The Effect of Vanes and Blades on Ingress in Gas Turbines

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

Abstract

This paper presents experimental and computational results using a 1.5-stage test rig designed to investigate the effects of ingress through a double radial overlap rim-seal. The effect of the vanes and blades on ingress was investigated by a series of carefully-controlled experiments: firstly, the position of the vane relative to the rim seal was varied; secondly, the effect of the rotor blades was isolated using a disc with and without blades.
Measurements of steady pressure in the annulus show a strong influence of the vane position. The relationship between sealing effectiveness and purge flow-rate exhibited a pronounced inflexion for intermediate levels of purge; the inflexion did not occur for experiments with a bladeless rotor. Shifting the vane closer to the rim-seal, and therefore the blade, caused a local increase in ingress in the inflexion region; again this effect was not observed for the bladeless experiments.
Unsteady pressure measurements at the periphery of the wheel-space revealed the existence of large-scale pressure structures (or instabilities) which depended weakly on the vane position and sealing flow rate. These were measured with and without the blades on the rotor disc. In all cases these structures rotated close to the disc speed.
Original languageEnglish
Title of host publicationProceedings of the ASME Turbo Expo 2019: Turbine Technical Conference and Exposition
PublisherAmerican Society of Mechanical Engineers (ASME)
Number of pages14
Publication statusPublished - 17 Jun 2019
EventASME Turbo Expo 2019 - Arizona, Phoenix, USA United States
Duration: 17 Jun 201921 Jun 2019
https://event.asme.org/Events/media/library/resources/turbo/Turbo-Expo-2019-Program.pdf

Conference

ConferenceASME Turbo Expo 2019
CountryUSA United States
CityPhoenix
Period17/06/1921/06/19
Internet address

Cite this

Hualca Tigsilema, F. P., Horwood, J., Sangan, C., Lock, G., & Scobie, J. (2019). The Effect of Vanes and Blades on Ingress in Gas Turbines. In Proceedings of the ASME Turbo Expo 2019: Turbine Technical Conference and Exposition [GT2019-90987] American Society of Mechanical Engineers (ASME).

The Effect of Vanes and Blades on Ingress in Gas Turbines. / Hualca Tigsilema, Fabian Patricio; Horwood, Joshua; Sangan, Carl; Lock, Gary; Scobie, James.

Proceedings of the ASME Turbo Expo 2019: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers (ASME), 2019. GT2019-90987.

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

Hualca Tigsilema, FP, Horwood, J, Sangan, C, Lock, G & Scobie, J 2019, The Effect of Vanes and Blades on Ingress in Gas Turbines. in Proceedings of the ASME Turbo Expo 2019: Turbine Technical Conference and Exposition., GT2019-90987, American Society of Mechanical Engineers (ASME), ASME Turbo Expo 2019, Phoenix, USA United States, 17/06/19.
Hualca Tigsilema FP, Horwood J, Sangan C, Lock G, Scobie J. The Effect of Vanes and Blades on Ingress in Gas Turbines. In Proceedings of the ASME Turbo Expo 2019: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers (ASME). 2019. GT2019-90987
Hualca Tigsilema, Fabian Patricio ; Horwood, Joshua ; Sangan, Carl ; Lock, Gary ; Scobie, James. / The Effect of Vanes and Blades on Ingress in Gas Turbines. Proceedings of the ASME Turbo Expo 2019: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers (ASME), 2019.
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N2 - This paper presents experimental and computational results using a 1.5-stage test rig designed to investigate the effects of ingress through a double radial overlap rim-seal. The effect of the vanes and blades on ingress was investigated by a series of carefully-controlled experiments: firstly, the position of the vane relative to the rim seal was varied; secondly, the effect of the rotor blades was isolated using a disc with and without blades.Measurements of steady pressure in the annulus show a strong influence of the vane position. The relationship between sealing effectiveness and purge flow-rate exhibited a pronounced inflexion for intermediate levels of purge; the inflexion did not occur for experiments with a bladeless rotor. Shifting the vane closer to the rim-seal, and therefore the blade, caused a local increase in ingress in the inflexion region; again this effect was not observed for the bladeless experiments.Unsteady pressure measurements at the periphery of the wheel-space revealed the existence of large-scale pressure structures (or instabilities) which depended weakly on the vane position and sealing flow rate. These were measured with and without the blades on the rotor disc. In all cases these structures rotated close to the disc speed.

AB - This paper presents experimental and computational results using a 1.5-stage test rig designed to investigate the effects of ingress through a double radial overlap rim-seal. The effect of the vanes and blades on ingress was investigated by a series of carefully-controlled experiments: firstly, the position of the vane relative to the rim seal was varied; secondly, the effect of the rotor blades was isolated using a disc with and without blades.Measurements of steady pressure in the annulus show a strong influence of the vane position. The relationship between sealing effectiveness and purge flow-rate exhibited a pronounced inflexion for intermediate levels of purge; the inflexion did not occur for experiments with a bladeless rotor. Shifting the vane closer to the rim-seal, and therefore the blade, caused a local increase in ingress in the inflexion region; again this effect was not observed for the bladeless experiments.Unsteady pressure measurements at the periphery of the wheel-space revealed the existence of large-scale pressure structures (or instabilities) which depended weakly on the vane position and sealing flow rate. These were measured with and without the blades on the rotor disc. In all cases these structures rotated close to the disc speed.

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