The effect of the purge flow, engine-like blade pressure field, and mainstream flow coefficient are studied experimentally for a single and double lip rim seal. Compared to the single lip, the double lip seal requires less purge flow for similar levels of cavity seal effectiveness. Unlike the double lip seal, the single lip seal is sensitive to overall Reynolds number, the addition of a simulated blade pressure field, and large-scale nonuniform ingestion. In the case of both seals, unsteady pressure variations attributed to shear layer interaction between the mainstream and rim seal flows appear to be important for ingestion at off-design flow coefficients. The double lip seal has both a weaker vane pressure field in the rim seal cavity and a smaller difference in seal effectiveness across the lower lip than the single lip seal. As a result, the double lip seal is less sensitive in the rotor–stator cavity to changes in shear layer interaction and the effects of large-scale circumferentially nonuniform ingestion. However, the reduced flow rate through the double lip seal means that the outer lip has increased sensitivity to shear layer interactions. Overall, it is shown that seal performance is driven by both the vane/blade pressure field and the gradient in seal effectiveness across the inner lip. This implies that accurate representation of both, the pressure field and the mixing due to shear layer interaction, would be necessary for more reliable modeling.
Skip Nav Destination
Article navigation
November 2017
Research-Article
A Comparison of Single and Double Lip Rim Seal Geometries
Svilen S. Savov,
Svilen S. Savov
Whittle Laboratory,
Department of Engineering,
University of Cambridge,
Cambridge CB3 0DY, UK
e-mail: sss44@cam.ac.uk
Department of Engineering,
University of Cambridge,
Cambridge CB3 0DY, UK
e-mail: sss44@cam.ac.uk
Search for other works by this author on:
Nicholas R. Atkins,
Nicholas R. Atkins
Whittle Laboratory,
Department of Engineering,
University of Cambridge,
Cambridge CB3 0DY, UK
e-mail: nra27@cam.ac.uk
Department of Engineering,
University of Cambridge,
Cambridge CB3 0DY, UK
e-mail: nra27@cam.ac.uk
Search for other works by this author on:
Sumiu Uchida
Sumiu Uchida
Technology and Innovation HQ,
Mitsubishi Heavy Industries Ltd.,
5-717-1 Fukahori-machi,
Nagasaki 851-0392, Japan
e-mail: sumiu_uchida@mhi.co.jp
Mitsubishi Heavy Industries Ltd.,
5-717-1 Fukahori-machi,
Nagasaki 851-0392, Japan
e-mail: sumiu_uchida@mhi.co.jp
Search for other works by this author on:
Svilen S. Savov
Whittle Laboratory,
Department of Engineering,
University of Cambridge,
Cambridge CB3 0DY, UK
e-mail: sss44@cam.ac.uk
Department of Engineering,
University of Cambridge,
Cambridge CB3 0DY, UK
e-mail: sss44@cam.ac.uk
Nicholas R. Atkins
Whittle Laboratory,
Department of Engineering,
University of Cambridge,
Cambridge CB3 0DY, UK
e-mail: nra27@cam.ac.uk
Department of Engineering,
University of Cambridge,
Cambridge CB3 0DY, UK
e-mail: nra27@cam.ac.uk
Sumiu Uchida
Technology and Innovation HQ,
Mitsubishi Heavy Industries Ltd.,
5-717-1 Fukahori-machi,
Nagasaki 851-0392, Japan
e-mail: sumiu_uchida@mhi.co.jp
Mitsubishi Heavy Industries Ltd.,
5-717-1 Fukahori-machi,
Nagasaki 851-0392, Japan
e-mail: sumiu_uchida@mhi.co.jp
Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received November 24, 2016; final manuscript received May 3, 2017; published online July 19, 2017. Editor: David Wisler.
J. Eng. Gas Turbines Power. Nov 2017, 139(11): 112601 (13 pages)
Published Online: July 19, 2017
Article history
Received:
November 24, 2016
Revised:
May 3, 2017
Citation
Savov, S. S., Atkins, N. R., and Uchida, S. (July 19, 2017). "A Comparison of Single and Double Lip Rim Seal Geometries." ASME. J. Eng. Gas Turbines Power. November 2017; 139(11): 112601. https://doi.org/10.1115/1.4037027
Download citation file:
Get Email Alerts
Numerical Investigation of CO and NO Production From Premixed Hydrogen/Methane Fuel Blends
J. Eng. Gas Turbines Power (April 2025)
An Efficient Uncertainty Quantification Method Based on Inter-Blade Decoupling for Compressors
J. Eng. Gas Turbines Power (April 2025)
Experimental Design Validation of a Swirl-Stabilized Burner With Fluidically Variable Swirl Number
J. Eng. Gas Turbines Power (April 2025)
Experimental Characterization of a Bladeless Air Compressor
J. Eng. Gas Turbines Power (April 2025)
Related Articles
Influence of Stator-Rotor Interaction on the Aerothermal Performance of Recess Blade Tips
J. Turbomach (January,2011)
Aerothermal Impact of Stator-Rim Purge Flow and Rotor-Platform Film Cooling on a Transonic Turbine Stage
J. Turbomach (April,2010)
Film-Cooling Effectiveness on a Rotating Turbine Platform Using Pressure Sensitive Paint Technique
J. Turbomach (October,2010)
Unsteady Forces of Rotor Blades in Full and Partial Admission Turbines
J. Turbomach (October,2011)
Related Proceedings Papers
Related Chapters
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Fans and Air Handling Systems
Thermal Management of Telecommunications Equipment