Research Papers: Gas Turbines: Turbomachinery

Numerical Testing of a Trailing Edge Passive Morphing Control for Large Axial Fan Blades

[+] Author and Article Information
Alessio Castorrini

Mechanical and Aerospace Engineering
Sapienza University of Rome,
Via Eudossiana, 18,
Rome I-00184, Italy
e-mail: alessio.castorrini@uniroma1.it

Alessandro Corsini

Mechanical and Aerospace Engineering
Sapienza University of Rome,
Via Eudossiana, 18,
Rome I-00184, Italy
e-mail: alessandro.corsini@uniroma1.it

Anthony G. Sheard

AGS Consulting, LLC,
P.O. Box 79267,
Atlanta, GA 30357
e-mail: anthonygeoffrey.sheard@gmail.com

Franco Rispoli

Mechanical and Aerospace Engineering
Sapienza University of Rome,
Via Eudossiana, 18,
Rome I-00184, Italy
e-mail: franco.rispoli@uniroma1.it

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 5, 2017; final manuscript received July 25, 2017; published online October 25, 2017. Editor: David Wisler.

J. Eng. Gas Turbines Power 140(3), 032606 (Oct 25, 2017) (8 pages) Paper No: GTP-17-1301; doi: 10.1115/1.4037921 History: Received July 05, 2017; Revised July 25, 2017

The concept of morphing geometry to control and stabilize the flow has been proposed and applied in several aeronautic and wind turbine applications. We studied the effect of a similar passive system applied on an axial fan blade, analyzing potential benefits and disadvantages associated to the passive coupling between fluid and structure dynamics. The present work completes a previous study made at the section level, giving a view also on the three-dimensional (3D) effects. We use the numerical computation to simulate the system, which defines a complex fluid–structure interaction (FSI) problem. In order to do that, an in-house finite element (FE) solver, already used in the previous study, is applied to solve the coupled dynamics.

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Fig. 4

Radial distribution of the inlet absolute velocity for a flow rate of 51 m3/s

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Fig. 1

Fan view and computer-aided design model

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Fig. 5

CFD solution of the reference blade velocity field section at three different radius

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Fig. 6

3D view of the blade with the elastic surface at the trailing edge

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Fig. 2

Mesh: 3D view, lateral view, and section detail

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Fig. 7

3D displacement solution of the elastic surface at time 0.8 s (left) and 1.2 s (right)

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Fig. 9

Sectional contour of pressure field at time 0.8 s and 1.2 s. Detail on the right.

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Fig. 8

Main oscillation cycle in the time history of the y component of the displacement for nodes 1 (maximum displaced node) and 2 (higher section tip)

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Fig. 11

Fan characteristic curve (experiment and CFD)

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Fig. 10

Velocity field at R = 0.5 m



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