portions of the overall structure of the micro turbine engine using layers of substructure that are stacked along a primary direction and each layer of substructure is formed geometrically but not necessarily manufactured by extruding one or more two dimensional patterns along the primary stacking direction the term u201c extruding u201d is being used herein for simplicity to represent the projection of a contour profile outline etc of a component feature along as axis in particular by implementing this design methodology the specific layered geometry allows a designer to build parts that are manufactured using conventional machining methods or metal forming methods including but not limited to 2 5 axis cnc milling laser cutting waterjet cutting electrical discharge machining etc fig5 shows a diagram of different substructure layers that form the overall structure of one embodiment of the micro turbine engine in this particular embodiment cold air flows into the engine from the top through the engine air inlet indicated by component 6 gets compressed by the compressor labeled by component 1 becomes heated in the combustor labeled by component 2 and then turns the turbine rotor labeled by component 3 before exiting the engine through the exhaust indicated by component 7 one benefit of using this design methodology is significantly reduced manufacturing cost from a combination of using common materials as well as cheaper manufacturing methods however in implementing simple contour geometries for the engine components in the present invention the efficiency of the engine in.