Combustor for gas turbine engine and gas turbine

Abstract

A combustor for gas turbine engine, wherein: a plurality of impingement-cooling holes are opened passing through an external wall of a liner for cooling air to blow out towards the outer surface of an internal wall of the liner; a plurality of pin-fins are formed on the outer surface of the internal wall of the liner; a plurality of effusion cooling holes are opened passing through the internal wall of the liner for cooling air to blow out along the inner surface of the internal wall of the liner. The top surface of each pin-fin is not in contact with the inner surface of the external wall of the liner and the ratio of the height of the pin-fin to the equivalent diameter of the impingement-cooling hole is set to be 1.0-3.0.

1 : A combustor for a gas turbine engine used in the gas turbine engine and configured to produce a combustion gas by combusting fuel in compressed air, the combustor comprising:
 a combustor case; and   a combustor liner installed inside the combustor case and including a combustion chamber which is formed inside the combustor liner, the combustion chamber configured to combust the fuel, wherein   the combustor liner is formed into a double-wall structure including an external wall of the liner and an internal wall of the liner,   a plurality of impingement-cooling holes are opened passing through the external wall of the liner for part of the compressed air as cooling air to blow out towards an outer surface of the internal wall of the liner,   a plurality of effusion cooling holes are opened passing through the internal wall of the liner for the cooling air to blow out along an inner surface of the internal wall of the liner,   a plurality of pin-fins are formed on the outer surface of the internal wall of the liner,   a top surface of each pin-fin is not in contact with an inner surface of the external wall of the liner, and   a ratio of a height of each pin-fin to an equivalent diameter of each impingement-cooling hole is set in a range of 1.0 to 3.0.   
     
     
         2 : The combustor for a gas turbine engine of  claim 1 , wherein a ratio of a clearance between the inner surface of the external wall of the liner and the outer surface of the internal wall of the liner to the equivalent diameter of the impingement-cooling hole is set in a range of 1.0 to 5.0. 
     
     
         3 : The combustor for a gas turbine engine of  claim 1 , wherein an outlet portion of each impingement-cooling hole, an inlet portion of each effusion cooling hole, and each pin-fin are placed in mutually different locations in a state where the combustor liner is developed into a plane. 
     
     
         4 : The combustor for a gas turbine engine of  claim 2 , wherein an outlet portion of each impingement-cooling hole, an inlet portion of each effusion cooling hole, and each pin-fin are placed in mutually different locations in a state where the combustor liner is developed into a plane. 
     
     
         5 : A gas turbine comprising the combustor for a gas turbine engine of  claim 1 .