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Research Papers

Experimental and Numerical Investigation of the Flow Field at Radial Holes in High-Speed Rotating Shafts

[+] Author and Article Information
Jan Sousek

Institut für Thermodynamik LRT-10,
Fakultät für Luft- und Raumfahrttechnik,
Universität der Bundeswehr München,
Neubiberg 85577, Germany
e-mail: sousek.jan@seznam.cz

Daniel Riedmüller

Institut für Thermodynamik LRT-10,
Fakultät für Luft- und Raumfahrttechnik,
Universität der Bundeswehr München,
Neubiberg 85577, Germany
e-mail: daniel.riedmueller@unibw.de

Michael Pfitzner

Institut für Thermodynamik LRT-10,
Fakultät für Luft- und Raumfahrttechnik,
Universität der Bundeswehr München,
Neubiberg 85577, Germany
e-mail: michael.pfitzner@unibw.de

1Address all correspondence to this author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received October 18, 2013; final manuscript received November 5, 2013; published online January 31, 2014. Editor: Ronald Bunker.

J. Turbomach 136(8), 081009 (Jan 31, 2014) (13 pages) Paper No: TURBO-13-1238; doi: 10.1115/1.4026121 History: Received October 18, 2013; Revised November 05, 2013

Rotating and stationary orifices are used within the secondary air system to transport sealing/cooling air to its consumers. This paper reports on measurements of the discharge coefficient of rotating radial holes since their aerodynamical behavior is different from that of axial or stationary holes due to the presence of centrifugal and Coriolis forces. A test rig containing two independently rotating shafts was designed in order to investigate the flow phenomena and the discharge behavior of these orifices. The required air mass flow is delivered by a screw compressor and can be independently regulated to supply the inner and outer annular passages of the test rig. It allows for measurements of the discharge coefficient with cross flow and co- and counter-rotating shafts with centrifugal and centripetal flow through the rotating holes. On the outer shaft, absolute and differential pressures and temperatures in the rotating frame of reference are measured via a telemetry system. Measurements of the discharge coefficient for sharp-edged and rounded shaft inserts at a variety of different flow conditions and with swirl added to the air upstream of the orifice are presented. Furthermore, experiments were conducted to quantify the influence of the inner shaft (nonrotating and rotating) on the discharge behavior of orifices in the outer shaft. To complement the data acquired from the experiments and to obtain a better understanding of the flow field near the rotating holes numerical flow simulations were also performed.

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References

Figures

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Fig. 1

Schematic line drawing of air supply

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Fig. 2

Details of experimental rig (dimensions are in mm)

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Fig. 8

Comparison of the CFD and experimental discharge coefficients (L/d = 1.2; swirl = 0 deg; r/d = 0.2; Π = 1.05–1.5; and Max = 0.1)

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Fig. 9

Comparison of the CFD grids in the sectional view of the orifice

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Fig. 7

Boundary conditions for the annular section

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Fig. 6

Velocity angle at the profile stage for the swirl generator 25 deg

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Fig. 5

Boundary conditions for the preswirl generator

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Fig. 4

Computational domain

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Fig. 10

Comparison of the experiment and the CFD (L/d = 1.2; r/d = 0; Π =1.05–1.5; and Max = 0.1)

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Fig. 11

Comparison of the experiment and the CFD (L/d = 0.6; r/d = 0; Π = 1.05–1.5; and Max = 0.1)

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Fig. 20

Flow vectors for different inlet edge radii at the constant velocity ratio v1,rel/Cid,rel = 0.55 (L/d = 1.2; Π = 1.25; and Max = 0.1)

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Fig. 24

Flow vectors in the orifice for the swirl generator with 25 deg (L/d = 1.2; r/d = 0; Π = 1.25; and Max = 0.1)

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Fig. 21

Discharge coefficient as a function of the total pressure ratio for different Mach numbers Max (L/d = 1.2 and r/d = 0.2)

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Fig. 22

Discharge coefficient for swirl = 25 deg (L/d = 1.2; r/d = 0; and Max = 0.1 – 0.2)

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Fig. 23

Qualitative plot of the incident flow at the orifice in the xz-plane (L/d = 1.2; r/d = 0; Π = 1.25; and Max = 0.1)

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Fig. 12

Comparison of the experiment and the CFD (L/d = 1.2; r/d = 0.2; Π = 1.05–1.5; and Max = 0.1-0.2)

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Fig. 13

Comparison of the experiment and the CFD (L/d = 0.6; r/d = 0.2; Π = 1.05—1.5; and Max = 0.1–0.2)

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Fig. 14

Flow vectors for different velocity ratios (L/d = 1.2; r/d = 0; Π = 1.25; and Max = 0)

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Fig. 15

Contour plot of the velocity in the hole outlet plane for different velocity ratios (L/d = 1.2; r/d = 0; Π = 1.25; and Max = 0)

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Fig. 16

Flow vectors for the constant velocity ratio v1,rel/Cid,rel = 0.19 (L/d = 1.2; r/d = 0; and Π = 1.25)

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Fig. 17

Contour plot of the velocity in the hole outlet for the constant velocity ratio v1,rel/Cid,rel = 0.19 (L/d = 1.2; r/d = 0; and Π = 1.25)

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Fig. 18

Flow vector of cases with different pressure ratios for v1,rel/Cid,rel = 0.3 (L/d = 1.2; r/d = 0; and Max = 0.1)

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Fig. 19

Discharge coefficient as a function of the total pressure ratio for different Mach numbers Max (L/d = 1.2 and r/d = 0)

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Fig. 25

Computational and experimental results for swirl = 25 deg (L/d = 1.2; r/d = 0; and Max = 0.1)

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Fig. 26

Discharge coefficient for swirl = 25 deg against it (L/d = 1.2; r/d = 0; and Max = 0.1 – 0.2)

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Fig. 27

Discharge coefficient for swirl = 45 deg (L/d = 1.2; r/d = 0; and Max = 0.1 – 0.2)

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Fig. 28

Test rig without inner shaft

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Fig. 29

Influence of the inner shaft on the discharge behavior

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Fig. 30

Influence of the rotating inner shaft on the discharge behavior (L/d = 1.2; r/d = 0; and Max = 0.2)

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