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Selection of one-dimensional design parameter 'reaction degree' for 1 st stage of a cooled gas turbine
KTH, School of Industrial Engineering and Management (ITM), Energy Technology, Heat and Power Technology.
KTH, School of Industrial Engineering and Management (ITM), Energy Technology, Heat and Power Technology.
2012 (English)In: Proc. ASME Turbo Expo, 2012, no PARTS A, B, AND C, 2345-2354 p.Conference paper, Published paper (Refereed)
Abstract [en]

The recommendations available today in open literature for the choice of design parameter such as flow coefficient, stage loading and reaction degree incorporates mainly the influence of aerodynamics loss on efficiency. However, it is difficult to find the recommendation relating the influence of not only the aerodynamics loss but also cooling mass flow and cooling losses on varying most influential design parameters. In this paper, preliminary design and performance guidelines are presented for a cooled turbine stage using the 1D design tool LUAXT. The intention is to provide recommendations on the selection of design parameters, mainly reaction degree, which is found to be highly influenced by not only the aerodynamics loss but also the cooling mass flow and cooling loss such as in 1st stage of a High Pressure Turbines (HPT). The One-Dimensional (1D) design methods used to perform this task are verified and validated against experimental test data. A comparison of different loss models has been performed to provide most accurate outcomes for certain tested ranges. Based on the outcomes of this study, 'Craig & Cox' loss model has been considered to perform subsequent investigations for HPT design and performance estimation while formulating a parametric study. From this study, the design recommendations for the selection of performance parameter reaction degree are developed for cooled turbines. The results shows that for a HPT 1st stage, the recommended reaction degree range of 0.20 to 0.37 seems to provide the optimum stage design when chosen for stage loading in between 1.40 to 1.80 along with the stator exit flow angle in range of 74° to 78°.

Place, publisher, year, edition, pages
2012. no PARTS A, B, AND C, 2345-2354 p.
Series
Proceedings of the ASME Turbo Expo, 8
Keyword [en]
Cooling mass flow, Design parameters, Design recommendations, Experimental test, High pressure turbine, Performance estimation, Performance parameters, Preliminary design, Design, Exhibitions, Gas turbines, Large scale systems, Aerodynamics
National Category
Energy Engineering
Identifiers
URN: urn:nbn:se:kth:diva-129686DOI: 10.1115/GT2012-69758ISI: 000335720901042Scopus ID: 2-s2.0-84881187785ISBN: 9780791844748 (print)OAI: oai:DiVA.org:kth-129686DiVA: diva2:654749
Conference
ASME Turbo Expo 2012: Turbine Technical Conference and Exposition
Note

QC 20131008

Available from: 2013-10-08 Created: 2013-10-03 Last updated: 2014-10-09Bibliographically approved

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CiteExportLink to record
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  • apa
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Output format
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