Patent ID: 8978389
Filing Date: 2015-03-17
Classification: F01D,F02C,F05D

Abstract:
1. A gas turbine engine, comprising: a turbine comprising radial inflow impellor blades; and an array of transition combustor assemblies arranged circumferentially about the radial inflow impellor blades and comprising inner surfaces that are adjacent to combustion gases, wherein the inner surfaces of the array are configured to accelerate and orient, for delivery directly onto the radial inflow impellor blades, a plurality of discrete flows of the combustion gases; wherein the array inner surfaces define respective combustion gas flow axes, wherein each combustion gas flow axis is straight from a point of ignition until reaching the radial inflow impellor blades, and wherein each combustion gas flow axis intersects a unique location on a circumference defined by a sweep of the radial inflow impellor blades.