Combustor triple liner assembly for gas turbine engines

Abstract

A combustor triple liner assembly includes coaxially aligned and radially spaced cylindrical inner, middle and outer liners forming an inner annular flow-path between the inner and the middle liners, and an outer annular flow-path between the middle and the outer liners. A plurality of inner dividers segments the inner annular flow-path into inner compartments. A plurality of outer dividers segments the outer annular flow-path into outer compartments and the middle liner into middle liner sections corresponding to each outer compartment. Each middle liner section includes a plurality of impingement holes fluidly connecting the outer compartment to one corresponding inner compartment which in turn is fluidly connected to one corresponding downstream outer compartment through an opening in the middle liner, such that cooling air flows from the outer compartment through the impingement holes into the corresponding inner compartment and therefrom through the opening into the corresponding downstream outer compartment.

1 . A combustor triple liner assembly for a gas turbine engine, the combustor triple liner assembly comprising:
 an inner liner having a longitudinal axis and defining a combustion chamber,   a middle liner housing the inner liner,   an outer liner housing the middle liner and the inner liner,   wherein the inner liner, the middle liner and the outer liner are coaxially aligned cylinders and are radially separated to create an inner annular flow-path between the inner liner and the middle liner, and to create an outer annular flow-path between the middle liner and the outer liner,   a plurality of inner dividers serially arranged longitudinally within the inner annular flow-path, wherein each of the inner dividers extends radially between the inner liner and the middle liner dividing the inner annular flow-path into a plurality of inner compartments,   a plurality of outer dividers serially arranged longitudinally within the outer annular flow-path, wherein each of the outer dividers extends radially between the middle liner and the outer liner dividing the outer annular flow-path into a plurality of outer compartments and dividing the middle liner into a plurality of middle liner sections corresponding to each outer compartment,   wherein the middle liner section of each outer compartment comprises a plurality of impingement holes fluidly connecting the outer compartment to one corresponding inner compartment and wherein the corresponding inner compartment is fluidly connected to one corresponding downstream outer compartment through at least one opening in the middle liner, such that cooling air entering the outer annular flow-path flows from the outer compartment through the impingement holes of the outer compartment to the corresponding inner compartment and therefrom through the opening to the corresponding downstream outer compartment.   
     
     
         2 . The combustor triple liner assembly according to  claim 1 ,
 wherein the inner liner comprises a plurality of film cooling holes adapted to allow a part of the cooling air from at least one of the inner compartments to enter the combustion chamber and to provide film cooling of an inner surface of the inner liner.   
     
     
         3 . The combustor triple liner assembly according to  claim 1 ,
 wherein the inner liner comprises at least one dilution hole adapted to allow a part of the cooling air from at least one of the inner compartments to enter the combustion chamber to dilute the combustion gases in the combustion chamber   
     
     
         4 . The combustor triple liner assembly according to  claim 1 ,
 wherein the impingement holes are located in the middle liner section of each outer compartment as an array extending circumferentially and axially in the middle liner section.   
     
     
         5 . The combustor triple liner assembly according to  claim 1 ,
 wherein at least one of the outer dividers comprises one or more by-pass holes configured to allow a part of the cooling air to flow from the outer compartment upstream of the outer divider to the outer compartment downstream of the outer divider.   
     
     
         6 . The combustor triple liner assembly according to  claim 1 ,
 wherein the outer dividers are integrally formed with the middle liner.   
     
     
         7 . The combustor triple liner assembly according to  claim 6 ,
 wherein the inner dividers are integrally formed with the middle liner.   
     
     
         8 . The combustor triple liner assembly according to  claim 6 ,
 wherein the inner dividers are integrally formed with the inner liner.   
     
     
         9 . The combustor triple liner assembly according to  claim 1 ,
 wherein the outer dividers are integrally formed with the outer liner.   
     
     
         10 . The combustor triple liner assembly according to  claim 9 ,
 wherein the inner dividers are integrally formed with the middle liner.   
     
     
         11 . The combustor triple liner assembly according to  claim 9 , wherein the inner dividers are integrally formed with the inner liner. 
     
     
         12 . A combustor assembly comprising:
 a burner and a combustor triple liner assembly,   wherein the combustor triple liner assembly is according to  claim 1 .   
     
     
         13 . A gas turbine engine comprising:
 a combustor triple liner assembly,   wherein the combustor triple liner assembly is according to  claim 1 .