Figure 1.
Investigation procedure.
Figure 1.
Investigation procedure.
Figure 2.
Schematic diagram of compressor aerodynamic noise test device. 1. Compressor inlet flowmeter. 2. Compressor inlet pressure sensor. 3. Compressor inlet temperature sensor. 4. Speed sensor. 5. Compressor. 6. Compressor outlet temperature sensor. 7. Automatic circulating valve. 8. Electric exhaust control valve. 9. Electric trimming valve. 10. Turbine. 11. Burner. 12. Turbine inlet flowmeter. 13. Turbine inlet control valve. 14. Air source vent valve. 15. Filter. 16. Air source. 17. Vibration sensors. 18. Microphone. 19. Signal acquisition port. 20. Computer.
Figure 2.
Schematic diagram of compressor aerodynamic noise test device. 1. Compressor inlet flowmeter. 2. Compressor inlet pressure sensor. 3. Compressor inlet temperature sensor. 4. Speed sensor. 5. Compressor. 6. Compressor outlet temperature sensor. 7. Automatic circulating valve. 8. Electric exhaust control valve. 9. Electric trimming valve. 10. Turbine. 11. Burner. 12. Turbine inlet flowmeter. 13. Turbine inlet control valve. 14. Air source vent valve. 15. Filter. 16. Air source. 17. Vibration sensors. 18. Microphone. 19. Signal acquisition port. 20. Computer.
Figure 3.
Aerodynamic noise test condition points.
Figure 3.
Aerodynamic noise test condition points.
Figure 4.
Aerodynamic noise simulation points.
Figure 4.
Aerodynamic noise simulation points.
Figure 5.
Compressor fluid domain and monitoring points distribution. (a) Compressor model (b) Rotor region (c) Diffuser and volute regions.
Figure 5.
Compressor fluid domain and monitoring points distribution. (a) Compressor model (b) Rotor region (c) Diffuser and volute regions.
Figure 6.
Extrapolation results in pressure ratio and efficiency to several elements at a speed of 60,000 r/min.
Figure 6.
Extrapolation results in pressure ratio and efficiency to several elements at a speed of 60,000 r/min.
Figure 7.
Compressor model test verification. (a) Pressure ratio (b) Efficiency.
Figure 7.
Compressor model test verification. (a) Pressure ratio (b) Efficiency.
Figure 8.
Aerodynamic noise emissions composition.
Figure 8.
Aerodynamic noise emissions composition.
Figure 9.
Aerodynamic noise emissions spectral characteristics of the compressor under different operating conditions. (a) 60,000 r/min (b) 90,000 r/min (c) 110,000 r/min.
Figure 9.
Aerodynamic noise emissions spectral characteristics of the compressor under different operating conditions. (a) 60,000 r/min (b) 90,000 r/min (c) 110,000 r/min.
Figure 10.
Aerodynamic noise emissions contour clouds of compressors under different operating conditions. (a) Case 1 (b) Case 2 (c) Case 3.
Figure 10.
Aerodynamic noise emissions contour clouds of compressors under different operating conditions. (a) Case 1 (b) Case 2 (c) Case 3.
Figure 11.
Total sound pressure level and blade passing frequency noise of the compressor under full operating range. (a) Total sound pressure level (b) BPF nose.
Figure 11.
Total sound pressure level and blade passing frequency noise of the compressor under full operating range. (a) Total sound pressure level (b) BPF nose.
Figure 12.
Blade passing frequency noise proportion.
Figure 12.
Blade passing frequency noise proportion.
Figure 13.
Transient acoustic-vibration characteristics of the compressor under high-efficiency regions. (a) 60,000 r/min (b) 90,000 r/min (c) 110,000 r/min.
Figure 13.
Transient acoustic-vibration characteristics of the compressor under high-efficiency regions. (a) 60,000 r/min (b) 90,000 r/min (c) 110,000 r/min.
Figure 14.
Fluctuation pressure analysis process of the compressor.
Figure 14.
Fluctuation pressure analysis process of the compressor.
