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research-article

An Experimental Verification of a New Design for Cantilevered Stators With Large Hub Clearances

[+] Author and Article Information
Martin Lange

e-mail: martin.lange@tu-dresden.de

Konrad Vogeler

e-mail: konrad.vogeler@tu-dresden.de
Technische Universität Dresden,
Institute of Fluid Mechanics,
D-01062 Dresden, Germany

Ronald Mailach

Ruhr-Universität Bochum,
Institute of Power Engineering,
D-44780 Bochum, Germany
e-mail: ronald.mailach@rub.de

Sergio Elorza Gomez

MTU Aero Engines,
D-80995 Munich, Germany
e-mail: sergio.elorza-gomez@mtu.de

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received August 7, 2012; final manuscript received August 14, 2012; published online June 5, 2013. Assoc. Editor: David Wisler.

J. Turbomach 135(4), 041022 (Jun 05, 2013) (9 pages) Paper No: TURBO-12-1168; doi: 10.1115/1.4007612 History: Received August 07, 2012; Revised August 14, 2012

Proportionally large relative radial clearances can be found within the rear stages of multistage axial compressors of gas turbines and aero engines, with significant impact on their efficiency. A new three-dimensional design for cantilevered stators in axial compressors is presented, with the aim of improving the overall efficiency and losses of rear stage vanes with large relative hub clearances. The new vane design comprises an unconventional dihedral, with special consideration to reduce the losses caused by the hub clearance vortex. The design was tested in a 4-stage low speed axial research compressor under rear stage conditions. The results are compared to the nominal design to validate the reduction of hub clearance losses and blockage. For both designs, the hub clearances over the third and fourth stator were varied from 1.5% up to 6.0% of span. Overall performance data and flow field traverses upstream and downstream of stator 3 and rotor 4 will be presented in this article in comparison with 3D CFD results.

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References

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Figures

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Fig. 1

Dresden LSRC cross section and parameters of reference design

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Fig. 2

Compressor map for hub clearance variation over stator 3 and 4 (reference design - hollow symbols / new design - filled symbols) at design speed

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Fig. 3

Nondimensional total pressure cp downstream of stator 3 at design point (ξ=1.00)

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Fig. 4

Nondimensional total pressure cp downstream of stator 3 near stall (ξ=0.85)

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Fig. 5

Total pressure loss ζ over stator 3 (reference design - hollow symbols / new design - filled symbols)

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Fig. 6

Relative total pressure loss ζ over rotor 4 (reference design - hollow symbols / new design - filled symbols)

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Fig. 7

Nondimensional total pressure cp downstream of stator 3 for CFD of design point (ξ=1.00)

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Fig. 8

Blade pressure distribution of stator 3 for CFD (no symbols) and experiment (symbols) of design point (ξ=1.00)

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Fig. 9

Static pressure difference over stator 3 for CFD of design point (ξ=1.00) close to hub clearance r*=8.3%

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Fig. 10

Axial velocity component cax at the hub clearance height of stator 3 for CFD of design point (ξ=1.00)

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Fig. 11

Total pressure loss ζ over stator 3 for CFD of design point (reference design - dashed line / new design - solid line)

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Fig. 12

Relative total pressure loss ζ over rotor 4 for CFD of design point (reference design - dashed line / new design - solid line)

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