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Int. J. Turbomach. Propuls. Power, Volume 3, Issue 4 (December 2018)

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Cover Story (view full-size image) Leading edge impingement systems are increasingly being used for high-pressure turbine blades in [...] Read more.
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Open AccessArticle A Comparison of Experimental and Computational Heat Transfer Results for a Leading Edge Impingement System
Int. J. Turbomach. Propuls. Power 2018, 3(4), 23; https://doi.org/10.3390/ijtpp3040023
Received: 20 June 2018 / Revised: 7 November 2018 / Accepted: 12 November 2018 / Published: 16 November 2018
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Abstract
Leading edge impingement systems are increasingly being used for high pressure turbine blades in gas turbine engines, in regions where very high heat loads are encountered. The flow structure in such systems can be very complex and high resolution experimental data is required
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Leading edge impingement systems are increasingly being used for high pressure turbine blades in gas turbine engines, in regions where very high heat loads are encountered. The flow structure in such systems can be very complex and high resolution experimental data is required for engine-realistic systems to enable code validation and optimal design. This paper presents spatially resolved heat transfer distributions for an engine-realistic impingement system for multiple different hole geometries, with jet Reynolds numbers in the range of 13,000–22,000. Following this, Reynolds-averaged Navier-Stokes computational fluid dynamics simulations are compared to the experimental data. The experimental results show variation in heat transfer distributions for different geometries, however average levels are primarily dependent on jet Reynolds number. The computational simulations match the shape of the distributions well however with a consistent over-prediction of around 10% in heat transfer levels. Full article
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Open AccessArticle Preliminary Design Considerations for Variable Geometry Radial Turbines with Multi-Points Specifications
Int. J. Turbomach. Propuls. Power 2018, 3(4), 22; https://doi.org/10.3390/ijtpp3040022
Received: 23 July 2018 / Revised: 24 October 2018 / Accepted: 26 October 2018 / Published: 8 November 2018
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Abstract
Radial turbines’ preliminary designs are usually carried out through some dimensionless approaches, such as the loading-to-flow-diagram and/or the blade speed ratio. In case of variable nozzle radial turbines, multi-points specifications must be considered, related to the improvement of the operating range. As preliminary
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Radial turbines’ preliminary designs are usually carried out through some dimensionless approaches, such as the loading-to-flow-diagram and/or the blade speed ratio. In case of variable nozzle radial turbines, multi-points specifications must be considered, related to the improvement of the operating range. As preliminary design correlations and standards usually taken into consideration arise from studies dedicated to fixed geometry radial turbines, they need to be updated with regard to nozzle off-design opening configurations. This paper provides some theoretical basics in order to help designers considering variable geometry problems. Some complementary elements about the dimensionless methods are given by taking into account the nozzle opening effect. Then, useful considerations are brought regarding the preliminary design of variable geometry radial turbines with multi-points specifications. Full article
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Int. J. Turbomach. Propuls. Power EISSN 2504-186X Published by MDPI AG, Basel, Switzerland RSS E-Mail Table of Contents Alert
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