A New Interpretation of Hot Gas Ingress Through Turbine Rim Seals Influenced by Mainstream Annulus Swirl

Research output: Chapter or section in a book/report/conference proceedingChapter in a published conference proceeding


Rim seals are fitted at the periphery of the stator and rotor discs to reduce the adverse effects of hot gas ingress on highly stressed turbine components limited by temperature. Ingress is induced by rotational effects such as disc pumping, as well as by asymmetric pressure-driven unsteady phenomena. These influences superpose to form a complex flow-physics problem that is a challenge for computational fluid dynamics. Engine designers typically use practical low-order models that require empirical validation and correlating parameters. This paper identifies the swirl ratio in the mainstream annulus as a dominant characterising parameter to predict ingress. This is a new interpretation that is supported by extending a low-order model based on turbulent transport using an effective eddy mixing length based on the difference in swirl between the annulus and seal clearance.

Experimental measurements were made using a 1.5-stage turbine rig at low Reynolds number. The influence of annulus swirl ratio was investigated over a range of flow conditions and two rim-seal geometries, with the ingress quantified using CO2 tracer concentration in the sealing flow. The concentration data were complemented by measurements in the annulus using a five-hole aerodynamic probe.
Original languageEnglish
Title of host publicationHeat Transfer - General Interest/Additive Manufacturing Impacts on Heat Transfer; Internal Air Systems; Internal Cooling
PublisherAmerican Society of Mechanical Engineers (ASME)
ISBN (Electronic)9780791886045
Publication statusPublished - Oct 2022
EventASME Turbo Expo 2022 - Rotterdam, Netherlands
Duration: 13 Jun 202217 Jun 2022

Publication series

NameProceedings of the ASME Turbo Expo


ConferenceASME Turbo Expo 2022

Bibliographical note

Publisher Copyright:
Copyright © 2022 by ASME.


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