skip to main content

SciTech ConnectSciTech Connect

Title: Gas turbine engine

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.
Authors:
;
Publication Date:
OSTI Identifier:
1241316
Report Number(s):
9,279,334
13/542,674
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; 42 ENGINEERING