This paper presents the design and initial development of a conventional combustion system to meet the specific requirements of an Intercooled Recuperated (ICR) Gas Turbine for Marine Propulsion use.

The ICR cycle offers considerable benefit in terms of fuel consumption over a wide power range, however, it presents the combustion designer with unique requirements including, but not limited to, air-to-fuel ratio (AFR) operating range, combustor inlet temperature range and combustion aerodynamics, whilst achieving acceptable combustion parameters such as ignition envelope, exit temperature traverse, smoke and emissions, component durability and integrity. The design and development of solutions to these challenges considered and chosen for the WR-21 are discussed, and results of early rig and engine testing outlined.

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