Research Papers: Gas Turbines: Turbomachinery

Optimizing the Performance of Swirl Recovery Vane on Fokker 29 Propeller Using Design of Experiments Method

[+] Author and Article Information
Yangang Wang

School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: wyg704@nwpu.edu.cn

Nanshu Chen

School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: chennanshu@mail.nwpu.edu.cn

Qingxi Li

School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China;
Faculty Aerospace Engineering,
Delft University of Technology,
Delft 2629 HS, The Netherlands
e-mail: q.li-2@tudelft.nl

Georg Eitelberg

Faculty Aerospace Engineering,
Delft University of Technology,
Delft 2629 HS, The Netherlands;
German-Dutch Wind Tunnel,
Marknesse 8316 PR, The Netherlands
e-mail: g.eitelberg@tudelft.nl

1Corresponding author.

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received October 27, 2016; final manuscript received December 9, 2017; published online May 7, 2018. Assoc. Editor: Haixin Chen.

J. Eng. Gas Turbines Power 140(8), 082605 (May 07, 2018) (7 pages) Paper No: GTP-16-1512; doi: 10.1115/1.4038913 History: Received October 27, 2016; Revised December 09, 2017

The swirl recovery vane (SRV) oriented in the slipstream of the propeller can in principle recover the swirl effect and thus would improve the propulsion performance in terms of thrust production and propulsive efficiency. The present study employs the design of experiments (DoEs) method to optimize the geometry of the specific SRV for Fokker 29 propeller for the sake of further enhancing the thrust generation and swirling recovery. First, orthogonal experiment was employed to identify the most significant factors, which directly influence the thrust production. Second, steepest ascent method was used to search the optimum range of target factors through climbing and factorial experiments. The resulting optimal solution was evaluated by the center composite experiment. Results show that the thrust generated by the SRV has been increased significantly (11.78%) after optimization at the design point, and a 0.66% increment in the total efficiency of the propeller–SRV system has been obtained. For the off-design point, an increment of the total efficiency (2.10%) can be observed at low rotating speed. Additionally, the optimized SRV is able to correct the out-flow behavior at the tip region of the vane, where the tip vortex and swirl kinetic energy loss is weaken, and the thrust distribution along the spanwise direction tends to be more uniform.

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Fig. 1

Sketch of the mesh

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Fig. 2

Outflow angles of experimental and numerical results

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Fig. 6

Relation trends of orthogonal experiment results: “1” represents the lower factor level and “2” represents the higher factor level

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Fig. 5

Optimization procedure

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Fig. 4

Schematic illustration of the computational domains

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Fig. 3

Three-dimensional rendered geometry of propeller–SRV system

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Fig. 11

Thrust coefficient distribution along the spanwise direction of original and optimized SRV

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Fig. 12

Contour of the swirl kinetic energy: (a) original design and (b) optimized design

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Fig. 7

Contour map of y and the steepest ascent direction

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Fig. 8

Contour map of response in center composite experiment design

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Fig. 9

Comparison of the original and optimized SRV

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Fig. 10

Performance comparison



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