Turbulent heat transfer and friction in a segmental channel that simulates leading-edge cooling channels of modern turbine blades /
2.0, 4.0, 6.0, and infinity, and mass flow rates
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| Format: | Thesis eBook |
| Language: | English |
| Published: |
[Place of publication not identified] :
[publisher not identified] ;
1995.
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| Subjects: | |
| Online Access: | Link to OAKTrust copy |
| Summary: | 2.0, 4.0, 6.0, and infinity, and mass flow rates are conducted to determine the streamwise distributions of cooling channels in stator blades of gas turbines. The corresponding to Reynolds numbers between 10 000 and 70 000 curved wall-to-smooth flat wall heat flux ratio of 0.0, 1.0, Experiments are conducted to study the effects of channel experiments using thermochromic liquid crystals at Reynolds friction characteristics of turbulent flows in leading edge geometry and asymmetric heating on the heat transfer and has a pitch-to-height ratio of 10. Steady state heat heat transfer between the ribs on the curved wall. heat transfer maps are also obtained from transient height-to-hydraulic diameter ratio of 0.0625. The rib array indicate that the effect of wall heat flux ratio gradually is only mildly dependent on the channel cross-sectional leading edge cooling channels are modeled as straight number ratio and relative thermal performance for the curved number. In addition, the transient results indicate that numbers of approximately 35 000. The overall ribbed curved Nusselt number for fully developed turbulent flow through a predicted with a simple power function of the Reynolds reduces with increasing Reynolds number. The overall Nusselt rib-roughened curved wall and the smooth flat wall. Local segmental channels with 90' rib turbulators on the curved shape. The smooth flat wall Nusselt number ratio decreases the regionally-averaged heat transfer coefficient on both the there is substantial streamwise and spanwise variations of transfer experiments for three channel cross sections, ribbed tube, increases slightly with increasing heat flux ratio and wall and smooth wall on all three test sections can be wall Nusselt number, normalized with the corresponding wall only. The ribs are square in cross section and have a with increasing heat flux ratio and, in general the results |
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| Item Description: | "Major subject: Mechanical Engineering". Vita. |
| Physical Description: | xv, 180 leaves : illustrations ; 28 cm. Also available online. Issued also on microfiche from Lange Micrographics. |
| Bibliography: | Includes bibliographical references. |