Research Papers

Modeling of Laminar-Turbulent Transition in Boundary Layers and Rough Turbine Blades

[+] Author and Article Information
Liang Wei, Jacob George

MetroLaser, Inc.,
Laguna Hills, CA 92653

Xuan Ge

Department of Mathematics,
Florida State University,
Tallahassee, FL 32306

Paul Durbin

Department of Aerospace Engineering,
Iowa State University,
Ames, IA 50011
e-mail: durbin@iastate.edu

1Corresponding author.

Manuscript received October 25, 2016; final manuscript received August 8, 2017; published online September 6, 2017. Assoc. Editor: Cengiz Camci.

J. Turbomach 139(11), 111009 (Sep 06, 2017) (8 pages) Paper No: TURBO-16-1283; doi: 10.1115/1.4037670 History: Received October 25, 2016; Revised August 08, 2017

A local, intermittency-function-based transition model was developed for the prediction of laminar-turbulent transitional flows with freestream turbulence intensity Tu at low (Tu < 1%), moderate (1% < Tu < 3%), and high Tu > 3% levels, and roughness effects in a broad range of industrial applications such as turbine and helicopter rotor blades, and in nature. There are many mechanisms (natural or bypass) that lead to transition. Surface roughness due to harsh working conditions could have great influence on transition. Accurately predicting both the onset location and length of transition has been persistently difficult. The current model is coupled with the k–ω Reynolds-averaged Navier–Stokes (RANS) model, that can be used for general computational fluid dynamics (CFD) purpose. It was validated on the ERCOFTAC experimental zero-pressure-gradient smooth flat plate boundary layer with both low and high leading-edge freestream turbulence intensities. Skin friction profiles agree well with the experimental data. The model was then tested on ERCOFTAC experimental flat plate boundary layer with favorable/adverse pressure gradients cases, periodic wakes, and flows over Stripf's turbine blades with roughness from hydraulically smooth to fully rough. The predicted skin friction and heat transfer properties by the current model agree well with the published experimental and numerical data.

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Grahic Jump Location
Fig. 1

Turbulence density decay for T3A-

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Fig. 2

Skin friction coefficient for T3A-

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Fig. 3

Skin friction coefficient for T3A

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Fig. 4

Skin friction coefficient for T3B

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Fig. 5

Computational domain

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Fig. 6

Skin friction profiles for T3C1–T3C5

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Fig. 7

Wake characteristics at inlet x = −0.05 (a, c), and 0.1 (b, d), where the deficit velocity Udef = 0.48 and 0.14, and the wake half width b = 0.03 and 0.1, respectively. Dashed lines represent the data from Wu and Durbin [52]: (a) uwake at x = −0.05; (b) uwake at x = 0.1; (c) kwake at x = −0.05; (d) kwake at x = 0.1.

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Fig. 8

x–t diagram of phase-averaged skin-friction coefficient: (a) current model and (b) DNS of Ref. [52]

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Fig. 9

Time-averaged skin friction coefficient

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Fig. 10

LPT computational domain

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Fig. 11

Nu for the Stripf's [47] LPT blade with different roughness (r, μm)

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Fig. 12

HPT computational domain

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Fig. 13

h for the Stripf's [47] HPT blade with different roughness (r, μm)




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