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      Computational Study of Combustor–Turbine Interactions

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          Abstract

          The Open National Combustion Code is applied to the simulation of a realistic combustor configuration (Energy Efficient Engine) in order to investigate the unsteady flowfields inside the combustor and around the first-stage stator of a high-pressure turbine. We consider 1 / 15 (24 deg) of the full annular Energy Efficient Engine combustor with three different geometries of the combustor exit: one without the vane and two others with the vane set at different relative positions in relation to the fuel nozzle (clocking). Although it is common to take the exit flow profiles obtained by separately simulating the combustor and then feed as the inflow profile when modeling the high-pressure turbine, our studies show that the unsteady flowfields are influenced by the presence of the vane as well as clocking. More importantly, the characteristics (e.g., distribution and strength) of the high-temperature spots (i.e., hot streaks) appearing on the vane are significantly altered. This indicates the importance of simultaneously modeling both the combustor and the high-pressure turbine to understand the mechanics of the unsteady formulation of hot streaks.

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          Most cited references35

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          Large Eddy Simulations of gaseous flames in gas turbine combustion chambers

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            Preconditioned methods for solving the incompressible and low speed compressible equations

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              The Application of Preconditioning in Viscous Flows

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                Author and article information

                Conference
                jpp
                Journal of Propulsion and Power
                J. Propulsion
                American Institute of Aeronautics and Astronautics
                0748-4658
                1533-3876
                30 July 2018
                November–December 2018
                : 34
                : 6
                : 1529-1541
                Affiliations
                NASA John H. Glenn Research Center at Lewis Field , Cleveland, Ohio 44135
                Author notes
                [*]

                Mechanical Engineer; currently Vantage Partners, LLC; kenji.miki@ 123456nasa.gov . Member AIAA.

                [†]

                Branch Chief, Engine Combustion; Jeffrey.P.Moder@ 123456nasa.gov . Member AIAA.

                [‡]

                Senior Technologist; meng-sing.liou@ 123456nasa.gov . Fellow AIAA.

                Article
                B36909 B36909
                10.2514/1.B36909
                80be7c7b-338f-425e-b33a-26583ac77588
                This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the ISSN 0748-4658 (print) or 1533-3876 (online) to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp.
                History
                : 14 September 2017
                : 15 May 2018
                : 18 May 2018
                Page count
                Figures: 19, Tables: 2
                Funding
                Funded by: Glenn Research Center10.13039/100006193
                Categories
                Full-Length Paper

                Engineering,Physics,Mechanical engineering,Space Physics
                Engineering, Physics, Mechanical engineering, Space Physics

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