Heat transfer augmentation in a rectangular channel with slit rib-turbulators on two opposite walls

Journal Article · Tue Jul 01 04:00:00 EDT 1997 · Journal of Turbomachinery

DOI:https://doi.org/10.1115/1.2841167· OSTI ID:516734

Hwang, J J ^[1]; Liou, T M ^[2]

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1. Chung-Hua Polytechnic Inst., Hsinchu (Taiwan, Province of China). Dept. of Mechanical Engineering
2. National Tsing-Hua Univ., Hsinchu (Taiwan, Province of China). Dept. of Power Mechanical Engineering

The effect of slit ribs on heat transfer and friction in a rectangular channel is investigated experimentally. The slit ribs are arranged in-line on two opposite walls of the channel. Three rib open-area ratios ({beta} = 24, 37, and 46%), three rib pitch-to-height ratios (Pi/H = 10, 20, and 30), and two rib height-to-channel hydraulic diameter ratios (H/De = 0.081, and 0.162) are examined. The Reynolds number ranges from 10,000 to 50,000. Laser holographic interferometry is employed to measure the local heat transfer coefficients of the ribbed wall quantitatively, and observe the flow over the ribbed wall qualitatively. The results show that the slit rib has an advantage of avoiding hot spots. In addition, the heat transfer performance of the slit-ribbed channel is much better than that of the solid-ribbed channel. Semi-empirical correlations for friction and heat transfer are developed to account for rib spacings and open-area ratios. These correlations may be used in the design of turbine blade cooling passages.

• Sponsoring Organization: National Science Council, Taipei (Taiwan, Province of China)
• OSTI ID: 516734
• Report Number(s): CONF-950629--
• Journal Information: Journal of Turbomachinery, Journal Name: Journal of Turbomachinery Journal Issue: 3 Vol. 119; ISSN JOTUEI; ISSN 0889-504X
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
AUGMENTATION
COOLING SYSTEMS
DUCTS
FINS
GAS TURBINE ENGINES
HEAT TRANSFER
TURBINE BLADES