Design of an improved turbine rim seal

James Scobie, Roy Teuber, Yan Sheng Li, Carl Sangan, Michael Wilson, Gary Lock

Research output: Chapter in Book/Report/Conference proceedingConference contribution

  • 5 Citations

Abstract

Rim seals are fitted in gas turbines at the periphery of the wheel-space formed between rotor discs and their adjacent casings. These seals, also called platform overlap seals, reduce the ingress of hot gases which can limit the life of highly-stressed components in the engine. This paper describes the development of a new, patented rim-seal concept showing improved performance relative to a reference engine design, using URANS computations of a turbine stage at engine conditions. The CFD study was limited to a small number of purge-flow rates due to computational time and cost, and the computations were validated experimentally at a lower rotational Reynolds number and in conditions under incompressible flow. The new rim seal features a stator-side angel wing and two buffer cavities between outer and inner seals: the angel-wing promotes a counter-rotating vortex to reduce the effect of the ingress on the stator; the two buffer cavities are shown to attenuate the circumferential pressure asymmetries of the fluid ingested from the mainstream annulus. Rotor disc pumping is exploited to reduce the sealing flow rate required to prevent ingress, with the rotor boundary layer also providing protective cooling. Measurements of gas concentration and swirl ratio, determined from static and total pressure, were used to assess the performance of the new seal concept relative to a bench-mark generic seal. The radial variation of concentration through the seal was measured in the experiments and these data captured the improvements due to the intermediate buffer cavities predicted by the CFD. This successful design approach is a potent combination of insight provided by computation, and the flexibility and expedience provided by experiment.
LanguageEnglish
Title of host publicationProceedings of ASME Turbo Expo 2015
Subtitle of host publicationTurbine Technical Conference and Exposition. Volume 5C
Place of PublicationMontreal, Canada.
PagesV05CT15A006
Number of pages12
DOIs
StatusPublished - 2015

Fingerprint

Seals
Turbines
Rotors
Engines
Stators
Computational fluid dynamics
Flow rate
Incompressible flow
Gases
Gas turbines
Wheels
Boundary layers
Vortex flow
Reynolds number
Experiments
Cooling
Fluids
Costs

Cite this

Scobie, J., Teuber, R., Li, Y. S., Sangan, C., Wilson, M., & Lock, G. (2015). Design of an improved turbine rim seal. In Proceedings of ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. Volume 5C (pp. V05CT15A006). [GT2015-42327] Montreal, Canada.. DOI: 10.1115/GT2015-42327

Design of an improved turbine rim seal. / Scobie, James; Teuber, Roy; Li, Yan Sheng; Sangan, Carl; Wilson, Michael; Lock, Gary.

Proceedings of ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. Volume 5C. Montreal, Canada., 2015. p. V05CT15A006 GT2015-42327.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Scobie, J, Teuber, R, Li, YS, Sangan, C, Wilson, M & Lock, G 2015, Design of an improved turbine rim seal. in Proceedings of ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. Volume 5C., GT2015-42327, Montreal, Canada., pp. V05CT15A006. DOI: 10.1115/GT2015-42327
Scobie J, Teuber R, Li YS, Sangan C, Wilson M, Lock G. Design of an improved turbine rim seal. In Proceedings of ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. Volume 5C. Montreal, Canada.2015. p. V05CT15A006. GT2015-42327. Available from, DOI: 10.1115/GT2015-42327
Scobie, James ; Teuber, Roy ; Li, Yan Sheng ; Sangan, Carl ; Wilson, Michael ; Lock, Gary. / Design of an improved turbine rim seal. Proceedings of ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. Volume 5C. Montreal, Canada., 2015. pp. V05CT15A006
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