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Figure 11.10: Static Pressure at a Point on The Stator Interface During the Final Revolution

11.4.11. Postprocessing

1.Examine the vertex-averaged static pressure at the stator during the final revolution of the rotor (as calculated from surf-mon-4.out), and plot the data.

Results → Plots → FFT...

a.Click the Load Input File... button to open the Select File dialog box.

i.Select All Files from the Files of type: drop-down list.

ii.Select surf-mon-4-rfile.out from the list of files.

iii.Click OK to close the Select File dialog box.

b.Click the Plot/Modify Input Signal... button to open the Plot/Modify Input Signal dialog box.

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Setup and Solution

i.Enable Subtract Mean Value in the Options group box.

ii.Enter flow-time as the X Axis Label.

iii.Select flow-time X Axis Variable drop-down list.

iv.Click Apply/Plot.

v.Close the Plot/Modify Input Signal dialog box.

c.Click Plot FFT in the Fourier Transform dialog box.

d.Click Axes... to open the Axes - Fourier Transform dialog box.

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e.Select exponential from the Type drop-down list, and set Precision to 1 in the Number Format group box.

f.Click Apply and close the Axes - Fourier Transform dialog box.

g.Click Plot FFT and close the Fourier Transform dialog box.

Figure 11.11: FFT of Static Pressure at the Stator

The FFT plot clearly shows that the pressure fluctuations due to interaction at the interface are dominated by the rotor and stator blade passing frequencies (which are 10 kHz and 20 kHz, respectively) and their higher harmonics.

2.Display contours of the mean static pressure on the walls of the axial compressor.

Results → Graphics → Contours → Edit

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Setup and Solution

a.Enable Filled in the Options group box.

b.Select Unsteady Statistics... and Mean Static Pressure from the Contours of drop-down lists.

c.Select wall from the Surface Types selection list.

Scroll down the Surfaces selection list to find wall.

d.Click Display and close the Contours dialog box.

e.Disable the Headlight and Lighting options.

f.Rotate the view to get the display as shown in Figure 11.12: Mean Static Pressure on the Outer Shroud of the Axial Compressor (p. 406).

Shock waves are clearly visible in the flow near the outlets of the rotor and stator, as seen in the areas of rapid pressure change on the outer shroud of the axial compressor.

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