elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Privacy Policy | Contact | Deutsch
Fontsize: [-] Text [+]

Aerodynamic Investigation of Guide Vane Configurations Downstream a Rotating Detonation Combustor

Asli, Majid and Stathopoulos, Panagiotis and Paschereit, Christian Oliver (2021) Aerodynamic Investigation of Guide Vane Configurations Downstream a Rotating Detonation Combustor. Journal of Engineering for Gas Turbines and Power, 143 (6). American Society of Mechanical Engineers (ASME). doi: 10.1115/1.4049188. ISSN 0742-4795.

Full text not available from this repository.

Official URL: https://doi.org/10.1115/1.4049188

Abstract

Any outlet restriction downstream of pressure gain combustion (PGC), such as turbine blades, affects its flow field and may cause additional thermodynamic losses. The unsteadiness in the form of pressure, temperature, and velocity vector fluctuations has a negative impact on the operation of conventional turbines. Additionally, experimental measurements and data acquisition present researchers with challenges that have to do mostly with the high temperature exhaust of PGC and the high frequency of its operation. Nevertheless, numerical simulations can provide important insights into PGC exhaust flow and its interaction with turbine blades. In this paper, a rotating detonation combustor (RDC) and a row of nozzle guide vanes have been modeled based on the data from literature and an available experimental setup. Unsteady Reynolds-averaged Navier-Stokes (URANS) simulations were done for five guide vane configurations with different geometrical parameters to investigate the effect of solidity and blade type representing different outlet restrictions on the RDC exhaust flow. The results analyzed the connection between total pressure loss and the vanes solidity and thickness to chord ratio. It is observed that more than 57 of the upstream velocity angle fluctuation amplitude was damped by the vanes. Furthermore, the area reduction was found to be the significant driving factor for damping the velocity angle fluctuations, whether in the form of solidity or thickness on chord ratio increment. This RDC exhaust flow investigation is an important primary step from a turbomachinery standpoint, which provided details of blade behavior in such an unsteady flow field.

Item URL in elib:https://elib.dlr.de/147776/
Document Type:Article
Additional Information:061011
Title:Aerodynamic Investigation of Guide Vane Configurations Downstream a Rotating Detonation Combustor
Authors:
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Asli, MajidUNSPECIFIEDUNSPECIFIED
Stathopoulos, PanagiotisUNSPECIFIEDUNSPECIFIED
Paschereit, Christian OliverUNSPECIFIEDUNSPECIFIED
Date:2021
Journal or Publication Title:Journal of Engineering for Gas Turbines and Power
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:Yes
Volume:143
DOI :10.1115/1.4049188
Publisher:American Society of Mechanical Engineers (ASME)
ISSN:0742-4795
Status:Published
Keywords:Blades, Chords (Trusses), Combustion chambers, Damping, Exhaust systems, Explosions, Flow (Dynamics), Guide vanes, Pressure, Combustion, Simulation, Temperature, Fluctuations (Physics), Boundary-value problems, Turbomachinery, Mach number
HGF - Research field:Energy
HGF - Program:Materials and Technologies for the Energy Transition
HGF - Program Themes:High-Temperature Thermal Technologies
DLR - Research area:Energy
DLR - Program:E VS - Combustion Systems
DLR - Research theme (Project):E - Combustion and Power Plant Systems
Location: Cottbus
Institutes and Institutions:Institute of Low-Carbon Industrial Processes
Deposited By: Stathopoulos, Panagiotis
Deposited On:17 Dec 2021 17:12
Last Modified:21 Dec 2021 12:57

Repository Staff Only: item control page

Browse
Search
Help & Contact
Information
electronic library is running on EPrints 3.3.12
Copyright © 2008-2017 German Aerospace Center (DLR). All rights reserved.