Advanced Combustor Designs Utilizing Inlet Swirl for High Acceleration of Gravity (G) Combustion

The recent incorporation of high g combustor designs in gas turbine engines at Spytek Aerospace has presented the need for the further optimization of the compressor/combustor interface (i.e. diffuser). Legacy combustor designs remove the inherent swirl out of the gas stream at the compressor exit, introducing aerodynamic losses and structural weight penalties. High g combustors utilize circumferential flows to decrease main combustor size ultimately allowing for the implementation of inter-turbine burners (ITB’s). Spytek Aerospace plans to utilize its operational ATG-2 high g combustor design as a basis for optimizing two ‘swirl-maintained’ diffuserless concepts. The major areas of study will include the efficient splitting of combustion/dilute flows directly into the combustor I.D. and flow lead–in into the entrainment region.