Lean Blow-out Studies in a Swirl Stabilized Annular Gas Turbine Combustor

2015 ◽  
Vol 32 (2) ◽  
Author(s):  
R. K. Mishra ◽  
S. Kishore Kumar ◽  
Sunil Chandel
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Gas Turbine ◽  
Cfd Analysis ◽  
Gas Turbine Combustor ◽  
Tetrahedral Meshes ◽  
Annular Combustor ◽  
Unstructured Tetrahedral Meshes ◽  
Annular Gas Turbine Combustor

AbstractLean blow out characteristics in a swirl stabilized aero gas turbine combustor have been studied using computational fluid dynamics. For CFD analysis, a 22.5° sector of an annular combustor is modeled using unstructured tetrahedral meshes comprising 1.2 × 10

Effect of Fuel Particle Size on the Stability of Swirl Stabilized Flame in a Gas Turbine Combustor

2014 ◽  
Vol 0 (0) ◽  
Author(s):  
R. K. Mishra ◽  
S. Kishore Kumar ◽  
Sunil Chandel
Keyword(s):  
Fluid Dynamics ◽  
Particle Size ◽  
Gas Turbine ◽  
Combustion Stability ◽  
Fuel Particle ◽  
Gas Turbine Combustor ◽  
Tetrahedral Meshes ◽  
Annular Combustor ◽  
Unstructured Tetrahedral Meshes ◽  
The Stability

AbstractCombustion stability is examined in a swirl stabilized aero gas turbine combustor using computational fluid dynamics. A 22.5° sector of an annular combustor is modeled for the study. Unstructured tetrahedral meshes comprising 1.2 × 10

Prometheus: A Geometry-Centric Optimization System for Combustor Design

2014 ◽  
Author(s):  
Xu Zhang ◽  
David J. J. Toal ◽  
Neil W. Bressloff ◽  
Andy J. Keane ◽  
Frederic Witham ◽  
...  
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Gas Turbine ◽  
Computer Aided Design ◽  
Design System ◽  
Gas Turbine Combustor ◽  
Computer Aided ◽  
Computational Fluid Dynamics Cfd ◽  
Automatic Mesh ◽  
Aided Design

The following paper presents an overview of the Prometheus design system and its applications to gas turbine combustor design. Unlike a traditional “optimizer-centric” method, Prometheus aims to reduce both the level of workflow complexity and rework by taking a more “geometry-centric” approach to design optimization by shifting the control of script generation away from the optimization program to the computer aided design (CAD) package. Prometheus therefore enables significant geometry changes to be automatically reflected in all subsequent scripts necessary for the analysis of a combustor. Prometheus’ current capabilities include automatic fluid volume generation and aero-thermal and thermo-acoustic network generation as well as automatic mesh and computational fluid dynamics (CFD) script generation.

scholarly journals CFD Indications of Premix Flame Stability in a Gas Turbine Combustor

1996 ◽  
Author(s):  
J. Allan
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Gas Turbine ◽  
Heating Rate ◽  
Flame Stability ◽  
Cfd Model ◽  
Gas Turbine Combustor ◽  
Flow Models ◽  
Cold Flow ◽  
Primary Zone

An approach for predicting the relative tendency for weak extinction among similar gas turbine premix combustors is presented. The method involves analyzing CFD (computational fluid dynamics) solutions so as to evaluate the recirculating masses in the primary zone and the resulting potential heating rate of incoming fresh mixture. Results are illustrated for two combustor geometries which look similar but have very different behaviour. The comparison between the combustors agrees with test data when the CFD model incorporates a simulation of the flame. The inadequacy of cold flow models for the purpose is shown.

COMBUSTION AND NOX FORMATION MODELING USING EDDY RESOLVING TURBULENCE MODELS

2020 ◽  
Author(s):  
A. M. Sipatov ◽  
◽  
A. V. Khokhlov ◽  
T. V. Abramchuk ◽  
R. A. Zagitov ◽  
...  
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Numerical Methods ◽  
Gas Turbine ◽  
Turbulence Models ◽  
Gas Turbine Combustor ◽  
Nox Formation ◽  
Engine Design ◽  
Computational Fluid Dynamics Cfd ◽  
Physical Phenomena

The study of processes occurring in gas turbine combustor is an important part of engine design for achieving the required technical, operational, and environmental characteristics of the engine. During engine design process, both experimental and computational methods are used. The progress in numerical methods of modeling fourdimensional (space and time) physical phenomena and increasing of computation capacity allow application of complex computational fluid dynamics (CFD) methods for simulating such technical devices as the gas turbine combustor.

