Combustor assembly for a turbo machine

Abstract

Embodiments of a combustor assembly for a turbine engine are generally provided. The combustor assembly includes a first separable portion defining a dome assembly, and a second separable portion defining a deflector assembly. The first separable portion and the second separable portion are coupled together at a fitted interface.

What is claimed is: 
     
         1 . A combustor assembly of a combustor in a combustion section of a turbine engine, the combustor assembly comprising:
 a dome including a dome assembly that is defined by a first separable portion; and   a deflector including a deflector assembly that is defined by a second separable portion,   wherein the first separable portion and the second separable portion are (a) coupled together at a fitted interface to fasten the dome assembly and the deflector assembly together, (b) removably coupled at the fitted interface by a plurality of threads, and (c) free from welds and brazes so that the dome assembly or the deflector assembly can be replaced without significantly damaging or destroying the dome assembly or the deflector assembly.   
     
     
         2 . The combustor assembly of  claim 1 , wherein the fitted interface joins the first separable portion and the second separable portion by (i) a threaded fit and (ii) one or more of a press fit, tight fit, and an interface fit. 
     
     
         3 . The combustor assembly of  claim 1 , wherein the plurality of threads includes a male threaded interface and a female threaded interface. 
     
     
         4 . The combustor assembly of  claim 3 , wherein the first separable portion defines the male threaded interface, and the second separable portion defines the female threaded interface. 
     
     
         5 . The combustor assembly of  claim 3 , wherein the first separable portion defines an outer diameter or a surrounding surface relative to the second separable portion, the first separable portion defining the female threaded interface and the second separable portion defining the male threaded interface. 
     
     
         6 . The combustor assembly of  claim 3 , wherein the plurality of threads includes a ballnose feature between the male threaded interface and the female threaded interface. 
     
     
         7 . The combustor assembly of  claim 6 , wherein the ballnose feature defines a rounded end or radius configured to provide an air seal between the plurality of threads. 
     
     
         8 . A method of assembling the combustor assembly of  claim 3 , comprising engaging the male threaded interface and the female threaded interface by screwing the first separable portion onto the second separable portion to couple the first separable portion and the second separable portion. 
     
     
         9 . The method of  claim 8 , further comprising heating an outer diameter of the second separable portion. 
     
     
         10 . The method of  claim 8 , further comprising cooling an inner diameter of the first separable portion. 
     
     
         11 . A gas turbine engine comprising a combustor assembly including:
 a dome including a dome assembly that is defined by a first separable portion; and   a deflector including a deflector assembly that is defined by a second separable portion,   wherein the first separable portion and the second separable portion are (a) coupled together at a fitted interface to fasten the dome assembly and the deflector assembly together, (b) removably coupled at the fitted interface by a plurality of threads, and (c) free from welds and brazes so that the dome assembly or the deflector assembly can be replaced without significantly damaging or destroying the dome assembly or the deflector assembly.   
     
     
         12 . The gas turbine engine of  claim 11 , wherein the fitted interface joins the first separable portion and the second separable portion by (a) a threaded fit and (b) one or more of a press fit, tight fit, and an interface fit. 
     
     
         13 . The gas turbine engine of  claim 11 , wherein the plurality of threads includes a male threaded interface and a female threaded interface. 
     
     
         14 . The gas turbine engine of  claim 13 , wherein the first separable portion defines the male threaded interface, and the second separable portion defines the female threaded interface. 
     
     
         15 . The gas turbine engine of  claim 13 , wherein the first separable portion defines an outer diameter or a surrounding surface relative to the second separable portion, the first separable portion defining the female threaded interface and the second separable portion defining the male threaded interface. 
     
     
         16 . The gas turbine engine of  claim 13 , wherein the plurality of threads includes a ballnose feature between the male threaded interface and the female threaded interface. 
     
     
         17 . The gas turbine engine of  claim 16 , wherein the ballnose feature defines a rounded end or radius configured to provide an air seal between the plurality of threads. 
     
     
         18 . A method for assembling the combustor assembly of the gas turbine engine of  claim 13 , comprising engaging the male threaded interface and the female threaded interface by screwing the first separable portion onto the second separable portion to couple the first separable portion and the second separable portion. 
     
     
         19 . The method of  claim 18 , further comprising heating an outer diameter of the second separable portion. 
     
     
         20 . The method of  claim 18 , further comprising cooling an inner diameter of the first separable portion.