Figure 15.
Time domain fluctuation pressure distributions of the compressor inlet region under different speeds. (a) 60,000 r/min (b) 90,000 r/min (c) 110,000 r/min.
Figure 15.
Time domain fluctuation pressure distributions of the compressor inlet region under different speeds. (a) 60,000 r/min (b) 90,000 r/min (c) 110,000 r/min.
Figure 16.
Frequency domain fluctuation pressure distributions of the compressor inlet region under different speeds. (a) 60,000 r/min (b) 90,000 r/min (c) 110,000 r/min.
Figure 16.
Frequency domain fluctuation pressure distributions of the compressor inlet region under different speeds. (a) 60,000 r/min (b) 90,000 r/min (c) 110,000 r/min.
Figure 17.
Time domain fluctuation pressure distributions of the compressor rotor region under different speeds. (a) 60,000 r/min (b) 90,000 r/min (c) 110,000 r/min.
Figure 17.
Time domain fluctuation pressure distributions of the compressor rotor region under different speeds. (a) 60,000 r/min (b) 90,000 r/min (c) 110,000 r/min.
Figure 18.
Frequency domain fluctuation pressure distributions of the compressor rotor region under different speeds. (a) 60,000 r/min (b) 90,000 r/min (c) 110,000 r/min.
Figure 18.
Frequency domain fluctuation pressure distributions of the compressor rotor region under different speeds. (a) 60,000 r/min (b) 90,000 r/min (c) 110,000 r/min.
Figure 19.
Pressure distribution in the compressor rotor region at 60,000 r/min of the high-efficiency region. (a) F1 (b) F2.
Figure 19.
Pressure distribution in the compressor rotor region at 60,000 r/min of the high-efficiency region. (a) F1 (b) F2.
Figure 20.
Time domain fluctuation pressure distributions of the compressor diffuser region under different speeds. (a) 60,000 r/min (b) 90,000 r/min (c) 110,000 r/min.
Figure 20.
Time domain fluctuation pressure distributions of the compressor diffuser region under different speeds. (a) 60,000 r/min (b) 90,000 r/min (c) 110,000 r/min.
Figure 21.
Frequency domain fluctuation pressure distributions of the compressor diffuser region under different speeds. (a) 60,000 r/min (b) 90,000 r/min (c) 110,000 r/min.
Figure 21.
Frequency domain fluctuation pressure distributions of the compressor diffuser region under different speeds. (a) 60,000 r/min (b) 90,000 r/min (c) 110,000 r/min.
Figure 22.
Time domain fluctuation pressure distributions of the compressor volute region under different speeds. (a) 60,000 r/min (b) 90,000 r/min (c) 110,000 r/min.
Figure 22.
Time domain fluctuation pressure distributions of the compressor volute region under different speeds. (a) 60,000 r/min (b) 90,000 r/min (c) 110,000 r/min.
Figure 23.
Frequency domain fluctuation pressure distributions of the compressor volute region under different speeds. (a) 60,000 r/min (b) 90,000 r/min (c) 110,000 r/min.
Figure 23.
Frequency domain fluctuation pressure distributions of the compressor volute region under different speeds. (a) 60,000 r/min (b) 90,000 r/min (c) 110,000 r/min.
Figure 24.
Static entropy and TKE distribution of the compressor at 60,000 r/min of the high-efficiency region. (a) Static entropy (b) TKE.
Figure 24.
Static entropy and TKE distribution of the compressor at 60,000 r/min of the high-efficiency region. (a) Static entropy (b) TKE.
Figure 25.
Blade-to-blade view of Static entropy and TKE distribution for the compressor at 60,000 r/min of the high-efficiency region. (a) Static entropy (b) TKE.
Figure 25.
Blade-to-blade view of Static entropy and TKE distribution for the compressor at 60,000 r/min of the high-efficiency region. (a) Static entropy (b) TKE.
Table 1.
Measuring ranges, accuracies, and uncertainties of instruments.
Table 1.