Calculation of the flow field and NO x emissions of a gas turbine combustor by a coarse computational fluid dynamics model

Energy ◽  
2012 ◽  
Vol 45 (1) ◽  
pp. 445-455 ◽  
Author(s):  
Paolo Gobbato ◽  
Massimo Masi ◽  
Andrea Toffolo ◽  
Andrea Lazzaretto ◽  
Giordano Tanzini
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Flow Field ◽  
Gas Turbine ◽  
Dynamics Model ◽  
Gas Turbine Combustor ◽  
Computational Fluid Dynamics Model

Analysis of an Airfoil Using a Transition and Turbulence Model

2016 ◽  
Vol 819 ◽  
pp. 356-360
Author(s):  
Mazharul Islam ◽  
Jiří Fürst ◽  
David Wood ◽  
Farid Nasir Ani
Keyword(s):  
Fluid Dynamics ◽  
Boundary Layer ◽  
Computational Fluid Dynamics ◽  
Kinetic Energy ◽  
Turbulence Model ◽  
Original Version ◽  
Transitional Region ◽  
Cfd Analysis ◽  
Computational Fluid Dynamics Cfd

In order to evaluate the performance of airfoils with computational fluid dynamics (CFD) tools, modelling of transitional region in the boundary layer is very critical. Currently, there are several classes of transition-based turbulence model which are based on different methods. Among these, the k-kL- ω, which is a three equation turbulence model, is one of the prominent ones which is based on the concept of laminar kinetic energy. This model is phenomenological and has several advantageous features. Over the years, different researchers have attempted to modify the original version which was proposed by Walter and Cokljat in 2008 to enrich the modelling capability. In this article, a modified form of k-kL-ω transitional turbulence model has been used with the help of OpenFOAM for an investigative CFD analysis of a NACA 4-digit airfoil at range of angles of attack.

A Fully Integrated Approach to Component Zooming Using Computational Fluid Dynamics

2004 ◽  
Vol 128 (3) ◽  
pp. 579-584 ◽  
Author(s):  
Vassilios Pachidis ◽  
Pericles Pilidis ◽  
Fabien Talhouarn ◽  
Anestis Kalfas ◽  
Ioannis Templalexis
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Gas Turbine ◽  
Engine Performance ◽  
Integrated Approach ◽  
High Fidelity ◽  
Performance Simulation ◽  
Fully Integrated ◽  
Engine Component ◽  
Simulation Strategy

Background . This study focuses on a simulation strategy that will allow the performance characteristics of an isolated gas turbine engine component, resolved from a detailed, high-fidelity analysis, to be transferred to an engine system analysis carried out at a lower level of resolution. This work will enable component-level, complex physical processes to be captured and analyzed in the context of the whole engine performance, at an affordable computing resource and time. Approach. The technique described in this paper utilizes an object-oriented, zero-dimensional (0D) gas turbine modeling and performance simulation system and a high-fidelity, three-dimensional (3D) computational fluid dynamics (CFD) component model. The work investigates relative changes in the simulated engine performance after coupling the 3D CFD component to the 0D engine analysis system. For the purposes of this preliminary investigation, the high-fidelity component communicates with the lower fidelity cycle via an iterative, semi-manual process for the determination of the correct operating point. This technique has the potential to become fully automated, can be applied to all engine components, and does not involve the generation of a component characteristic map. Results. This paper demonstrates the potentials of the “fully integrated” approach to component zooming by using a 3D CFD intake model of a high bypass ratio turbofan as a case study. The CFD model is based on the geometry of the intake of the CFM56-5B2 engine. The high-fidelity model can fully define the characteristic of the intake at several operating condition and is subsequently used in the 0D cycle analysis to provide a more accurate, physics-based estimate of intake performance (i.e., pressure recovery) and hence, engine performance, replacing the default, empirical values. A detailed comparison between the baseline engine performance (empirical pressure recovery) and the engine performance obtained after using the coupled, high-fidelity component is presented in this paper. The analysis carried out by this study demonstrates relative changes in the simulated engine performance larger than 1%. Conclusions. This investigation proves the value of the simulation strategy followed in this paper and completely justifies (i) the extra computational effort required for a more automatic link between the high-fidelity component and the 0D cycle, and (ii) the extra time and effort that is usually required to create and run a 3D CFD engine component, especially in those cases where more accurate, high-fidelity engine performance simulation is required.

scholarly journals Theoretical Analysis of Brush Seals Leakage Using Local Computational Fluid Dynamics Estimated Permeability Laws

2018 ◽  
Vol 140 (6) ◽  
Author(s):  
Lilas Deville ◽  
Mihai Arghir
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Reynolds Number ◽  
Principal Direction ◽  
Experimental Results ◽  
Leakage Flow ◽  
Cfd Analysis ◽  
Brush Seal ◽  
Brush Seals ◽  
Local Reynolds Number

Brush seals are a mature technology that has generated extensive experimental and theoretical work. Theoretical models range from simple correlations with experimental results to advanced numerical approaches coupling the bristles deformation with the flow in the brush. The present work follows this latter path. The bristles of the brush are deformed by the pressure applied by the flow, by the interference with the rotor and with the back plate. The bristles are modeled as linear beams but a nonlinear numerical algorithm deals with the interferences. The brush with its deformed bristles is then considered as an anisotropic porous medium for the leakage flow. Taking into account, the variation of the permeability with the local geometric and flow conditions represents the originality of the present work. The permeability following the principal directions of the bristles is estimated from computational fluid dynamics (CFD) calculations. A representative number of bristles are selected for each principal direction and the CFD analysis domain is delimited by periodicity and symmetry boundary conditions. The parameters of the CFD analysis are the local Reynolds number and the local porosity estimated from the distance between the bristles. The variations of the permeability are thus deduced for each principal direction and for Reynolds numbers and porosities characteristic for brush seal. The leakage flow rates predicted by the present approach are compared with experimental results from the literature. The results depict also the variations of the pressures, of the local Reynolds number, of the permeability, and of the porosity through the entire brush seal.

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