Detailed radial distributions of rotor heat transfer coefficients are presented for three basic disk-cavity geometries applicable to gas turbines. The experimental apparatus has been designed to obtain local heat transfer data on a number of easily interchangeable rotor surfaces. The method employs thin thermochromic liquid crystal coatings upon the rotor surfaces together with video system data acquisition and computer-assisted image analysis to detect surface color display and to extract heat transfer information. A thermally transient, aerodynamically steady technique is used, which attains consistent thermal boundary conditions over the entire disk cavity. Cooling air is introduced into the disk cavity via a single circular jet mounted perpendicularly into the stator at one of the three radial locations: 0.4, 0.6, or 0.8 times the rotor radius. Rotor heat transfer coefficients have been obtained over a range of parameters including disk rotational Reynolds numbers of 2 to 5 × 105, rotor/stator hub spacing-to-disk radius ratios of 0.025 to 0.15, and jet mass flow rates between 0.10 and 0.40 times the turbulent pumped flow rate of a free disk. The rotor surfaces include a parallel rotor-stator system, a rotor with 5 percent diverging taper, and a similarly tapered rotor with a rim sealing lip at its extreme radius. Results are presented showing the effects of the parallel rotor, which indicate strong variations in local Nusselt numbers for all but rotational speed. These results are compared to associated hub injection data of Part I of this study, demonstrating that overall rotor heat transfer is optimized by either hub injection or radial location injection of coolant dependent upon the configuration. Results with the use of the tapered rotor show significant variations in local Nusselt number compared with those of the parallel rotor, while the addition of a rim sealing lip appears to increase the Nusselt number level.
Skip Nav Destination
Article navigation
January 1992
Research Papers
Local Heat Transfer in Turbine Disk Cavities: Part II—Rotor Cooling With Radial Location Injection of Coolant
R. S. Bunker,
R. S. Bunker
Lehrstuhl und Institut fu¨r Thermische Stro¨mungsmaschinen, Universita¨t Karlsruhe, Karlsruhe, Federal Republic of Germany
Search for other works by this author on:
D. E. Metzger,
D. E. Metzger
Lehrstuhl und Institut fu¨r Thermische Stro¨mungsmaschinen, Universita¨t Karlsruhe, Karlsruhe, Federal Republic of Germany
Search for other works by this author on:
S. Wittig
S. Wittig
Lehrstuhl und Institut fu¨r Thermische Stro¨mungsmaschinen, Universita¨t Karlsruhe, Karlsruhe, Federal Republic of Germany
Search for other works by this author on:
R. S. Bunker
Lehrstuhl und Institut fu¨r Thermische Stro¨mungsmaschinen, Universita¨t Karlsruhe, Karlsruhe, Federal Republic of Germany
D. E. Metzger
Lehrstuhl und Institut fu¨r Thermische Stro¨mungsmaschinen, Universita¨t Karlsruhe, Karlsruhe, Federal Republic of Germany
S. Wittig
Lehrstuhl und Institut fu¨r Thermische Stro¨mungsmaschinen, Universita¨t Karlsruhe, Karlsruhe, Federal Republic of Germany
J. Turbomach. Jan 1992, 114(1): 221-228 (8 pages)
Published Online: January 1, 1992
Article history
Received:
January 13, 1990
Online:
June 9, 2008
Connected Content
This is a companion to:
Stress Analysis and Thermal Characterization of a High Pin Count PQFP
This is a companion to:
Surface Roughness and Its Effects on the Heat Transfer Mechanism in Spray Cooling
Citation
Bunker, R. S., Metzger, D. E., and Wittig, S. (January 1, 1992). "Local Heat Transfer in Turbine Disk Cavities: Part II—Rotor Cooling With Radial Location Injection of Coolant." ASME. J. Turbomach. January 1992; 114(1): 221–228. https://doi.org/10.1115/1.2927989
Download citation file:
Get Email Alerts
Related Articles
Local Heat Transfer in Turbine Disk Cavities: Part I—Rotor and Stator Cooling With Hub Injection of Coolant
J. Turbomach (January,1992)
Transient Liquid Crystal Measurement of Local Heat Transfer on a Rotating Disk With Jet Impingement
J. Turbomach (January,1991)
Influence of Fluid Dynamics on Heat Transfer in a Preswirl Rotating-Disk System
J. Eng. Gas Turbines Power (October,2005)
Heat Transfer Measurements Using Liquid Crystals in a Preswirl Rotating-Disk System
J. Eng. Gas Turbines Power (April,2005)
Related Proceedings Papers
Related Chapters
Thermodynamic Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential