scholarly journals Numerical modeling of steady and unsteady combustion regimes of methane-air mixture in research combustion chamber with step

2019 ◽  
Vol 1261 ◽  
pp. 012020
Author(s):  
A B Lebedev ◽  
K Ya Yakubovskii ◽  
P D Toktaliev
Keyword(s):  
Numerical Modeling ◽  
Combustion Chamber ◽  
Unsteady Combustion ◽  
Combustion Regimes

scholarly journals Investigation of unsteady combustion of methane-air flame in a model combustion chamber with swirling flow

2021 ◽  
Vol 2119 (1) ◽  
pp. 012015
Author(s):  
A S Lobasov
Keyword(s):  
Combustion Chamber ◽  
Large Scale ◽  
Recirculation Zone ◽  
Swirling Flow ◽  
Heating Temperature ◽  
Combustion Products ◽  
Flow Dynamics ◽  
Unsteady Combustion ◽  
Stereoscopic Piv ◽  
Large Scale Vortex

Abstract The present paper reports on the investigation of unsteady combustion of a methane-air mixture, including combustion at increased pressure in the combustion chamber and increased temperature of mixture heating for a model gas-turbine swirl burner based on a design by Turbomeca. To measure the velocity and OH fluorescence fields in the flows a combination of stereoscopic PIV and acetone PLIF systems is used. In all cases, the flow dynamics is associated with the movement of large-scale vortex structures in the inner and outer mixing layers and the flow structure corresponds to a swirling jet with a central recirculation zone containing combustion products. An increase in the heating temperature of the mixture and pressure in the combustion chamber leads to a periodic partial separation of the flame from the model swirl nozzle. However, the flow of fuel through the central channel will stabilize the flame.

Combustion chamber design and reaction modeling for aero turbo-shaft engine

2018 ◽  
Vol 91 (1) ◽  
pp. 94-111
Author(s):  
Raja Marudhappan ◽  
Chandrasekhar Udayagiri ◽  
Koni Hemachandra Reddy
Keyword(s):  
Numerical Modeling ◽  
Combustion Chamber ◽  
Gas Turbine ◽  
Diffusion Flame ◽  
Internal Flow ◽  
Content Type ◽  
Combustion Modeling ◽  
Flame Combustion ◽  
Aero Engine ◽  
Exit Temperature

Purpose The purpose of this paper is to formulate a structured approach to design an annular diffusion flame combustion chamber for use in the development of a 1,400 kW range aero turbo shaft engine. The purpose is extended to perform numerical combustion modeling by solving transient Favre Averaged Navier Stokes equations using realizable two equation k-e turbulence model and Discrete Ordinate radiation model. The presumed shape β-Probability Density Function (β-PDF) is used for turbulence chemistry interaction. The experiments are conducted on the real engine to validate the combustion chamber performance. Design/methodology/approach The combustor geometry is designed using the reference area method and semi-empirical correlations. The three dimensional combustor model is made using a commercial software. The numerical modeling of the combustion process is performed by following Eulerian approach. The functional testing of combustor was conducted to evaluate the performance. Findings The results obtained by the numerical modeling provide a detailed understanding of the combustor internal flow dynamics. The transient flame structures and streamline plots are presented. The velocity profiles obtained at different locations along the combustor by numerical modeling mostly go in-line with the previously published research works. The combustor exit temperature obtained by numerical modeling and experiment are found to be within the acceptable limit. These results form the basis of understanding the design procedure and opens-up avenues for further developments. Research limitations/implications Internal flow and combustion dynamics obtained from numerical simulation are not experimented owing to non-availability of adequate research facilities. Practical implications This study contributes toward the understanding of basic procedures and firsthand experience in the design aspects of combustors for aero-engine applications. This work also highlights one of the efficient, faster and economical aero gas turbine annular diffusion flame combustion chamber design and development. Originality/value The main novelty in this work is the incorporation of scoops in the dilution zone of the numerical model of combustion chamber to augment the effectiveness of cooling of combustion products to obtain the desired combustor exit temperature. The use of polyhedral cells for computational domain discretization in combustion modeling for aero engine application helps in achieving faster convergence and reliable predictions. The methodology and procedures presented in this work provide a basic understanding of the design aspects to the beginners working in the gas turbine combustors particularly meant for turbo shaft engines applications.

scholarly journals Development of combustion chamber of a reference calorimeter with numerical analysis

ACTA IMEKO ◽  
2015 ◽  
Vol 4 (4) ◽  
pp. 26
Author(s):  
Jose Eli Eduardo Gonzalez-Duran ◽  
Alejandro Estrada-Baltazar ◽  
Leonel Lira-Cortes
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Numerical Modeling ◽  
Numerical Analysis ◽  
Combustion Chamber ◽  
Calorific Value ◽  
Combustion Chambers ◽  
Isoperibolic Calorimeter ◽  
Computational Fluid Dynamics Cfd ◽  
Superior Calorific Value

<p class="Abstract">The present work focuses on the numerical modeling of two combustion chambers to be used inside an isoperibolic calorimeter to measure the Superior Calorific Value (SCV) from natural gas. This work shows performance of both chambers working under isoperibolic principle, through simulations based on Computational Fluid Dynamics (CFD). The aim of the work is expose the performance of chamber combustion published in the literature versus another one proposed in this work, and show how was improved the performance of the chamber which proposed in this work by changing the geometry. And it is checked by analyzing temperature of burned gases at exit of combustion chamber.</p>

Numerical Modeling Of The Ignition Initiation In The Scramjet Combustion Chamber Via Detonation

2016 ◽  
Vol 11 (4) ◽  
pp. 33-44
Author(s):  
Igor Bedarev ◽  
Valentin Temerbekov ◽  
Aleksandr Fedorov ◽  
Kristina Rylova
Keyword(s):  
Numerical Modeling ◽  
Detonation Wave ◽  
Combustion Chamber ◽  
Wave Interaction ◽  
Kinetic Scheme ◽  
Reacting Flow ◽  
Mixing Process ◽  
Detonation Tube ◽  
Cellular Detonation ◽  
Air Mixing

The paper studies of the cellular detonation wave interaction with supersonic reacting flow in the scramjet combustion chamber. Comparing the flow fields for the details and the reduced chemical kinetics models is allowed verifying the acceptability of the proposed simplified kinetic scheme. The possibility of using pulsating detonation for the ignition intensification in the scramjet combustion chamber is shown. Calculation of the detonation wave interaction with nonpremixed hydrogenair mixture is made. The ability to influence on the hydrogen-air mixing process by means of detonation tube is detected. The effect of tube sizes to intensification of hydrogen air mixing in the flow at channel with a cavity is calculated.

scholarly journals Studying unsteady combustion processes that occur in an annular combustion chamber of a gas turbine engine

2021 ◽  
Vol 1891 (1) ◽  
pp. 012027
Author(s):  
M.Hernandez Morales ◽  
I.A. Zubrilin ◽  
N.I. Gurakov ◽  
O.V. Kolomzarov ◽  
G.M. Makaryants ◽  
...  
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Unsteady Combustion ◽  
Turbine Engine ◽  
Combustion Processes
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