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Title: Regeneratively cooled transition duct with transversely buffered impingement nozzles

Abstract

A cooling arrangement (56) having: a duct (30) configured to receive hot gases (16) from a combustor; and a flow sleeve (50) surrounding the duct and defining a cooling plenum (52) there between, wherein the flow sleeve is configured to form impingement cooling jets (70) emanating from dimples (82) in the flow sleeve effective to predominately cool the duct in an impingement cooling zone (60), and wherein the flow sleeve defines a convection cooling zone (64) effective to cool the duct solely via a cross-flow (76), the cross-flow comprising cooling fluid (72) exhausting from the impingement cooling zone. In the impingement cooling zone an undimpled portion (84) of the flow sleeve tapers away from the duct as the undimpled portion nears the convection cooling zone. The flow sleeve is configured to effect a greater velocity of the cross-flow in the convection cooling zone than in the impingement cooling zone.

Inventors:
; ;
Issue Date:
Research Org.:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1178277
Patent Number(s):
9010125
Application Number:
13/956,405
Assignee:
Siemens Energy, Inc. (Orlando, FL)
Patent Classifications (CPCs):
F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F - MECHANICAL ENGINEERING F05 - INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04 F05D - INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
DOE Contract Number:  
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2013 Aug 01
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

Citation Formats

Morrison, Jay A, Lee, Ching-Pang, and Crawford, Michael E. Regeneratively cooled transition duct with transversely buffered impingement nozzles. United States: N. p., 2015. Web.
Morrison, Jay A, Lee, Ching-Pang, & Crawford, Michael E. Regeneratively cooled transition duct with transversely buffered impingement nozzles. United States.
Morrison, Jay A, Lee, Ching-Pang, and Crawford, Michael E. Tue . "Regeneratively cooled transition duct with transversely buffered impingement nozzles". United States. https://www.osti.gov/servlets/purl/1178277.
@article{osti_1178277,
title = {Regeneratively cooled transition duct with transversely buffered impingement nozzles},
author = {Morrison, Jay A and Lee, Ching-Pang and Crawford, Michael E},
abstractNote = {A cooling arrangement (56) having: a duct (30) configured to receive hot gases (16) from a combustor; and a flow sleeve (50) surrounding the duct and defining a cooling plenum (52) there between, wherein the flow sleeve is configured to form impingement cooling jets (70) emanating from dimples (82) in the flow sleeve effective to predominately cool the duct in an impingement cooling zone (60), and wherein the flow sleeve defines a convection cooling zone (64) effective to cool the duct solely via a cross-flow (76), the cross-flow comprising cooling fluid (72) exhausting from the impingement cooling zone. In the impingement cooling zone an undimpled portion (84) of the flow sleeve tapers away from the duct as the undimpled portion nears the convection cooling zone. The flow sleeve is configured to effect a greater velocity of the cross-flow in the convection cooling zone than in the impingement cooling zone.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2015},
month = {4}
}

Works referenced in this record:

Gas turbine combustion apparatus
patent, October 1989


Breach-cooled structure
patent, April 1990


Uniform cooling film replenishment thermal liner assembly
patent, November 1993


Gas turbine airfoil
patent, October 1994


Gas turbine combustion chamber with impingement cooling tubes
patent, February 1995


Turbine cooling blade having inner hollow structure with improved cooling
patent, July 1996


Baffle-cooled wall part
patent, December 1996


Thermal spreading combustor liner
patent, May 1998


Thermal spreading combustion liner
patent, October 1999


Cooling for double-wall structures
patent, December 1999


Dimpled impingement baffle
patent, May 2001


Turbine blade wall section cooled by an impact flow
patent, August 2002


Combustor liner cooling thimbles and related method
patent, November 2002


Tangential flow baffle
patent, April 2003


Method and apparatus for cooling combustor liner and transition piece of a gas turbine
patent, February 2009


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


Wavy CMC wall hybrid ceramic apparatus
patent, March 2011


Method of fabricating a nearwall nozzle impingement cooled component for an internal combustion engine
patent-application, November 2012


Method of forming a multi-panel outer wall of a component for use in a gas turbine engine
patent-application, November 2012


Ducting Arrangement For Cooling A Gas Turbine Structure
patent-application, April 2014