Advanced 2-spool turboprop engine

Abstract

A low cost, high power density, low emissions general aviation turbine engine (GATE) with improved fuel economy over current engines. Ideally suited for 50 to 500 shaft horsepower (SHP) range aircraft applications such as GA, UAS, UAS, air taxi, helicopters and commercial markets. The engine design features with centrifugal compressor and radial turbine rotors has a high-end practical limit of ˜800 (SHP). The new turboprop incorporates 2 non-concentric spools aero-thermal—pressure coupled wherein staged compressor rotors lend to a simple engine design, optimized high overall engine pressure ratio (OPR) and low specific fuel consumption (SFC). An integral starter-generator system further simplifies the engine design and offers high electrical output power capability for auxiliary power requirements. A 2-stage low emissions combustor with fuel-air premix chambers is incorporated lending to stable combustion at any engine spool speed/power requirement, further fuel optimization and use of a low cost simple fixed pitch propeller. Some other highlights include: any fuel or mixture thereof, TBO greater than piston or other turbine engines, less maintenance costs, oil/filter change at ˜15000 hrs. and other inherent advantages of a gas turbine engine. Of the two spools that make up this turboprop engine, one is the High Pressure (HP) spool that is part of the gas generator using combustor hot gases to power the integral HP turbine rotor, HP compressor and high-speed alternator starter—generator. The other engine spool is the Low-Pressure (LP) spool that receives the HP turbine exhaust heat energy to power the integral LP compressor rotor, LP turbine rotor, integrated gearbox with resultant output shaft horsepower. This invention represents the most advanced engine for general aviation since Charles Edward Taylor's engine powered the Wright Brothers first aircraft-controlled powered flight Dec. 17, 1903.