Thermal power plant upgrade via a rotating detonation combustor and retrofitted turbine with optimized endwalls

Liu, Zhe; Braun, James; Paniagua, Guillermo

doi:10.1016/j.ijmecsci.2020.105918

Title: Thermal power plant upgrade via a rotating detonation combustor and retrofitted turbine with optimized endwalls

Journal Article · Wed Jul 15 00:00:00 EDT 2020 · International Journal of Mechanical Sciences

DOI:https://doi.org/10.1016/j.ijmecsci.2020.105918· OSTI ID:1849138

Liu, Zhe ^[1]; Braun, James ^[1]; Paniagua, Guillermo ^[1]

Purdue Univ., West Lafayette, IN (United States)

Over the past decade, pressure gain combustion research has promised over 10 percentage-points of increase in power plant thermal efficiency. Alas, to realize such potential gain, one must effectively couple the turbine with the detonation combustor, whose exhaust conditions differ substantially from current state of the art gas turbines. This paper presents a modeling approach that enables a superior thermodynamic cycle with a rotating detonation combustor and a retrofitted gas turbine by including a diffuser downstream of the combustor and by contouring the turbine endwall, while preserving the airfoil geometry. We propose a multi-step optimization strategy, parametrizing the endwall geometry with a few control points, without altering the airfoil geometry, and with the stage turbine efficiency as objective function. In a first step the turbine performance is assessed with steady inlet conditions by solving the steady three-dimensional Reynolds-Averaged Navier-Stokes equations. In a second step, the inlet conditions are unsteady, as predicted from a detonation combustor and a diffuser, and three-dimensional full unsteady simulations are performed with an unsteady Reynolds-Averaged Navier-Stokes solver. By altering the vane endwall, the steady optimization yielded an efficiency increase of 12% relative to the baseline, while the unsteady optimization resulted in 21% increase compared to the datum turbine. Finally, a full engine analysis demonstrated the superiority of pressure gain combustion which included a realistic thermodynamic cycle of the combustor, the diffuser and the optimized turbine components.

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Research Organization:: Aerojet Rocketdyne, Sacramento, CA (United States)

Sponsoring Organization:: USDOE Office of Fossil Energy (FE)

Grant/Contract Number:: FE0023983; 077-17

OSTI ID:: 1849138

Alternate ID(s):: OSTI ID: 1809419

Journal Information:: International Journal of Mechanical Sciences, Vol. 188, Issue C; ISSN 0020-7403

Publisher:: ElsevierCopyright Statement

Country of Publication:: United States

Language:: English

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