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Design Procedure of a Reverse Flow Combustor for a Helicopter Engine with High Temperature Rise Cranfield University, UK
- Format:
- Conference/Event
- Author/Creator:
- Khandelwal, Khandelwal, author.
- Conference Name:
- Aerospace Technology Conference & Exposition (2011-10-18 : Toulouse, France)
- Language:
- English
- Physical Description:
- 1 online resource
- Place of Publication:
- Warrendale, PA SAE International 2011
- Summary:
- Modern advanced engines are expected to operate with highercombustor temperature rise and lower emissions. These developmenttrends result in more combustor design difficulties. Hightemperature rise requires more air for complete combustion, hencereducing the amount of cooling air. Emissions consist of CO₂, UHC,NOx, smoke and water vapor. CO₂ is an unavoidableemission of combustion reaction, whereas emissions ofNOx mainly depend on temperature. A lean primary zonedesign is required to achieve low NOx emission. Reverseflow combustors have more difficulties because of the presence ofturn section which does not exist in other combustorconfigurations.There are many studies in public domain which talk about designof combustors. But none of them gives detailed guide on designingreverse flow combustor. The objective of this paper is to provide areverse flow combustor design procedure, with emissions andperformance analysis. The combustor designed in this study isexpected to be used in advanced helicopter engine. Substantialamount of literature is available on conventional combustor designswhich mainly include empirical and semi-empirical models plusexperiment test methods. All these combustor design methods focuson the direct flow combustor. In this study, a reverse flowcombustor design methodology is proposed. The design procedureincludes the combustor sizing, fuel injector design, swirl cupdesign, air distribution along the liner, primary hole design,dilution zone design and the cooling system design. Finaldimensions are also shown in a figure, which have been validatedwith one of the present combustor designs. After finalizing thedesign of the combustor, overall performance has been evaluatedusing empirical correlations and equations
- Notes:
- Vendor supplied data
- Publisher Number:
- 2011-01-2562
- Access Restriction:
- Restricted for use by site license
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