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Title: Gas turbine engine

Abstract

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.

Inventors:
;
Issue Date:
Research Org.:
Dresser-Rand Company, Olean, NY (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1241316
Patent Number(s):
9,279,334
Application Number:
13/542,674
Assignee:
Dresser-Rand Company (Olean, NY)
DOE Contract Number:  
FE0000493
Resource Type:
Patent
Resource Relation:
Patent File Date: 2012 Jul 06
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS; 42 ENGINEERING

Citation Formats

Lawlor, Shawn P., and Roberts, II, William Byron. Gas turbine engine. United States: N. p., 2016. Web.
Lawlor, Shawn P., & Roberts, II, William Byron. Gas turbine engine. United States.
Lawlor, Shawn P., and Roberts, II, William Byron. Tue . "Gas turbine engine". United States. https://www.osti.gov/servlets/purl/1241316.
@article{osti_1241316,
title = {Gas turbine engine},
author = {Lawlor, Shawn P. and Roberts, II, William Byron},
abstractNote = {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.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2016},
month = {3}
}

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