Combustor and heat shield configurations for a gas turbine engine

Abstract

The present disclosure relates to combustor and heat shield configurations for gas turbine engines. A heat shield for a gas turbine engine can include one or more effusion holes downstream of a dilution hole to restore a cooling film applied to the heat shield in the combustor. Effusion holes may be clustered in one or more configurations and rows following each dilution hole and/or on a trailing edge of each heat shield panel structure. One or more embodiments are directed to effusion holes positioned along a trailing edge of a heat shield panel.

What is claimed is: 
     
         1 . A heat shield for a combustor of a gas turbine engine, the heat shield comprising:
 a panel structure having a surface configured to face a combustor cavity, the surface of the panel structure configured to receive cooling airflow;   a dilution hole in the surface of the panel structure, the dilution hole to provide airflow for the combustor cavity; and   one or more effusion holes in the panel structure, wherein the one or more effusion holes are downstream of the dilution hole, wherein the one or more effusion holes are configured to restore cooling airflow to the surface of the panel structure downstream from dilution hole.   
     
     
         2 . The heat shield of  claim 1 , wherein the panel structure is configured to be mounted downstream from a second panel structure, the second panel structure arranged to provide a cooling air film to the surface. 
     
     
         3 . The heat shield of  claim 1 , wherein the one or more effusion holes are located in one or more rows, and wherein each row includes one or more effusion holes. 
     
     
         4 . The heat shield of  claim 1 , wherein the one or more effusion holes are located in one or more regions following the dilution hole. 
     
     
         5 . The heat shield of  claim 1 , wherein the one or more effusion holes are formed with at least one of a trumpet and cone shape. 
     
     
         6 . The heat shield of  claim 1 , wherein the one or more effusion holes include at least one pair of effusion holes angled towards one another. 
     
     
         7 . The heat shield of  claim 1 , wherein the one or more effusion holes are formed with openings smaller than an opening of the dilution hole. 
     
     
         8 . The heat shield of  claim 1 , further comprising one or more effusion holes along a trailing edge of the panel structure and downstream of the dilution hole. 
     
     
         9 . A combustor of a gas turbine engine, the combustor comprising:
 a combustor structure including a combustor cavity; and   one or more panels lining the combustor shell structure, wherein each panel is configured to include
 a panel structure having a surface configured to face the combustor cavity, the surface of the panel structure configured to receive cooling airflow, 
 a dilution hole in the surface of the panel structure, the dilution hole to provide airflow for the combustor cavity; and 
 one or more effusion holes downstream of the dilution hole, wherein the one or more effusion holes are configured to restore cooling airflow to the surface of the panel structure downstream from dilution hole. 
   
     
     
         10 . The combustor of  claim 9 , wherein the combustor structure is an annular structure including one or more heat shield panels mounted to an inner diameter structure and outer diameter structure of the annular structure. 
     
     
         11 . The combustor of  claim 9 , wherein the panel structure is configured to be mounted downstream from a second panel structure, the second panel structure arranged to provide a cooling air film to the surface. 
     
     
         12 . The combustor of  claim 9 , wherein the one or more effusion holes are located in one or more rows, and wherein each row includes one or more effusion holes. 
     
     
         13 . The combustor of  claim 9 , wherein the one or more effusion holes are located in one or more regions following the dilution hole. 
     
     
         14 . The combustor of  claim 9 , wherein the one or more effusion holes are formed with at least one of a trumpet and cone shape. 
     
     
         15 . The combustor of  claim 9 , wherein the one or more effusion holes include at least one pair of effusion holes angled towards one another. 
     
     
         16 . The combustor of  claim 9 , wherein the one or more effusion holes are formed with openings smaller than an opening of the dilution hole. 
     
     
         17 . The combustor of  claim 9 , further comprising one or more effusion holes along a trailing edge of the panel structure and downstream of the dilution hole. 
     
     
         18 . The combustor of  claim 9 , wherein the one or more panels line second and third rows of the combustor shell structure.