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Title: Ducting arrangement with injector assemblies arranged in an expanding cross-sectional area of a downstream combustion stage in a gas turbine engine

Abstract

A ducting arrangement (10) in a combustion stage downstream of a main combustion stage of a gas turbine engine is provided. A duct (18) is fluidly coupled to receive a cross-flow of combustion gases from the main combustion stage. Duct (18) includes a duct segment (23) with an expanding cross-sectional area (24) where one or more injector assemblies (26) are disposed. Injector assembly (26) includes one or more reactant-guiding structures (27) arranged to deliver a flow of reactants into the downstream combustion stage to be mixed with the cross-flow of combustion gases. Disclosed injector assemblies are arranged in expanding cross-sectional area (24) to reduce total pressure loss while providing an effective level of mixing of the injected reactants with the passing cross-flow. Respective duct components or the entire ducting arrangement may be formed as a unitized structure, such as a single piece using a rapid manufacturing technology, such as 3D Printing/Additive Manufacturing (AM) technologies.

Inventors:
; ; ; ; ;
Issue Date:
Research Org.:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1525025
Patent Number(s):
10222066
Application Number:
15/165,195
Assignee:
Siemens Energy, Inc. (Orlando, FL)
Patent Classifications (CPCs):
F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23R - GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
F - MECHANICAL ENGINEERING F02 - COMBUSTION ENGINES F02C - GAS-TURBINE PLANTS
DOE Contract Number:  
FE0023968
Resource Type:
Patent
Resource Relation:
Patent File Date: 2016-05-26
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS

Citation Formats

Chen, Yuntao, Portillo Bilbao, Juan Enrique, North, Andrew J., Tran, Lucky, Meadows, Joseph, and Laster, Walter Ray. Ducting arrangement with injector assemblies arranged in an expanding cross-sectional area of a downstream combustion stage in a gas turbine engine. United States: N. p., 2019. Web.
Chen, Yuntao, Portillo Bilbao, Juan Enrique, North, Andrew J., Tran, Lucky, Meadows, Joseph, & Laster, Walter Ray. Ducting arrangement with injector assemblies arranged in an expanding cross-sectional area of a downstream combustion stage in a gas turbine engine. United States.
Chen, Yuntao, Portillo Bilbao, Juan Enrique, North, Andrew J., Tran, Lucky, Meadows, Joseph, and Laster, Walter Ray. Tue . "Ducting arrangement with injector assemblies arranged in an expanding cross-sectional area of a downstream combustion stage in a gas turbine engine". United States. https://www.osti.gov/servlets/purl/1525025.
@article{osti_1525025,
title = {Ducting arrangement with injector assemblies arranged in an expanding cross-sectional area of a downstream combustion stage in a gas turbine engine},
author = {Chen, Yuntao and Portillo Bilbao, Juan Enrique and North, Andrew J. and Tran, Lucky and Meadows, Joseph and Laster, Walter Ray},
abstractNote = {A ducting arrangement (10) in a combustion stage downstream of a main combustion stage of a gas turbine engine is provided. A duct (18) is fluidly coupled to receive a cross-flow of combustion gases from the main combustion stage. Duct (18) includes a duct segment (23) with an expanding cross-sectional area (24) where one or more injector assemblies (26) are disposed. Injector assembly (26) includes one or more reactant-guiding structures (27) arranged to deliver a flow of reactants into the downstream combustion stage to be mixed with the cross-flow of combustion gases. Disclosed injector assemblies are arranged in expanding cross-sectional area (24) to reduce total pressure loss while providing an effective level of mixing of the injected reactants with the passing cross-flow. Respective duct components or the entire ducting arrangement may be formed as a unitized structure, such as a single piece using a rapid manufacturing technology, such as 3D Printing/Additive Manufacturing (AM) technologies.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2019},
month = {3}
}

Works referenced in this record:

Combustion transition duct providing stage 1 tangential turning for turbine engines
patent, May 2010


Forming structures from CAD solid models
patent, November 2004


Assembly for directing combustion gas
patent, October 2012


Dual stage-dual mode low emission gas turbine combustion system
patent, December 1983


Combustor assembly in a gas turbine engine
patent, February 2013


Air/fuel supply system for use in a gas turbine engine
patent, June 2014


Gas turbine engine combustion chamber
patent, December 1995


Late lean injection with adjustable air splits
patent, February 2012


Method and apparatus for sequentially staged combustion using a catalyst
patent, April 1997


Fuel nozzle
patent, November 2015


Combustor and method of operating same
patent, April 1993