Pressure-Based Finite Volume Unstructured Solution - Adaptive CFD Code for Heat Transfer and Pollutant Dispersal

Period of Performance: 03/25/1997 - 03/25/1999


Phase 2 SBIR

Recipient Firm

CFD Research Corp.
701 McMillian Way NW Suite D
Huntsville, AL 35806
Principal Investigator

Research Topics


High combustor inlet pressure and temperature required to meet aggressive IHPTET Phase III goals for the JTAGG program put critical demands on the fuel injection and primary zone aerodynamic design. An innovative Rapid-Mix fuel nozzle that quickly mixes fuel with combustor front-end airflow in order to minimize heat loads to the combustor liner and reduce temperature pattern factor will be designed, developed and demonstrated in this SBIR project. The fuel nozzle includes features that optimize fuel-air distribution, maintain operability, prevent fuel passage coking, and minimize cost and complexity. In Phase I, fuel nozzle feasibility was demonstrated by ignition and lean blow-out experimental tests and by CFD calculations showing uniform fuel-air distribution at full power. In Phase II, the Rapid-Mix fuel nozzle will be applied to the high-temperature-rise JTAGG III combustor through a collaborative effort between CFD Research Corporation (CFDRC) , AlliedSignal Engines, and Delavan, Inc. The fuel nozzle design will be further optimized through CFD analyses and prototype nozzle tests at atmospheric pressure. A series of full scale high pressure tests will then be performed using a combustor rig at AlliedSignal. In Phase III of this SBIR, the Rapid-Mix fuel nozzle will proceed to further development and testing in the JTAGG demonstrator engine. If successful, the nozzle will play a critical role in meeting JTAGG and IHPTET Phase III goals. The final product of this project will be a Rapid-Mix fuel injector capable of durable operation for IHPTET Phase III combustor inlet conditions in the AlliedSignal JTAGG III combustor. The product is therefore of significant interest to the U.S Army and DoD and to manufacturers of gas turbine engines.