Gas Turbine Reverse-Flow Combustor Research

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Gas Turbine Reverse-Flow Combustor Research Objective Investigate the aerothermal behavior in the dump diffuser and the revered-flow combustor with and without jet impingement sheath to achieve more effective cooling and reduced aerodynamic losses. Reverse-flow Combustor Advantages • Reverse-flow combustor can reduce the length of the gas turbine and make the transportation much easier. • Reduced length will allow single shaft sitting on two bearings instead of three. This will reduce the vibration and maintenance GE 7FA Gas Turbine problems. • The reverse-flow layout effectively uses the air flow to cool down the combustor liner and the transition piece as a counterflow heat exchanging process. The absorbed heat by the air is returned back to the system. In other words, the reverse- flow combustor cooling process is actually a preheating process for the air. • The reverse-flow process also allow warmer air to serve as the dilution air to control the NOx formation instead of using other energy to preheat the dilution air or use cold air which could 1/7th sector of dump diffuser-combustor quench the flame and produce CO. • Similarly, the preheat air also serves as wall jet film cooling on inside of the combustor liner. Penetration of air jet into the combustion chamber can enhance air-fuel mixing to achieve more effective and uniform combustion and help reduce NOx formation near the wall. Mid-plane velocity vector Pressure contour without sheath Pathlines colored by pressure End-view of velocity vector Combustor employing outer sheath Mid-plane velocity vector Cut-away view of velocity vectors And pressure contour with impinging jet cooling holes and pressure contour and pressure contour in the top hat of combustor .

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