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Title: Radial inflow gas turbine engine with advanced transition duct

Abstract

A gas turbine engine (10), including: a turbine having radial inflow impellor blades (38); and an array of advanced transition combustor assemblies arranged circumferentially about the radial inflow impellor blades (38) and having inner surfaces (34) that are adjacent to combustion gases (40). The inner surfaces (34) of the array are configured to accelerate and orient, for delivery directly onto the radial inflow impellor blades (38), a plurality of discrete flows of the combustion gases (40). The array inner surfaces (34) define respective combustion gas flow axes (20). Each combustion gas flow axis (20) is straight from a point of ignition until no longer bound by the array inner surfaces (34), and each combustion gas flow axis (20) intersects a unique location on a circumference defined by a sweep of the radial inflow impellor blades (38).

Inventors:
Issue Date:
Research Org.:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1172766
Patent Number(s):
8,978,389
Application Number:
13/326,392
Assignee:
Siemens Energy, Inc. (Orlando, FL) NETL
DOE Contract Number:  
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2011 Dec 15
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS

Citation Formats

Wiebe, David J. Radial inflow gas turbine engine with advanced transition duct. United States: N. p., 2015. Web.
Wiebe, David J. Radial inflow gas turbine engine with advanced transition duct. United States.
Wiebe, David J. Tue . "Radial inflow gas turbine engine with advanced transition duct". United States. https://www.osti.gov/servlets/purl/1172766.
@article{osti_1172766,
title = {Radial inflow gas turbine engine with advanced transition duct},
author = {Wiebe, David J},
abstractNote = {A gas turbine engine (10), including: a turbine having radial inflow impellor blades (38); and an array of advanced transition combustor assemblies arranged circumferentially about the radial inflow impellor blades (38) and having inner surfaces (34) that are adjacent to combustion gases (40). The inner surfaces (34) of the array are configured to accelerate and orient, for delivery directly onto the radial inflow impellor blades (38), a plurality of discrete flows of the combustion gases (40). The array inner surfaces (34) define respective combustion gas flow axes (20). Each combustion gas flow axis (20) is straight from a point of ignition until no longer bound by the array inner surfaces (34), and each combustion gas flow axis (20) intersects a unique location on a circumference defined by a sweep of the radial inflow impellor blades (38).},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2015},
month = {3}
}

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