发明名称 EXHAUST-GAS TURBOCHARGER
摘要 An exhaust-gas turbocharger, preferably for a passenger vehicle, including a turbine having a turbine wheel and a turbine housing. A number of S≧2 of channels are formed in the turbine housing and are intended for guiding the exhaust gas onto the turbine wheel. Each channel directs flow against the turbine wheel over the entire width of the latter, as seen in the axial direction, and over a segment, as seen in relation to the circumferential direction. The turbine wheel has a number of Z≧10 turbine blades. The turbine blades are defined in the faun of main blades and intermediate blades. The intermediate blades, at least at their hub-side ends, do not extend as far toward the turbine outlet, as seen in the axial direction, as the main blades.
申请公布号 US2017107896(A1) 申请公布日期 2017.04.20
申请号 US201515310145 申请日期 2015.05.19
申请人 BorgWarner Inc. 发明人 GUGAU Marc;SCHERI Alessio
分类号 F02B37/02;F01D25/24;F01D5/14;F01D5/04 主分类号 F02B37/02
代理机构 代理人
主权项 1. An exhaust-gas gas turbocharger (1) comprising a compressor (2) having a compressor wheel (3), a turbine (4) having a turbine wheel (5) and a turbine housing (6), a shaft (7), which connects the compressor wheel (3) to the turbine wheel (5), and a number of S≧2 of channels (13, 14), which are formed in the turbine housing (6) and are intended for guiding the exhaust gas onto the turbine wheel (5), wherein an axial direction (8) is defined along the shaft (7), from the compressor (2) to the turbine (4), a radial direction (9) is defined perpendicularly to the axial direction (8), and a circumferential direction (10) is defined around the axial direction (8), counter to the direction of rotation of the turbine wheel (5), wherein each channel (13, 14) directs flow against the turbine wheel (5) over the entire width of the latter, as seen in the axial direction (8), and over a segment, as seen in relation to the circumferential direction (10), wherein the turbine wheel (5) comprises a number of Z≧10 turbine blades (12), and wherein the turbine blades (12) are defined in the form of main blades (22) and intermediate blades (23), wherein the intermediate blades (23), at least at their hub-side ends (24), do not extend as far toward the turbine outlet, as seen in the axial direction (8), as the main blades (22).
地址 Auburn Hills MI US
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