NDLI: Numerical study of low emission gas turbine combustor concepts

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Numerical study of low emission gas turbine combustor concepts

Content Provider	NASA Technical Reports Server (NTRS)
Author	Yang, Song-Lin
Copyright Year	2002
Description	To further reduce pollutant emissions, such as CO, NO(x), UHCs, etc., in the next few decades, innovative concepts of gas turbine combustors must be developed. Several concepts, such as the LIPP (Lean- Premixed- Prevaporized), RQL (Rich-Burn Quick-Quench Lean-Burn), and LDI (Lean-Direct-Injection), have been under study for many years. To fully realize the potential of these concepts, several improvements, such as inlet geometry, air swirler, aerothermochemistry control, fuel preparation, fuel injection and injector design, etc., must be made, which can be studied through the experimental method and/or the numerical technique. The purpose of this proposal is to use the CFD technique to study, and hence, to guide the design process for low emission gas turbine combustors. A total of 13 technical papers have been (or will be) published.
File Size	122272
Page Count	4
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_20020052421
Archival Resource Key	ark:/13960/t6c29v91t
Language	English
Publisher Date	2002-01-01
Access Restriction	Open
Subject Keyword	Aircraft Propulsion And Power Numerical Analysis Gas Turbines Injectors Aerothermochemistry Computational Fluid Dynamics Contaminants Premixing Injection Fuel Injection Combustion Chambers Exhaust Emission Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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