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TECHNICAL PAPERS: Gas Turbines: Combustion and Fuels

Research on a Methane-Fueled Low NOx Combustor for a Mach 3 Supersonic Transporter Turbojet Engine

[+] Author and Article Information
Y. Kinoshita, T. Oda, J. Kitajima

Akashi Technical Institute, Kawasaki Heavy Industries, Ltd., 1-1 Kawasaki-cho, Akashi City, Hyogo, Japan

J. Eng. Gas Turbines Power 123(4), 787-795 (Oct 01, 2000) (9 pages) doi:10.1115/1.1377009 History: Received October 01, 1999; Revised October 01, 2000
Copyright © 2001 by ASME
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References

Shaw,  R. J., Gilkey,  S., and Hines,  R., 1993, “Engine Technology Challenges for a 21st Century High-Speed Civil Transport,” ISABE, 93, pp. 673-683.
Kinoshita, Y., Kitajima, J., and Oda, T., 1997, “Low NOx Combustor Research for a Mach 3 Turbojet—Concept Validation Test Results,” ASME Paper 97-GT-153.
Rizk, N. K., and Mongia, H. C., 1990, “Ultra-Low NOx Rich-Lean Combustion,” ASME paper 90-GT-87.
Nguyen, H., Bittker, D., and Niedzwiecki, R., 1989, “Investigation of Low NOx Staged Combustor Concept in High Speed Civil Transport Engine,” Paper AIAA 89-2942.
Koff, B. L., 1993, “Aircraft Gas Turbine Emissions Challenge,” ASME Paper 93-GT-422.
Mularz, E. J., 1979, “Lean, Premixed, Prevaporized Combustion for Aircraft Gas Turbine Engine,” Paper AIAA 79-1318.
United Technologies Report, 1992, “JFY1991 Hypersonic Transport Ramjet Propulsion System Study Technical Results Report,” United Technologies.

Figures

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Schematic of the axial staged double annular combustor
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Schematic of the screening rig test apparatus
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Combustion efficiency of axial staged double annular combustor (ASDAC) and same plane double annular combustor (SPDAC) at idle
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Combustor exit temperature profiles of same plane double annular combustor (SPDAC) at idle
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NOx emission index of axial staged double annular combustor (ASDAC) and same plane double annular combustor (SPDAC) at Mach 3 cruise
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Photograph of the demonstration sector combustor
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Engine operations and combustion staging modes
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Emission index of demonstration sector combustor (DSC) at Mach 3 cruise
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Exit gas temperature profiles of demonstration sector combustor (DSC) at Mach 3 cruise
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Linear wall temperature profiles of demonstration sector combustor (DSC) at Mach 3 cruise
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Emissions at landing and takeoff (LTO) cycle to the ICAO regulatory limitations
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Schematic of the same plane double annular combustor
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Staged combustor configurations and their features
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NOx emissions of high-temperature and high-pressure (HTHP) combustor at Mach 3 cruise
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Photograph of high-temperature and high-pressure (HTHP) combustor
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Effect of premixing tube installation angles on NOx and combustion efficiency
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Fuel concentration distributions of fuel injectors
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Concept illustration of the premixture jet swirl combustor
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Low NOx research overall schedules
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Super/hypersonic transport propulsion system research project (HYPR) target NOx emission

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