Regeneratively cooled transition duct with transversely buffered impingement nozzles

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:: Morrison, Jay A; Lee, Ching-Pang; Crawford, Michael E

Issue Date:: 2015-04-21

Research Org.:: Siemens Energy, Inc., Orlando, FL (United States)

Sponsoring Org.:: USDOE

OSTI Identifier:: 1178277

Patent Number(s):: 9,010,125

Application Number:: 13/956,405

Assignee:: Siemens Energy, Inc. (Orlando, FL) NETL

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. 
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                    Morrison, Jay A, Lee, Ching-Pang, & Crawford, Michael E. Regeneratively cooled transition duct with transversely buffered impingement nozzles.  United States.

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                    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.

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@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}

}

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Works referenced in this record:

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

Bancalari, Eduardo; Wilson, Jody; Little, David A.
US Patent Document 7,721,547
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=/netahtml/PTO/search-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN/7721547

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Title: Regeneratively cooled transition duct with transversely buffered impingement nozzles

Abstract

Citation Formats

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

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