Research Papers

Aerodynamic Design, Model Test, and CFD Analysis for a Multistage Axial Helium Compressor

[+] Author and Article Information
X. Yan

 Japan Atomic Energy Agency, Oarai-Machi, Ibaraki-ken 311-1394, Japanyan.xing@jaea.go.jp

T. Takizuka, K. Kunitomi

 Japan Atomic Energy Agency, Oarai-Machi, Ibaraki-ken 311-1394, Japan

H. Itaka

 Mitsubishi Heavy Industries, Ltd., Akunoura-Machi, Nagasaki 850-8610, Japan

K. Takahashi

 Mitsubishi Heavy Industries, Ltd., Takasago, Hyogo 676-8686, Japan

J. Turbomach 130(3), 031018 (May 06, 2008) (12 pages) doi:10.1115/1.2777190 History: Received May 10, 2007; Revised June 07, 2007; Published May 06, 2008

Results of an aerodynamic design study for the multistage axial helium compressor of a 300 MWe class nuclear gas turbine are presented. Helium compressor aerodynamics is challenged by the characteristically narrow and numerous-stage flow path, which enhances loss effects of blade surface and end wall boundary layer growth, secondary and clearance flows, and any occurrence of flow separation and stage mismatch. To meet the high efficiency and reliability requirements of the nuclear application, base line and advanced aerodynamic design techniques are incorporated with the intent to mitigate the flow path adverse working condition and losses. Design validation is carried out by test and test-calibrated 3D viscous CFD analyses of a subscale model compressor. In addition to verifying the success of the design intent, the data and computational insights of overall performance and internal flow behavior are used to establish a performance model based on Reynolds number and used for the full compressor performance prediction. The model applicable to all geometrically similar designs shows sensitive responses of helium compressor aerodynamic efficiency to Reynolds number and surface roughness. Presented in the paper is the first modern design with experimental validation for multistage axial helium compressor that concerned itself with a difficult past but which has strong current interest in countries now developing thermal and fast nuclear gas reactors.

Copyright © 2008 by American Society of Mechanical Engineers
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Figure 2

Elements of base line and advanced design approach to high performing helium compressor

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Figure 3

Improved spanwise incidence by stage matching, shown for the tenth stator only

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Figure 4

Spanwise normalized total pressure difference (ϖ) at the tenth rotor and stator blade row exits

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Figure 5

Pitchwise Mach number contour for the second rotor blade row at 80% span

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Figure 6

Helium test compressor in one-third dimensional scale

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Figure 7

Helium compressor test rig

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Figure 8

Measured and predicted high speed compressor performance maps

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Figure 9

Traversed measurements at nominal design point

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Figure 10

Multistage 3D CFD mesh for helium test compressor

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Figure 11

Measured and CFD computed spanwise distributions of axial velocity

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Figure 12

CFD results of blade suction surface streaklines (upper) and wake Mach number contours of Case 1 airfoils at nominal design point

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Figure 13

Correlation of helium compressor efficiency data with Reynolds number

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Figure 14

Blade passage Mach number distribution at 50% span at two Reynolds numbers (IGV-to-OGV multistage CFD result)

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Figure 15

Blade wake Mach contours of the third stage at Reynolds number of 1.6×105

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Figure 16

Full helium compressor high speed performance map

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Figure 1

300MWe class helium gas turbine design




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