite the hub end;wherein the compressor wheel is configured to compress the input air into the pressurized air stream when the rotor is driven in rotation around the axis of rotor rotation by the turbine wheel;wherein the turbine housing forms an inwardly spiraling turbine primary-scroll passageway; andwherein the turbine is configured to limit the static pressure upstream of the wheel near the wheel hub to a value that is not greater than 120% of the turbine outlet static pressure for at least some operating conditions of the range of standard operating conditions. 11. The turbocharger of claim 10, the engine exhaust gas stream being characterized by gas-specific attributes including a specific gas constant Rsp and a Boltzmann constant k, wherein: wherein the turbine housing forms an inwardly spiraling turbine primary-scroll passageway forming a primary-scroll inlet port characterized by an area and a centroid;the axially upstream edges of the turbine wheel blades define a turbine wheel inlet, the turbine wheel inlet being characterized by an area;the combined turbine housing and turbine wheel are characterized by a primary-scroll radius ratio rr defined as a radius of the hub at the axially upstream edge of the blade, divided by a radius of the centroid of the primary-scroll inlet port;the combined turbine housing and turbine wheel are further characterized by a corrected mass flow rate surface density at the primary-scroll inlet port when driven at a critical expansion ratio Ecr;the primary-scroll radius ratio rr and the primary-scroll inlet port area are sized such that the corrected mass flow rate surface density at the primary-scroll inlet port when driven at the critical expansion ratio Ecr is greater than a critical corrected mass flow rate surface density Dcr; andthe values of Dcr and Ecr are determined by the equations Dcr=rr101325288Rsp(1-(k-1)(rr)2(k+1))(1k-1)2kk+1andEcr=(k+12)(kk-1). 12. The turbocharger of claim 11, wherein the radius at the hub end of each turbine wheel trailing edge is no more than 60% of the radius of the tip end of each turbine wheel trailing edge. 13. The turbocharger of claim 12, wherein the turbine blades are each characterized by a blade turning angle at the hub that is greater than or equal to 45 degrees. 14. The turbocharger of claim 13, wherein the turbine blades are each characterized by a blade turning angle at an intermediate radius between the hub and the tip that is greater than or equal to 80 degrees. 15. The turbocharger of claim 12, wherein the turbine blades are each characterized by a blade turning angle at an intermediate radius between the hub and the tip that is greater than or equal to 80 degrees. 16. The turbocharger of claim 11, wherein the inwardly spiraling turbine primary-scroll passageway is a vaneless passageway. 17. A turbocharged internal combustion engine system, comprising: an engine configured to receive a pressurized air stream and to produce an exhaust gas stream, the engine being configured to operate over the range of standard operating conditions; andthe turbocharger of claim 11, the turbocharger being configured to receive the exhaust gas stream from the engine when operating in the standard operating conditions, and to compress input air into the pressurized air stream received by the engine. 18. The turbocharged internal combustion engine system of claim 17, wherein the inwardly spiraling primary-scroll passageway substantially forms a convergent passageway that turns axially downstream and spirals inward enough to cause the input air to achieve supersonic speeds when reaching the upstream edges of the turbine wheel blades for at least some operating conditions of the range of standard operating conditions.
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