 Open Access
 Total Downloads : 1851
 Authors : P. Muthukumar, S. R. Balakrishnan
 Paper ID : IJERTV2IS60013
 Volume & Issue : Volume 02, Issue 06 (June 2013)
 Published (First Online): 01062013
 ISSN (Online) : 22780181
 Publisher Name : IJERT
 License: This work is licensed under a Creative Commons Attribution 4.0 International License
CFD Analysis of recirculating flows induced by Axial Swirler
P.Muthukumar1, S.R.Balakrishnan2
PG scholar1, Director/H.O.D2
1, 2, Department of Aeronautical Engineering, Nehru institute of engineering and technology
Abstract
The main objective of this paper is to investigate the flow through axial Swirler. Air swirler can control the combustor performance by assisting in the fuelair mixing process and producing recirculation region which act as flame holders and influences residence time. Such analyses are necessary for predictions and optimization of real gas combustors Thus, proper selection of a swirler is needed to enhance combustor performance and to reduce NOx emissions. Four different axial air swirlers were used based on their vane angles i.e., 30, 40, 50, 60.The model geometry has been created using CATIA Software, meshing and analysis were carried out in Ansys Fluent 13.The K and RSM (Reynolds stress model) turbulence model are to be used to model the turbulence and results were compared for the effect of swirlers and mass flow rate on the flow field.
Keywords Combustor, Axial swirler, Turbulence, recirculation, Combustion efficiency

Introduction
The combustion chamber is a turboengine component to which fuel supplied by feeding nozzles, is mixed with air flow coming from the compressor, after the fuel has been injected into the flow, the flow will enter the flame region. It does this with quite a high velocity. To make sure the flame isnt blown away, flow reversal can be applied in the primary zone. This causes the flow to reverse direction. The best way to reverse the flow is to swirl it. This is done using swirlers. The two most important types of swirlers are axial swirlers and radial swirlers .The most important advantage of flow reversal, is that the flow speed varies a lot. So there will be a point at which the airflow velocity matches the flame speed. (The flame speed is the speed, relative to the airflow, at which the flame can move.) This is the point where the flame anchors.

Air Swirler
A basic requirement of all gas turbine engines is that the flame stay lighted over a wide range of operating conditions. This is especially for aircraft
combustor which has to cope with the adverse condition of low pressure and temperature, occasionally the ingestion of rain or ice. The primary zone airflow pattern is of primary importance to flame stability. Many different type of air flow pattern are employed, but one feature common to all is the creation of toroidal flow reversal that entrains and recirculates a portion of the hot combustion product to mix with the incoming air and fuel. These vortices are continually refreshed by air admitted through holes pierced in the linear walls, supplemented in most cases by air flowing through swirler.
Fig. 1 Recirculation zone created by air swirler

Recirculation Zone
Swirl develops the radial pressure gradient and axial pressure gradient in the flow, these pressure gradient are responsible for the formation of the recirculation zone. The central toroidal recirculation zone (CTRZ) occurs due to the swirl strength. Central recirculation zone (CTRZ) is in the form of toroidal vortex .Low pressure region is created in the downstream of the combustor. In that region centrifugal force is created, this pushes the flow away from the centre axis. Because of this reason the recirculation zone is created. Efficiency of swirl flow create pressure drop along the downstream of the combustor reappears as kinetic energy of the swirling jet flow. Recirculation zone is created to provide a low velocity region, which is used to anchor the flame.
Fig. 2 Recirculation zone induced by swirler.

Swirl Flow
Swirling jets were used for stabilization and control of flame and to achieve high intensity combustion. The common method of generating swirl is by using by using angled vanes in the passage of air. Most conventional combustor employs the axial flow type swirlers. The swirler vanes were usually flat for easy of manufacture, but curved vane was sometimes used for their better aerodynamics properties

Swirl flow generation methods
Swirl flows are generated by three principal methods:

Tangential entry (axialplustangential entry swirl generator)

Guided vanes (Swirl vane pack or Swirler)

Direct rotation (rotating pipe)


