A Simple Combustor System for a Small Gas Turbine Engine

The design of a simple, low cost annular combustor, based on a unique aerodynamic mixing concept, is described in terms of its mechanical simplicity, versatility in the use of different fuel injection systems, and its demonstrated performance characteristics. The design, called a circumferentially stirred combustor, incorporates a primary zone flame stabilization method which results in an inexpensive shape for the combustor liner and a reduction of the number of fuel injectors to about one half that normally used for a swirl stabilized annular primary zone design. This circumferentially stirred combustor design has been applied to LTS 101 helicopter engine models now in production and to advanced shaft and fan engines in the STAGG, ATDE and QCGAT engine programs.