Rotating detonation combustors (RDCs) offer theoretically a significant total pressure increase, which may result in enhanced cycle efficiency. The fluctuating exhaust of RDC, however, induces low supersonic flow and large flow angle fluctuations at several kHz, which affects the performance of the downstream turbine. In this paper, a numerical methodology is proposed to characterize a supersonic turbine exposed to fluctuations from RDC without any dilution. The inlet conditions of the turbine were extracted from a three-dimensional (3D) unsteady Reynolds-averaged Navier–Stokes simulation of a nozzle attached to a rotating detonation combustor, optimized for minimum flow fluctuations and a mass-flow averaged Mach number of 2 at the nozzle outlet. In a first step, a supersonic turbine able to handle steady Mach 2 inflow was designed based on a method of characteristics solver and total pressure loss was assessed. Afterward, unsteady simulations of eight stator passages exposed to periodic oblique shocks were performed. Total pressure loss was evaluated for several oblique shock frequencies and amplitudes. The unsteady stator outlet profile was extracted and used as inlet condition for the unsteady rotor simulations. Finally, a full stage unsteady simulation was performed to characterize the flow field across the entire turbine stage. Power extraction, airfoil base pressure, and total pressure losses were assessed, which enabled the estimation of the loss mechanisms in supersonic turbine exposed to large unsteady inlet conditions.
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March 2019
Research-Article
Characterization of a Supersonic Turbine Downstream of a Rotating Detonation Combustor
Z. Liu,
Z. Liu
School of Mechanical Engineering,
Purdue University,
West Lafayette, IN 47906
e-mail: liu1752@purdue.edu
Purdue University,
West Lafayette, IN 47906
e-mail: liu1752@purdue.edu
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J. Braun,
J. Braun
School of Mechanical Engineering,
Purdue University,
West Lafayette, IN 47906
e-mail: jamesbraun91@gmail.com
Purdue University,
West Lafayette, IN 47906
e-mail: jamesbraun91@gmail.com
Search for other works by this author on:
G. Paniagua
G. Paniagua
Search for other works by this author on:
Z. Liu
School of Mechanical Engineering,
Purdue University,
West Lafayette, IN 47906
e-mail: liu1752@purdue.edu
Purdue University,
West Lafayette, IN 47906
e-mail: liu1752@purdue.edu
J. Braun
School of Mechanical Engineering,
Purdue University,
West Lafayette, IN 47906
e-mail: jamesbraun91@gmail.com
Purdue University,
West Lafayette, IN 47906
e-mail: jamesbraun91@gmail.com
G. Paniagua
1Corresponding author.
Contributed by the Aircraft Engine Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received June 23, 2018; final manuscript received July 1, 2018; published online October 4, 2018. Editor: Jerzy T. Sawicki.
J. Eng. Gas Turbines Power. Mar 2019, 141(3): 031501 (13 pages)
Published Online: October 4, 2018
Article history
Received:
June 23, 2018
Revised:
July 1, 2018
Citation
Liu, Z., Braun, J., and Paniagua, G. (October 4, 2018). "Characterization of a Supersonic Turbine Downstream of a Rotating Detonation Combustor." ASME. J. Eng. Gas Turbines Power. March 2019; 141(3): 031501. https://doi.org/10.1115/1.4040815
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