US2014216044A1PendingUtilityA1

Gas turbine engine combustor heat shield with increased film cooling effectiveness

47
Assignee: UNITED TECHNOLOGIES CORPPriority: Dec 17, 2012Filed: Dec 17, 2012Published: Aug 7, 2014
Est. expiryDec 17, 2032(~6.4 yrs left)· nominal 20-yr term from priority
Inventors:Nurhak Erbas-SenJames B. HokeFrank J. Cunha
F23R 2900/00004F23R 3/002F23R 3/06F23R 2900/03042Y02T50/60
47
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Claims

Abstract

A heat shield for a gas turbine engine includes a hot side with one or more raised features that extend therefrom.

Claims

exact text as granted — not AI-modified
What is claimed is: 
     
         1 . A heat shield for use in a combustor of a gas turbine engine comprising:
 a cold side; and   a hot side with one or more raised features that extend therefrom.   
     
     
         2 . The heat shield as recited in  claim 1 , further comprising a plurality of studs which extend from said cold side. 
     
     
         3 . The heat shield as recited in  claim 1 , wherein said raised feature is adjacent to a hole through said heat shield. 
     
     
         4 . The heat shield as recited in  claim 3 , wherein said hole is a dilution hole. 
     
     
         5 . The heat shield as recited in  claim 4 , wherein said raised feature includes a film cooling hole therethrough. 
     
     
         6 . The heat shield as recited in  claim 4 , wherein said raised feature is forward of said dilution hole. 
     
     
         7 . The heat shield as recited in  claim 6 , wherein said raised feature is a ramp. 
     
     
         8 . The heat shield as recited in  claim 7 , wherein said ramp includes a film cooling hole therethrough. 
     
     
         9 . The heat shield as recited in  claim 4 , wherein said raised feature is aft of said dilution hole. 
     
     
         10 . The heat shield as recited in  claim 9 , wherein said raised feature is a ramp. 
     
     
         11 . The heat shield as recited in  claim 10 , wherein said ramp includes a film cooling hole therethrough. 
     
     
         12 . The heat shield as recited in  claim 3 , wherein said raised feature is a ramp. 
     
     
         13 . The heat shield as recited in  claim 12 , wherein said ramp includes a film cooling hole therethrough. 
     
     
         14 . The heat shield as recited in  claim 3 , wherein said raised feature is rectilinear. 
     
     
         15 . The heat shield as recited in  claim 14 , wherein said raised feature includes a film cooling hole therethrough. 
     
     
         16 . The heat shield as recited in  claim 3 , wherein said raised feature is arcuate. 
     
     
         17 . The heat shield as recited in  claim 16 , wherein said raised feature includes a film cooling hole therethrough. 
     
     
         18 . A method of increasing heat transfer through a heat shield of a combustor of a gas turbine engine, comprising:
 augmenting cooling film airflow proximate a dilution hole.   
     
     
         19 . The method as recited in  claim 18 , further comprising:
 locating a raised feature proximate the dilution hole.   
     
     
         20 . The method as recited in  claim 19 , further comprising:
 directing film airflow through the raised feature toward the dilution hole.

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