"A high fuel-air ratio combustor/turbine computational model (computer code) is proposed for development in this SBIR project. The proposed computational model will address fuel-air ratio and temperature non-uniformities and fluctuations at the combustorand 1st stage high pressure turbine exit… More

A high fuel-air ratio combustor computational model (computer code) is proposed for development in this SBIR project. The proposed computational model will address fuel-air ratio and temperature non-uniformities and fluctuations at the combustor and 1ststage high pressure turbine exit planes based… More

An innovative ariblast-based single-lip fuel injector with piloted fuel for advanced military gas turbine combustors is proposed for development in this SBIR. The proposed innovative fuel injector design concept will significantly improve the mixing performance of fuel and air in the vicinity of the… More

An innovative piloted airblast fuel injector concept called "SAWBLAST" is proposed for development. Phase-I work demonstrated the potential of the proposed SAWBLAST concept through detailed CFD analyses for improved performance over existing piloted aiblast fuel injectors. Phase-II efforts will… More

A transient performance PDE code is proposed for development and demonstration in this SBIR project. The proposed formulation methodology for the performance code is based upon a zero-order time-marching methodology to compute PDE properties as a function of PDE cycle time. The proposed PDE code… More

A new unique reduced order heat release model is proposed for development in this SBIR. The proposed reduced order heat release model is derived based on the prevailing local flow conditions and it expresses the complex relationship between the fluctuating heat release and the fluctuating local… More

A novel damping model to damp acosutic pressures in gas turbine afterburners is proposed for development and validation in this SBIR project. The proposed model will account for as many of the physical phenomena present in the afterburenr as possible which will include grazing, bias, and mean flows,… More

An integrated Pulse Detonation Engine (PDE)and Airframe Transient Cycle Analysis and Airframe Performance (PDE-CAASP) code is proposed for development based upon the successful development of a PDE Transient Cycle Analysis Code during Phase-I. The Integrated PDE/Airframe code will include flight… More

A new inovative passive mxing enhancer design concept is proposed for development and implementation in either turbine engine augmentor and/or main combustor. The design concept utilzes certain geometrical features to create and induce significant amounts of axial vorticity that leads to enhanced… More

A Three-Dimensional Damping (TDD) Model and an Alpha V1.1 computer code successfully developed and demonstrated in Phase-I will be further developed to include additional important processes such as unsteady heat release and sheared flows. In addition, aero-acoustics and screech tests will be… More

A novel multi-lobe flame holder design concept was designed, fabricated, and tested under high vitiated air flow temperature conditions for Light-Off (LO)and Lean Blow Out (LBO) performance. The new novel flame holder concept clearly demonstrated an improved LO/LBO performance pver the conventional… More