Integration of a transonic high-pressure turbine with a rotating detonation combustor and a diffuser

Liu, Zhe; Braun, James; Paniagua, Guillermo

doi:10.1515/tjj-2020-0016

Integration of a transonic high-pressure turbine with a rotating detonation combustor and a diffuser

Journal Article · Mon Feb 20 23:00:00 EST 2023 · International Journal of Turbo and Jet Engines

DOI:https://doi.org/10.1515/tjj-2020-0016· OSTI ID:2418121

Liu, Zhe ^[1]; Braun, James ^[2]; Paniagua, Guillermo ^[2]

Purdue University , School of Mechanical Engineering , West Lafayette , USA; OSTI
Purdue University , School of Mechanical Engineering , West Lafayette , USA

Abstract

In this paper, a diffuser is used to integrate a transonic high-pressure turbine with a rotating detonation combustor (RDC). The paper focuses on the required design modifications to the turbine endwalls (EW) to enable high efficiency, while preserving the airfoil blade-to-blade geometry. The main challenge is the stator passage unstarting, due to the high inlet Mach number. First of all, steady Reynolds Averaged Navier Stokes simulations were performed to compare the efficiency of turbines with constant-radius EWs to turbines with axisymmetric EWs. A modified EW design prevented the unstarting of the stator passage, enabling a significant gain in performance. Afterward, the influence on the turbine efficiency and damping due to the unsteadiness from the diffuser-like fluctuations of the RDC was evaluated with unsteady Reynolds Averaged Navier Stokes simulations with a mixing plane approach (MPA). Full unsteady simulations were carried out on selected inlet conditions and compared to the mixing plane results. This parametric study provides turbine designers with recommended diffusion rates along the vane EWs. Additionally, we provide guidance on the upstream diffuser design, specifically the required damping and outlet Mach number.

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

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

DOE Contract Number:: FE0023983

OSTI ID:: 2418121

Journal Information:: International Journal of Turbo and Jet Engines, Journal Name: International Journal of Turbo and Jet Engines Journal Issue: 1 Vol. 40; ISSN 0334-0082

Publisher:: De Gruyter

Country of Publication:: United States

Language:: English

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