Title

Fan Report

Date

2009/05/24 22:05:17

Contents

1. File Report
    Table 1  File Information for CFX
2. Mesh Report
    Table 2  Mesh Information for CFX
    Table 3  Mesh Statistics for CFX
3. Physics Report
    Table 4  Domain Physics for CFX
    Table 5  Boundary Physics for CFX
4. Tabulated Results
    Table 6  Performance Results
    Table 7  Summary Data
5. Blade Loading Charts
    Chart 1  Blade Loading at 20% Span
    Chart 2  Blade Loading at 50% Span
    Chart 3  Blade Loading at 80% Span
6. Streamwise Charts
    Chart 4  Streamwise Plot of Pt and Ps
    Chart 5  Streamwise Plot of C
    Chart 6  Streamwise Plot of W
    Chart 7  Streamwise Plot of Alpha and Beta
7. Spanwise Charts
    Chart 8  Spanwise Plot of Alpha and Beta at LE
    Chart 9  Spanwise Plot of Alpha and Beta at TE
8. Blade Geometry Plots
    Figure 1  Isometric 3D View of the Blade, Hub and Shroud
    Figure 2  Meridional View of the Blade, Hub and Shroud
9. Blade Mesh Plot
    Figure 3  Mesh Elements at 50% Span
10. Blade to Blade Plots
    Figure 4  Contour of Pt at 50% Span
    Figure 5  Contour of Ptr at 50% Span
    Figure 6  Contour of Ps at 50% Span
    Figure 7  Contour of W at 50% Span
    Figure 8  Velocity Vectors at 20% Span
    Figure 9  Velocity Vectors at 50% Span
    Figure 10  Velocity Vectors at 80% Span
11. Meridional Plots
    Figure 11  Contour of Mass Averaged Pt on Meridional Surface
    Figure 12  Contour of Mass Averaged Ptr on Meridional Surface
    Figure 13  Contour of Mass Averaged W on Meridional Surface
    Figure 14  Vector of Area Averaged Cm on Meridional Surface
12. Circumferential Plots
    Figure 15  Contour of Pt at Blade LE
    Figure 16  Contour of Ptr at Blade LE
    Figure 17  Contour of W at Blade LE
    Figure 18  Contour of Pt at Blade TE
    Figure 19  Contour of Ptr at Blade TE
    Figure 20  Contour of W at Blade TE
13. Streamline Plot
    Figure 21  Velocity Streamlines at Blade TE
14. Noise Analysis
  14.1. Noise input data
      Table 8  Noise input data
  14.2. Sound Pressure Levels
      Table 9  Sound Pressure Levels
      Chart 10  Sound Pressure Levels
  14.3. Sound Power Levels
      Table 10  Sound Power Levels
      Chart 11  Sound Power Levels
  14.4. Directivity
      Chart 12  Directivity
  14.5. Overall Noise
      Table 11  Overall Noise
  14.6. Broadband Noise
      Table 12  Proudman Sound Power
      Figure 22  Isosurface at 95% of Proudman Sound Power
  14.7. Noise Sources
      Table 13  Summary of noise sources at the blade and at the final timestep
      Figure 23  Monopole Source
      Figure 24  Dipole Source
      Table 14  Summary of quadrupole sources at the final timestep
      Figure 25  Isosurface at 80% of Quadrupole Source Strength

1. File Report

2. Mesh Report

3. Physics Report

4. Tabulated Results

The first table below gives a summary of the performance results for the fan. The second table lists the mass or area averaged solution variables and derived quantities computed at the inlet, leading edge (LE Cut), trailing edge (TE Cut) and outlet locations. The flow angles Alpha and Beta are relative to the meridional plane; a positive angle implies that the tangential velocity is the same direction as the machine rotation.

5. Blade Loading Charts

Chart 1.  Blade Loading at 20% Span

Chart 2.  Blade Loading at 50% Span

Chart 3.  Blade Loading at 80% Span

6. Streamwise Charts

Chart 4.  Streamwise Plot of Pt and Ps

Chart 5.  Streamwise Plot of C

Chart 6.  Streamwise Plot of W

Chart 7.  Streamwise Plot of Alpha and Beta

7. Spanwise Charts

Chart 8.  Spanwise Plot of Alpha and Beta at LE

Chart 9.  Spanwise Plot of Alpha and Beta at TE

8. Blade Geometry Plots

Figure 1.  Isometric 3D View of the Blade, Hub and Shroud

Figure 2.  Meridional View of the Blade, Hub and Shroud

9. Blade Mesh Plot

Figure 3.  Mesh Elements at 50% Span

10. Blade to Blade Plots

Figure 4.  Contour of Pt at 50% Span

Figure 5.  Contour of Ptr at 50% Span

Figure 6.  Contour of Ps at 50% Span

Figure 7.  Contour of W at 50% Span

Figure 8.  Velocity Vectors at 20% Span

Figure 9.  Velocity Vectors at 50% Span

Figure 10.  Velocity Vectors at 80% Span

11. Meridional Plots

Figure 11.  Contour of Mass Averaged Pt on Meridional Surface

Figure 12.  Contour of Mass Averaged Ptr on Meridional Surface

Figure 13.  Contour of Mass Averaged W on Meridional Surface

Figure 14.  Vector of Area Averaged Cm on Meridional Surface

12. Circumferential Plots

Figure 15.  Contour of Pt at Blade LE

Figure 16.  Contour of Ptr at Blade LE

Figure 17.  Contour of W at Blade LE

Figure 18.  Contour of Pt at Blade TE

Figure 19.  Contour of Ptr at Blade TE

Figure 20.  Contour of W at Blade TE

13. Streamline Plot

Figure 21.  Velocity Streamlines at Blade TE

14. Noise Analysis

This analysis has been supplied to assist in the evaluation of tonal noise levels generated by low speed fans (Mach Number less than 0.4). The equations were obtained from available literature, however some equations may have alternate definitions. It is your responsibility to verify the accuracy of these definitions.

14.1. Noise input data

This data is based on the input to the Fan Noise macro. To change the input values, select Turbo tab > Fan Noise macro, change parameters and select Calculate to re-generate the report.

14.2. Sound Pressure Levels

Chart 10.  Sound Pressure Levels

14.3. Sound Power Levels

Chart 11.  Sound Power Levels

14.4. Directivity

Chart 12.  Directivity

14.5. Overall Noise

14.6. Broadband Noise

Broadband noise model is derived from Proudman's formula (see expression Proudman Sound Power Exp), which predicts overall sound power. Associated variable (Proudman Sound Power) is evaluated on the entire domain, allowing visualization of isosurfaces that can be used to locate the portion of the flow that is responsible for noise generation.

Note that this model predicts overall noise levels, not at a specific observer location.

Figure 22.  Isosurface at 95% of Proudman Sound Power

14.7. Noise Sources

This section reports on Monopole, Dipole and Quadrupole noise sources, derived from Ffowcs Williams and Hawkings (FW-H) equations. These sources can be compared with each other and with the broadband noise to determine the dominant noise source in the design.

Monopole source is related to the movement of the source surface. It defines the volume displacement of the source. It is usually called self noise.

Dipole source describes the interaction between the fluid and the surface of the source. It defines the loading fluctuations exerted on the surface.

Quadrupole source is related to the turbulence fluctuation levels of the fluid. It is also called self noise.

Figure 23.  Monopole Source

Figure 24.  Dipole Source

Figure 25.  Isosurface at 80% of Quadrupole Source Strength