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Title: Gas turbine engine with supersonic compressor

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.
Authors:
;
Publication Date:
OSTI Identifier:
1223700
Report Number(s):
9,163,521
13/542,669
DOE Contract Number:
FE0000493
Resource Type:
Patent
Resource Relation:
Patent File Date: 2012 Jul 06
Research Org:
Dresser-Rand Company, Olean, NY (United States)
Sponsoring Org:
USDOE
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS