Skip to Content
Find More Like This
Return to Search

Gas turbine engine

United States Patent

March 8, 2016
View the Complete Patent at the US Patent & Trademark Office
A gas turbine engine with a compressor rotor having compressor impulse blades that delivers gas at supersonic conditions to a stator. The stator includes a one or more aerodynamic ducts that each have a converging portion and a diverging portion for deceleration of the selected gas to subsonic conditions and to deliver a high pressure oxidant containing gas to flameholders. The flameholders may be provided as trapped vortex combustors, for combustion of a fuel to produce hot pressurized combustion gases. The hot pressurized combustion gases are choked before passing out of an aerodynamic duct to a turbine. Work is recovered in a turbine by expanding the combustion gases through impulse blades. By balancing the axial loading on compressor impulse blades and turbine impulse blades, asymmetrical thrust is minimized or avoided.
Lawlor; Shawn P. (Bellevue, WA), Roberts, II; William Byron (Wellington, NV)
Dresser-Rand Company (Olean, NY)
13/ 542,674
July 6, 2012
STATEMENT OF GOVERNMENT INTEREST This invention was made with United States Government support under Contract No. DE-FE0000493 awarded by the United States Department of Energy. The United States Government has certain rights in the invention.