Measuring ranges, accuracies, and uncertainties of instruments.
Instruments | Parameters | Measuring Range | Accuracy | Uncertainty |
---|
Tachometer | Speed | 0~400,000 r/min | 0.1 r/min | 0.01 r/min |
Microphone | Noise | 15~165 dB | 0.1 dB | ±0.02 dB |
Vibration sensor | Vibration | ±490 m/s2 pk | 1% | ±0.2 m/s2 |
Temperature sensor | Compressor inlet and outlet temperature | −200~400 °C | 0.25 °C | ±0.1 °C |
Pressure sensor | Compressor inlet pressure | −175~35,000 Pa, −40~85 °C | 0.05% | ±0.01% |
Pressure sensor | Compressor outlet pressure | 0~700,000 Pa, −40~85 °C | 0.05% | ±0.01% |
Temperature sensor | Turbine inlet and outlet temperature | −200~1372 °C | 0.4% | ±0.1 °C |
Pressure sensor | Turbine inlet pressure | 0~700,000 Pa, −40~85 °C | 0.05% | ±0.01% |
Pressure sensor | Turbine outlet pressure | −175~35,000 Pa, −40~85 °C | 0.05% | ±0.01% |
Table 2.
Compressor parameters.
Table 2.
Compressor parameters.
Item | Value |
---|
Turbocharger compatibility | Heavy-duty diesel engine |
Outlet diameter of impeller (mm) | 94.4 |
Inlet diameter of impeller (mm) | 66.46 |
Main blade number | 7 |
Splitter blade number | 7 |
Diffuser height (mm) | 4.77 |
Design pressure ratio | 4.5 |
Rated speed (r/min) | 117,000 |
Outlet diameter of the diffuser (mm) | 166.15 |
Inlet diameter of the diffuser (mm) | 90 |
Type of cooling | Oil cooling |
Table 3.
Comparison of the various numerical parameters critical to modeling compressor aerodynamics and noise generation in this survey with other literature surveys.
Table 3.
Comparison of the various numerical parameters critical to modeling compressor aerodynamics and noise generation in this survey with other literature surveys.
Study | Tip Diameter (mm) | Elements (Million) | Wheel Rotation (-) | Turbulence Method (-) | Boundary Conditions | Time Steps (°) |
---|
Inlet | Outlet |
---|
Sundström et al. [24] | 88 | 9 | Sliding | LES | Pressure | Mass flow | 1 |
Fontenasi et al. [18] | - | 9.6 | Sliding | DES | Mass flow | Pressure | 0.5 |
Broatch et al. [27] | 48.6 | 9.6 | Sliding | DES | Mass flow | Pressure | 1 |
Karim et al. [9] | - | - | Sliding | LES | Pressure | Mass flow | - |
Semlitsch et al. [32] | 88 | 6 | Sliding | LES | Mass flow | Pressure | 5 |
Jyothishkumar et al. [26] | 88 | 6 | Sliding | LES | Mass flow | Pressure | 5 |
Tomita et al. [29] | 50 | 3.2 | - | URANS (k-ε) | - | - | 3.6/7.2 |
Guo et al. [28] | 182.8 | 2.5 | Sliding | URANS (k-ε) | Pressure | Mass flow | 3 |
Dehner et al. [21] | - | 5.5 | Static | DES | Pressure | Mass flow | - |
Galindo et al. [22] | - | 10 | Sliding | DES | Mass flow | Pressure | 4 |
Galindo et al. [23] | - | 9.5 | Sliding | SST/DES | Mass flow | Pressure | 1 |
Fardafshar et al. [33] | - | - | Static | SAS-SST | - | - | - |
This investigation | - | 4.9 | Sliding | SST | Pressure | Mass flow | 4 |
Table 4.
Equations for Richardson extrapolation method.
Table 4.
Equations for Richardson extrapolation method.
Factor | Equation |
---|
Representative mesh size h | |
Grid refinement factor r | |
Apparent order | |
Approximate relative error | |
Extrapolated relative error | |
Grid convergence index | |
Table 5.