Swirl Flow Characterisation
Swirl flow is a main flow produced by air swirled by the swirler. Swirl is to decrease the velocity gradient causes rapid decay of the velocity in the flow field with increase of swirl flow. Swirling flow induces a very high turbulent recirculation zone. Swirl flow has a centrifugal force to accelerate the flow. Air is introduced tangentially into the chamber, forced to change its path which is due to the formation of recirculation zone. Strength of the flow is dependent of swirler vane angle and supplied air pressure. One of the effective ways of inducing flow recirculation is to fit swirler in the dome around the fuel injector. Vortex breakdown causes recirculation in the core region .When the amount of rotation imparted to the flow is high. The swirl component produce strong shear, high turbulence and rapid mixing thus having control over stability, intensity of the combustion, size and shape of the flame region. Swirl has a better aerodynamic properties, Swirl can promotes high combustion efficiency, easy ignition, recirculation zone, residence time stability and blow off limits.


Computational Method
In this study, to understand the effect of swirl angle on the flow field produced by axial swirler, four different configuration of swirler with varying swirl angle of 30o, 40o, 50o, and 60o were taken. In all the cases of swirler configuration constant pressure drop of
0.5 bars were maintained. Turbulence is modeled using both RSM and K turbulence model, and results were compared with each other. To predict the effect of inlet Reynolds number on the flow field, four different cases of swirler were selected with of Reynolds number (24700, 62800, 125000, 190000 and 250000). In this part also both RSM and K turbulence models were used and the results were compared.

Swirler Dimensions
Parameters of interest to axial swirler designers are depicted by below. They include:
Vane angle v – 30Â°, 40Â°, 50Â°, 60Â° Inner hub radius Rhub 10mm Outer swirler radius Rsw 30mm Vane thickness tv, 1.5mm
Vane length cv,5mm Number of vanes nv 8
Fig 3 Swirler Dimensions

Computational Domain Details
The geometry considered for the study consists of an inlet pipe of length 100mm and of diameter 30mm, swirler is fixed with inlet pipe. Swirler consists of 8 vanes of thickness 1.5mm and height of 8mm. All the eight vanes are symmetrical about center axis. A divergent extension is provided at the swirler exit to support the strength of tangential velocity produced by swirler. A long circular duct consists of diameter 25mm and length is about 600mm fixed with divergent extension, a convergent type of nozzle is attached to prevent the reversal of flow from the atmosphere into the domain.

Geometry and Grid details
The three dimensional flow regions along with swirler with appropriate swirl angle was modelled using software CATIA. Three dimensional unstructured grids was generated using tetrahedral mesh in Ansys work bench. The grid cells were refined in the critial regions, like swirler inlet and exit, in anticipation of high velocity and pressure gradient. The solutions were predicted by using Ansys Fluent 13.


Assumptions and Boundary conditions
The assumptions and boundary conditions are essential and is a critical part in modelling a flow accurately. In this the flow is assumed to be steady, isothermal and turbulent.
Inlet
At the inlet of the computational region, the inlet boundary condition is defined as mass flow inlet.
Condition
Value
Flow regime
Subsonic
Pressure
1.5 bar
Flow direction
Normal to boundary
Temperature
300 K
Hydraulic Diameter
26mm
Turbulence Intensity
10%
Outlet
Table 2.Inlet Boundary Condition
Fig 4 Computational grid of axial swirler
Fig.5 Computational grid of domain
Swirler angle
Nodes
Elements
30o
5952
26418
40o
5963
26437
50o
5923
26057
60o
6054
26450
Table 1. Swirler angle with corresponding nodes and elements
The exit boundary is defined as pressure outlet .For the inlet and outlet constant pressure drop of 0.5 has been maintained. The details of the outlet boundary condition are provided in Table 3
Condition
Value
Flow regime
Subsonic
Outlet pressure
1 bar
Hydraulic Diameter
35.68mm
Turbulence Intensity
15%
Table 3.Outlet boundary condition
Mass Flow rate
For mass flow rate across the different cases of swirler mass flow inlet boundary condition was chosen at inlet with varying mass flow values of 0.01, 0.025, 0.05, 0.075 and 0.1 kg/s was given to vary the inlet Reynolds number.
Mass flow rate (kg/s)
Reynolds number (Re)
0.010
24700
0.025
62800
0.050
125000
0.075
190000
0.100
250000
Table 4 Reynolds number effect on mass flow rate

