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Gas turbine engine with supersonic compressor

United States Patent

October 20, 2015
View the Complete Patent at the US Patent & Trademark Office
A gas turbine engine having a compressor section using blades on a rotor to deliver a gas at supersonic conditions to a stator. The stator includes one or more of aerodynamic ducts that have converging and diverging portions for deceleration of the gas to subsonic conditions and to deliver a high pressure gas to combustors. The aerodynamic ducts include structures for changing the effective contraction ratio to enable starting even when designed for high pressure ratios, and structures for boundary layer control. In an embodiment, aerodynamic ducts are provided having an aspect ratio of two to one (2:1) or more, when viewed in cross-section orthogonal to flow direction at an entrance to the aerodynamic duct.
Roberts, II; William Byron (Wellington, NV), Lawlor; Shawn P. (Bellevue, WA)
Dresser-Rand Company (Olean, NY)
13/ 542,669
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.