In a gas turbine, natural gas (methane) and stoichiometric air flow into the combustion chamber at 1000
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In a gas turbine, natural gas (methane) and stoichiometric air flow into the combustion chamber at 1000 kPa, 500 K. Secondary air (see Fig. P13.51), also at 1000 kPa, 500 K, is added right after the combustion to result in a product mixture temperature of 1500 K. Find the air–fuel ratio mass basis for the primary reactant flow and the ratio of the secondary air to the primary air (mass flow rates ratio).
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The airfuel ratio for the primary reactant flow and the ratio of secondary air to primary air can be ...View the full answer
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Related Book For 
Fundamentals Of Thermodynamics
ISBN: 9781118131992
8th Edition
Authors: Claus Borgnakke, Richard E. Sonntag
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