Effect of Reynolds number on axial velocity
Axial velocity distributions of all five cases of Reynolds number along the axial direction for both the K and RSM model were shown in the figure 6 and 7 respectively, it indicates that reverse flow axial velocity within the recirculation increases with increase in Reynolds number. Higher Reynolds number cases producing stronger recirculation zone with increase in size. But continuous increase in inlet velocity will increase the size CTRZ, after some limit it will form open recirculation zone, which may not able to hold the flame. This maximum velocity limit is called stability limit of that particular swirler. Exit axial velocity predicted by RSM model was almost constant. But exit axial velocity predicted by K model was not constant.
Fig. 6 Reynolds number effects on axial velocity along axial distance for K model.
Fig.7 Reynolds number effects on axial velocity along axial distance for RSM method.

Effect of Reynolds number on Turbulence Intensity
Turbulent intensity distributions of all five cases of Reynolds number along the axial direction for both the K and RSM model were shown in the figure 8 and 9 respectively; it indicates that turbulent intensity with in the CTRZ increases with increase in Reynolds number. With increase in inlet Reynolds number the inlet kinetic energy increases. This increase in kinetic energy produces higher turbulence in the flow. So intensity of turbulence increases with increase in inlet Reynolds number. RSM model gives uniform profile for different Reynolds number case. But K model gives different forms of profile.
Fig.8 Reynolds number effects on turbulence intensity for K method.
Fig. 9 Reynolds number effects on turbulence intensity for RSM method.

Conclusions
Complete investigations of various factors on the performance of flow through axial swirler with different swirl angle configuration were studied. The change in swirl angle had a large effect on the flow field. For a various values of Swirl angle at constant pressure drop across the swirler, variation in the mass flow rate, velocity variation and intensity of turbulence inside the reverse flow region were predicted by using the turbulence model RSM and K. The effect of Reynolds number (24700, 62800, 125000, 190000 and 250000) on
the flow field for single swirler was predicted using the turbulence model RSM and K. It was observed that increase in Reynolds number has a significant effect on the flow field, and the results of 30Â° RSM model were better than K at higher Reynolds number cases.

References

Beer and Chigier, N.A., Combustion aerodynamics,
Applied science pub., London 1972

David G.Lilley Modeling of combustor swirl flows, ACTA Astronautical, Volume 1, PP.1129 1147.November 1974

R.ECharles, J.I.Emdee, L.J.Muzio, G.S.Samuelsen
,The effect of inlet Conditions on the performance and flow field structure of a nonpremixed swirl stabilized distributed reaction, International journal of combustion, 1986.pp.14551461.

J.L xia,B.L,Smith,A.C Benim,J.Schmidli and G.Yadigaroglu ,Effect of inlet and outlet boundary conditions on swirling flows, Computers and fluids,Volume26,No.8,1997,PP.81182

Aldo Coghe, Giulio Solero, Gianfranco Scribano, Recirculation phenomena natural gas swirl combustor, Journal of thermal and fluid science,2004,PP.709714.

Ying Huang and Vigor Yang effect of swirl on combustion dynamics in a lean premixed swirl stabilized combustor, combustion institution, 2005, PP.17751782.

S.Bharat Krishna and V.Ganesan CFD Analysis of flow through vane swirler (1) journalMC, Volume 86, April 2005.

R.Palm, S.Grundmann, M.Weismuller, S.Saric, S.Jakirlic, C.Tropea Experimental characteristics and modeling of inflow condition for a gas turbine swirl combustor, International journal of heat and fluid flow

A.Panduranga Reddy, R.I.Sujith, and S.R.Chakravarthy Swirler flow field characteristics in a sudden expansion combustor geometry, Journal of propulsion and power, Volume 2. No.4, July August 2006.

R.Thundil Karuppa Raj and V.Ganesan Experimental study of recirculation flows induced by vane swirler, Indian journal engineering and
materials sciences, Volume 16, FebruarVyol2. 02 0Is6su,PeP6, June – 2013
.1422

Saravanamuttoo, H.I.H., Rogers, G.F.C., & Cohen,
H. 2001. Gas Turbine Theory. 5edn. New York: Prentice Hall.

Dodds, W.J., & Bahr, D.W. 1990. Combustion System Design. Chap. 4, pages 343476 of: Mellor,
A.M. (ed). Design of Modern Turbine Combustors. New York: Academic Press.