Discretization errors of three meshes.
Table 5.
Discretization errors of three meshes.
| | |
---|
N1, N2, N3 | 6,730,132, 4,932,456, 3,102,894 | 6,730,132, 4,932,456, 3,102,894 |
r31 | 2.4192 | 2.4192 |
r21 | 1.8292 | 1.8292 |
r32 | 1.3226 | 1.3226 |
| 1.5864 | 0.8146 |
| 1.5841 | 0.8120 |
| 1.5736 | 0.8017 |
| 0.7932 | 2.2437 |
| 1.5901 | 0.8155 |
| 0.145% | 0.3192% |
| 0.2327% | 0.1101% |
| 0.295% | 0.1387% |
Table 6.
Comparison of the investigation and other literature survey.
Table 6.
Comparison of the investigation and other literature survey.
Study | Research Object | Research Methods | Main Conclusions |
---|
Li et al. [12] | Turbocharger for small vehicles | Experiment | The compressor was the main noise source of the turbocharger. |
Raitor et al. [13] | Two centrifugal compressors of SRV2 and SRV4 | Experiment | - (1)
At the design speed, blade tone and buzz-saw noise were the main contributors. - (2)
On the inlet, rotor-alone noise was the main source.
|
Figurella et al. [14] | An automotive centrifugal compressor | Experiment | Near-choke condition, discrete tones, including rotor-order frequency and its harmonics (blade-pass), were observed. |
Zhang et al. [15] | Single-stage compressor with low speed and high load | Experiment | The sound pressure level of the compressor was lowest at a relatively small tip clearance rather than zero. |
Galindo et al. [16] | A small automotive turbocharger compressor | Experiment | The effects of several inlet geometries on compressor performance were investigated. |
Dehner et al. [21] | A turbocharger centrifugal compressor from a spark-ignition internal combustion engine | Numerical simulation, experiments and modal decomposition | - (1)
Revealed the presence of rotating instabilities that may interact with the rotor blades to generate noise. - (2)
The whooshing noise primarily propagated along the duct as acoustic azimuthal modes.
|
Galindo et al. [22] | An automotive centrifugal compressor | Numerical simulation | The use of a convergent-divergent nozzle could strongly reduce the intake orifice noise. |
Galindo et al. [23] | A 49 mm exducer diameter centrifugal compressor | Numerical simulation | In near-surge conditions, there were no significant changes in the compressor acoustic signature when varying the tip clearance. |
Sundström et al. [24] | An automotive centrifugal compressor | Numerical simulation | For the near-surge condition, an amplified broadband feature at two times the frequency of the rotating order of the shaft (possible whoosh noise) was captured. In addition, an amplified feature of around 50% of the rotating order was captured. |
Jyothishkumar et al. [26] | A turbocharger centrifugal compressor from a heavy truck engine | Numerical simulation | There existed a flow-acoustics coupling at near-surge operating conditions. |
Broatch et al. [27] | A turbocharger centrifugal compressor from a diesel engine | In-duct experimental measurements and numerical simulation | - (1)
A suitable comparison methodology was developed, relying on pressure decomposition. - (2)
Whoosh, noise at the outlet duct was detected in experimental and numerical spectra.
|
Guo et al. [28] | A turbocharger centrifugal compressor | Numerical simulation | A distinct stall frequency at the given compressor speed. |
This investigation | A turbocharger centrifugal compressor from a heavy-duty diesel engine | Based on radiated noise experimental measurements and numerical simulation | - (1)
The aerodynamic noise characteristics of the centrifugal compressor in the full operating range based on the radiation noise experimental measurements were given. - (2)
For the centrifugal compressor from a heavy-duty diesel engine, the blade passing frequency and its harmonic frequency noise were mainly caused by the unsteady fluctuation pressure. - (3)
The impeller blades interfere with the incoming airflow, and the dynamic-static interference between the impeller and the diffuser significantly contributed to the BPF and its harmonic frequency noise.
|