Measurements of heat transfer coefficients and friction factors in passages rib-roughened on all walls

Journal Article · Wed Jul 01 04:00:00 EDT 1998 · Journal of Turbomachinery

DOI:https://doi.org/10.1115/1.2841754· OSTI ID:290034

Taslim, M E; Li, T ^[1]; Spring, S D ^[2]

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1. Northeastern Univ., Boston, MA (United States). Dept. of Mechanical Engineering
2. GE Aircraft Engines, Lynn, MA (United States)

A liquid crystal technique was used to measure heat transfer coefficients in twelve test sections with square and trapezoidal cross-sectional areas representing blade midchord cooling cavities in a modern gas turbine. Full-length ribs were configured on suction side as well as pressure side walls while half-length ribs were mounted on partition walls between adjacent cooling cavities. Ribs were in staggered arrangements with a nominal blockage ratio of 22% and an angle of attack to the mainstream flow, {alpha}, of 90 deg. Heat transfer measurements were performed on the roughened walls with full-length as well as half-length ribs. Nusselt numbers, friction factors, and thermal performances of all geometries are compared. The most important conclusion of this study is that the roughening of the partition walls enhances the heat transfer coefficients on those walls but, more importantly, enhances heat transfer coefficients on the primary walls considerably.

• Sponsoring Organization: USDOE
• OSTI ID: 290034
• Report Number(s): CONF-960608--
• Journal Information: Journal of Turbomachinery, Journal Name: Journal of Turbomachinery Journal Issue: 3 Vol. 120; ISSN JOTUEI; ISSN 0889-504X
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
42 ENGINEERING
AUGMENTATION
DUCTS
GAS TURBINE ENGINES
HEAT EXCHANGERS
HEAT TRANSFER
TURBINE BLADES