Journal of Aerospace Power Vol. 25 No. 3 Mar : (2010) , 1, 2, 1, 1 (11, ; 21, ) : CFD ( ),,., ;.,,

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1 Journal of Aerospace Power Vol. 25 No. 3 Mar : (2010) , 1, 2, 1, 1 (11, ; 21, ) : CFD ( ),,., ;.,, ;,. : ; ; ; : T K : A Research on the effect of centrif ugal compressor blade tip clearance distribution on conbustion engine turbocharger perf ormance GUO Gong2da 1, ZHAN G Yang2jun 1, XU Jian2zhong 2, ZH EN G Xin2qian 1, ZHU GE Wei2lin 1 (11 State Key Laboratory of Automotive Safety and Energy, Department of Automotive Engineering, School of Mechanical Engineering, Tsinghua U niver sit y, Beijing , China ; 21 Instit ute of Engineering Thermop hysics, Chinese Academy of Science, Beijing , China) Abstract : Based o n t hree2dimensio nal co mp utatio nal fluid dynamics met hod, t he flow fields of two opposite impeller blade tip clearance distribution compressor stages wit h vane2 less diff user were analyzed. The law and actio n mechanism of tip clearance dist ributio n effect o n t he high charging ratio t ranso nic cent rif ugal co mp ressor impeller and vaneless diff user performance were researched. This p roves t hat no n2uniform cho rd directio n blade tip clear2 ance dist ributio n impellers have wider operating range. The p ressure ratio and efficiency of co mp ressor stage who se o utlet axial clearance height is smaller t han inlet radial clearance height are higher t han that of compressor stage whose outlet axial clearance height is larger t han inlet radial clearance height. The smaller o utlet axial clearance height weakens t he clearance flow in aft half of impeller passage, improves the impeller aft passage power inp ut and obtains higher impeller pressure ratio and compressor stage pressure ratio. The smaller outlet axial clearance height get s higher efficiency since it reduces impeller aft blade tip clear2 ance leakage vortices intensity and makes t he vortices breakdown and dissipation loss less in impeller passage and vaneless diff user passage. : ; : : ( ) : ( ),,,,.

2 Key words : tip clearance ; internal combustion engine ; t urbocharger ; centrif ugal compressor,,80 %, [ 1 ].,, CO2.,, [ 2 ].,,,,,,.,, : [ 328 ],. : [ 9 ], [ 10 ].,. CFD ( ),,,,.. J ameson, ; Runge2Kutta ; Spalart2Allmaras (S2A),. [ 11 ]. [11 ], [12 ] :,. 2 / 3 9, 1. (a). (b). : 1 Navier2Stokes (N2S),,, 5U 5t + Fi + Fv = Q (1) U, Fi Fv,Q 1 Fig. 1 Blade tip clearance distribution

3 : 551 1) 3 : 012 mm2012 mm,015 mm2015 mm,110 mm2110 mm. 2) 3 :015 mm2012 mm,110 mm2012 mm, 110 mm2015 mm. 3) 3 :012 mm2015 mm,012 mm2110 mm, 015 mm2110 mm. 30 %,. 2) 3) 6, 1 (b). 3 311 9.

3 3 : 551 1) 3 : 012 mm2012 mm,015 mm2015 mm,110 mm2110 mm. 2) 3 :015 mm2012 mm,110 mm2012 mm, 110 mm2015 mm. 3) 3 :012 mm2015 mm,012 mm2110 mm, 015 mm2110 mm. 30 %,. 2) 3) 6, 1 (b) mm, [ 11 ], %. 1 2.,, 0101 kg/ s.,,110 mm2012 mm.. 2 4, :012 mm2012 mm ; 110 mm2110 mm ; 012 mm2 110 mm 110 mm2012 mm,110 mm2012 mm.,. 1 Table 1 Clearance distribution effect on choke boundary / mm / (kg/ s) / mm Table 2 Clearance distribution effect on surge boundary / mm / (kg/ s) / mm Fig12 Clearance height distribution along chord effect on operating range kg/ s ( 1).,9 ( 012 mm2012 mm ) 4 ( 1).,012 mm2012 mm,,, [ 328 ]. 012 mm2012 mm 015 mm2 015 mm, 013, 1 % ; 015 mm2015 mm 110 mm2110 mm, 0125, 6 %. 012 mm, 012 mm 015 mm 015 mm

4 Fig. 3 Compressor stage performance at different clearance distributions mm2012 mm Fig. 4 Compressor stage performance drop at different clearance distributions compared with 012 mm201 2 mm compressor stage 110 mm,, , 1 % 3 % ; 01 2 mm, 012 mm 015 mm 015 mm 110 mm, , 1 % 3 %. 015 mm,,,,,. 4, 012 mm2110 mm 110 mm2012 mm,,, mm2110 mm 110 mm2012 mm 012 mm2012 mm S3.,

