Experimental and Numerical Investigation of Non-reacting Flow …
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Fig. 2 Gas turbine combustor experimental setup
3 Experimental Study
The pressure loss across the combustor is measured using pitot tubes connected to
a U-tube water column manometer (Fig. 2). The compressed air at 5 bar is passed
through the combustor. The air mass flow rate is determined using rotameters.
4 Numerical Study
The numerical simulation is performed to predict the detailed flow field characteristics of the combustor. Here, the three-dimensional models of 90° sector are taken for
analysis. The combustor flame tube wall thickness is assumed as zero, to minimize
the complexness of the geometry. The turbulence modeling has been done using k-ε
RNG model. The combustor inlet is specified as a velocity boundary. The outlet of
the geometry is specified as a pressure outlet boundary. The inlet and outlet of snot,
swirler, primary ports, secondary ports and dilution ports are specified as a interior.
The sectional plane of the sector model is specified as a periodic boundary. The
remaining faces of the combustor model are specified as a wall. The computational
domain taken in the present study is given in Fig. 3.
Fig. 3 90° sector can combustor computational domain
133
Fig. 2 Gas turbine combustor experimental setup
3 Experimental Study
The pressure loss across the combustor is measured using pitot tubes connected to
a U-tube water column manometer (Fig. 2). The compressed air at 5 bar is passed
through the combustor. The air mass flow rate is determined using rotameters.
4 Numerical Study
The numerical simulation is performed to predict the detailed flow field characteristics of the combustor. Here, the three-dimensional models of 90° sector are taken for
analysis. The combustor flame tube wall thickness is assumed as zero, to minimize
the complexness of the geometry. The turbulence modeling has been done using k-ε
RNG model. The combustor inlet is specified as a velocity boundary. The outlet of
the geometry is specified as a pressure outlet boundary. The inlet and outlet of snot,
swirler, primary ports, secondary ports and dilution ports are specified as a interior.
The sectional plane of the sector model is specified as a periodic boundary. The
remaining faces of the combustor model are specified as a wall. The computational
domain taken in the present study is given in Fig. 3.
Fig. 3 90° sector can combustor computational domain