Abstract: A gas turbine engine includes a compressor section and turbine section. The gas turbine engine of the present disclosure is a relatively small gas turbine engine, configured to generate less than 2,000 horsepower during peak operations. The compressor section defines an overall compressor ratio of at least 15:1 in order to increase in overall efficiency of the gas turbine engine.

Abstract: According to one aspect of the exemplary embodiment, a turbomachine includes a compressor portion, a combustor fluidly connected to the compressor portion, and a turbine portion fluidly connected to the combustor portion and mechanically coupled to the compressor portion. The combustor portion is configured and disposed to burn ash-bearing fuel oils. The turbine portion includes a first stage having a first plurality of airfoils, and a second stage having a second plurality of airfoils. The first plurality of airfoils have a trailing edge discharge member. The second plurality of airfoils is clocked circumferentially relative to the first plurality of airfoils. The first plurality of airfoils are configured and disposed to direct an ash depleted flow upon corresponding adjacent ones of the second plurality of airfoils.