5 3 : %, 100 %, 200 %, 100 % 200 %. 012 mm2012 mm S mm2110 mm ;, ; 140 %, 110 mm2012 mm 012 mm2110 mm 2 % ;, 115 %. 5,,,,.,, ; 110 mm2012 mm 012 mm2110 mm, : 6, 110 mm2012 mm V10, 0. 2 mm21. 0 mm, 1 g/ (kw h). 110 mm2012 mm mm211 0 mm 11 0 mm2012 mm S3 Fig. 5 Relative performance drop on S3 sections of 01 2 mm2110 mm and 11 0 mm2012 mm compressor stages 5 70 %, 012 mm2110 mm 110 mm2012 mm ; 70 %, 012 mm2110 mm, 110 mm2012 mm 012 ;, 012 mm2110 mm 110 mm2 012 mm S3,012 mm2 110 mm 110 mm2012 mm, 42 %, 3 % ; 50 %,110 mm2012 mm 6 Fig. 6 Brake specific fuel consumption (BSFC) of the matched internal engine mm2012 mm, 012 mm2110 mm 110 mm2012 mm 3 S3 ( PS,SS, p s ss )., 012 mm2012 mm /, S3. 40 % S3,110 mm2012 mm, 012 mm2

6 S3 ( :s - 1 ) Fig. 7 Vorticity magnitude contour on S3 sections (unit :s - 1 ) 110 mm. 60 % S3,110 mm2012 mm 012 mm2110 mm,, 60 %. 80 % S3,012 mm2110 mm s mm2012 mm, s mm2012 mm,012 mm2110 mm,. 012 mm2110 mm 140 % S3,,012 mm2110 mm s mm2 012 mm mm2012 mm, 012 mm2110 mm 110 mm2 012 mm 3 S3

3 : 555 8 S3 ( :J/ (kg K) ) Fig. 8 Entropy contour on S3 sections (unit :J/ (kg K) ). S3 5, : 012 mm2012 mm,, 6.

7 3 : S3 ( :J/ (kg K) ) Fig. 8 Entropy contour on S3 sections (unit :J/ (kg K) ). S3 5, : 012 mm2012 mm,, mm2 110 mm 110 mm2012 mm, ; 80 % S3, 110 mm2012 mm 012 mm2110 mm,,, ; mm2 012 mm 012 mm2110 mm,.,,,. 4 1) ;. 012 mm2012 mm, 110 mm2110 mm, 012 mm2 110 mm 110 mm2012 mm, 110 mm2012 mm. 2), 70 %, 012 mm2110 mm 110 mm2 012 mm ; 70 %,. S3, ;, ;,.

8 556 25,,,,. 3) 9,, ;110 mm2012 mm 012 mm2110 mm, 1 g/ (kw h),.,,,. : [ 1 ]. [J ].,1998, (3) : CHEN Bingyi. Improvement of t he properties of aero2 engine by turbocompressor [ J ]. Aeronautical Science and Technology,1998, (3) : (in Chinese) [ 2 ] XU Jianzhong, WU Yulin, ZHAN G Yangjun,et al. Fluid machinery and fluid mechanics[ M ]. Beijing : Tsinghua Uni2 versity Press,2008 : [ 3 ] Senoo Y, Ishida M. Deterioration of compressor perform2 ance due to tip clearance of cent rifugal impellers[j ]. Jour2 nal of Turbomachinery,1987,109 (1) : [ 4 ] Schleer M. Flow structure and stability of a turbocharger centrifugal compressor [ D ]. Z rich, Switzerland : Swiss Federal Institute of Technology Z rich,20061 [ 5 ] Klassen H A,Wood J R,Schumann L F. Experimental per2 formance of a centimetre2tip2diameter tandem2blad2 ed sweptback centrifugal compressor designed for a pres2 sure ratio of 6[ R]. NASA Technical Paper 1091,1977. [ 6 ] Mashimo T, Watanabe I, Ariga I. Effect s of fluid leakage on performance of a centrifugal compressor [J ]. Journal of Engineering for Power,1979,101 (2) : [ 7 ],. [J ].,2003,21 (3) : YAN G Ce,WAN G Hang. Design and numerical investiga2 tion on a small mass flow rate centrifugal compressor [J ]. Transactions of Csice,2003,21 (3) : (in Chinese) [ 8 ] Schumann L F,Clark D A,Wood J R. Effect of area ratio on t he performance of a pressure ratio centrifugal impeller [ J ]. Journal of Turbomachinery, 1987, 109 ( 1) : [ 9 ] Backman J L H,Reunanen A. Effect s of impeller tip clear2 ance on centrifugal compressor efficiency[ R ]. ASME Paper GT ,20071 [ 10 ] Wei C, Grates D R. Numerical investigation of t he influ2 ence of t he tip clearance on wake formation inside a radial impeller[ R ]. ASME Paper GT ,20031 [ 11 ],,,. [J ]. ( ),2008, 48 (11) : GUO Gongda, ZHAN G Yangjun, ZH EN G Xinqian,et al. Transonic centrifugal compressor blade tip region vortex flow character discussion [ J ]. J. Tsinghua Univ. ( Sci. & Tech. ),2008,48 (11) : (in Chinese) [ 12 ],,,. [J ].,2008,23 (10) : ZHEN G Xinqian, ZHAN G Yangjun, GUO Gongda,et al. Design of transonic centrifugal compressor for vehicle[j ]. Journal of Aerospace Power,2008,23 (10) : (in Chinese)

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