Turbomachine combustor including a combustor sleeve baffle

Abstract

A turbomachine combustor includes a combustor body extending from a head end to a discharge end. The combustor body includes a combustor liner defining a combustion chamber. A combustor sleeve surrounds the combustor liner. The combustor sleeve is spaced from the combustor liner forming a passage. The combustor sleeve includes at least one opening. A baffle is arranged in the passage. The baffle includes a curvilinear surface extending from the combustor sleeve across the at least one opening toward the head end of the combustor body. The baffle is configured and disposed to compress a fluid flow passing through the passage toward the head end.

What is claimed is: 
     
         1 . A turbomachine combustor comprising:
 a combustor body extending from a head end to a discharge end, the combustor body including a combustor liner defining a combustion chamber;   a combustor sleeve surrounding the combustor liner, the combustor sleeve being spaced from the combustor liner forming a passage, the combustor sleeve including at least one opening; and   a baffle arranged in the passage, the baffle including a curvilinear surface extending from the combustor sleeve across the at least one opening toward the head end of the combustor body, the baffle being configured and disposed to compress a fluid flow passing through the passage toward the head end.   
     
     
         2 . The turbomachine combustor according to  claim 1 , wherein the at least one opening comprises a plurality of openings extending circumferentially about the combustor sleeve. 
     
     
         3 . The turbomachine combustor according to  claim 2 , wherein the baffle includes an opening arranged between adjacent ones of the plurality of openings. 
     
     
         4 . The turbomachine combustor according to  claim 3 , wherein the opening includes at least one hole formed in the curvilinear surface. 
     
     
         5 . The turbomachine combustor according to  claim 1 , wherein the baffle extends from a first end to a second, cantilevered end through the curvilinear surface, the second end includes a divergent portion. 
     
     
         6 . The turbomachine combustor according to  claim 5 , wherein the divergent portion diverges from the second end at an angle of less than 5 degrees. 
     
     
         7 . The turbomachine combustor according to  claim 1 , wherein the passage is substantially unobstructed downstream of the baffle. 
     
     
         8 . A turbomachine comprising:
 a compressor portion;   a turbine portion operatively connected to the compressor portion; and   a combustor assembly fluidically connected to the compressor portion and the turbine portion, the combustor assembly including at least one combustor, the at least one combustor including:
 a combustor body extending from a head end to a discharge end, the combustor body including a combustor liner defining a combustion chamber; 
 a combustor sleeve surrounding the combustor liner, the combustor sleeve being spaced from the combustor liner forming a passage, the combustor sleeve including at least one opening; and 
 a baffle arranged in the passage, the baffle including a curvilinear surface extending from the combustor sleeve across the at least one opening toward the head end of the combustor body, the baffle being configured and disposed to compress a fluid flow passing through the passage toward the head end. 
   
     
     
         9 . The turbomachine according to  claim 8 , wherein the at least one opening comprises a plurality of openings extending circumferentially about the combustor sleeve. 
     
     
         10 . The turbomachine according to  claim 9 , wherein the baffle includes an opening arranged between adjacent ones of the plurality of openings. 
     
     
         11 . The turbomachine according to  claim 10 , wherein the opening includes at least one hole formed in the curvilinear surface. 
     
     
         12 . The turbomachine according to  claim 8 , wherein the baffle extends from a first end to a second, cantilevered end through the curvilinear surface, the second end includes a divergent portion. 
     
     
         13 . The turbomachine according to  claim 8 , wherein the passage is substantially unobstructed downstream of the baffle. 
     
     
         14 . A method of passing air through a combustor including a passage defined between a combustor liner and a combustor sleeve, the method comprising:
 guiding a first airflow through the passage toward a head end of the combustor;   passing the first airflow over a baffle;   compressing the first airflow between the baffle and the combustor liner;   introducing a second airflow into the first airflow downstream of the baffle; and   merging the first airflow and the second airflow creating a substantially turbulent free airflow.   
     
     
         15 . The method of  claim 14 , further comprising: passing a portion of the first airflow through the baffle. 
     
     
         16 . The method of  claim 15 , wherein passing the portion of the first airflow through the baffle includes passing the portion of the first airflow through openings formed in the baffle. 
     
     
         17 . The method of  claim 15 , wherein passing the portion of the first airflow through the baffle includes passing the portion of the first airflow through an interruption in the baffle. 
     
     
         18 . The method of  claim 14 , further comprising: passing the substantially turbulent free airflow toward the head end of the combustor through an unobstructed portion of the passage. 
     
     
         19 . The method of  claim 14 , wherein compressing the first airflow includes passing the first airflow over a curvilinear surface of the baffle. 
     
     
         20 . The method of  claim 14 , further comprising: passing the second airflow over a divergent portion of the baffle. 
     
     
         21 . The method of  claim 14 , wherein creating the substantially turbulent free airflow enhances heat transfer from the combustion liner. 
     
     
         22 . The method of  claim 14 , wherein creating the substantially turbulent free airflow enhances circumferential uniformity of the airflow. 
     
     
         23 . The method of  claim 14 , wherein creating the substantially turbulent free airflow reduces impingement pressure losses.