Combustor for gas turbine engine

Abstract

A combustor for a gas turbine engine that is placed in a compressed air chamber of the gas turbine engine to generate combustion gas, the combustor being provided with a liner that defines a combustion chamber therein around a prescribed central axis, the liner comprising: a thick wall portion provided in a part of a wall of the liner, the thick wall portion having a prescribed axial length and extending circumferentially around the central axis; an air guide portion that extends from the thick wall portion along an inner surface of the wall of the liner so as to define a gap jointly with an opposing inner surface of the wall of the liner; a plurality of first cooling air holes passed through the wall and opening to the gap; and a plurality of second cooling air holes passed through the thick wall portion.

1 . A combustor for a gas turbine engine that is placed in a compressed air chamber of the gas turbine engine to generate combustion gas, the combustor being provided with a liner that defines a combustion chamber therein around a prescribed central axis, the liner comprising:
 a thick wall portion provided in a part of a wall of the liner, the thick wall portion having a prescribed axial length and extending circumferentially around the central axis;   an air guide portion that extends from the thick wall portion along the wall of the liner so as to define a gap jointly with an inner surface of the wall of the liner;   a plurality of first cooling air holes passed through the wall and opening to the gap; and   a plurality of second cooling air holes passed through the thick wall portion.   
     
     
         2 . The combustor for a gas turbine engine according to  claim 1 , wherein the liner includes an end wall substantially orthogonal to the central axis and a peripheral wall extending along the central axis and connected to the end wall via a first end part of the peripheral wall which is curved so as to join a main part of the peripheral wall with the end wall,
 the thick wall portion is provided in a junction portion between the first end part of the peripheral wall and the end wall, and   the air guide portion extends from the thick wall portion radially outward substantially in parallel with the end wall.   
     
     
         3 . The combustor for a gas turbine engine according to  claim 1 , wherein the liner includes an end wall substantially orthogonal to the central axis and a peripheral wall extending along the central axis and connected to the end wall via a first end part of the peripheral wall which is curved so as to join a main part of the peripheral wall with the end wall,
 the thick wall portion is provided in a junction portion between the first end part of the peripheral wall and a main part of the peripheral wall, and   the air guide portion extends from the thick wall portion substantially in parallel with the peripheral wall away from the end wall.   
     
     
         4 . The combustor for a gas turbine engine according to  claim 1 , wherein the combustor consists of an annular combustor including an annular end wall substantially orthogonal to the central axis and having an outer peripheral edge and an inner peripheral edge, an outer peripheral wall extending along the central axis and connected to the outer peripheral edge of the end wall via a first end part thereof which is curved so as to join a main part of the outer peripheral wall with the end wall, and an inner peripheral wall extending along the central axis and connected to the inner peripheral edge of the end wall via a first end part thereof which is curved so as to join a main part of the inner peripheral wall with the end wall,
 the thick wall portion is provided in each of junction portions between the first end part of the outer peripheral wall and the end wall and between the first end part of the inner peripheral wall and the end wall, and   the air guide portion extends from each of the thick wall portions radially away from the end wall.   
     
     
         5 . The combustor for a gas turbine engine according to  claim 4 , wherein the second cooling air holes are inclined in a circumferential direction, and the second cooling air holes of one of the junction portions are inclined in a different circumferential direction from the second cooling air holes of the other junction portions. 
     
     
         6 . The combustor for a gas turbine engine according to  claim 1 , wherein the thick wall portion and the air guide portion define inner surfaces which face the combustion chamber and are substantially planar and continuous to each other. 
     
     
         7 . The combustor for a gas turbine engine according to  claim 6 , wherein the thick wall portion defines a substantially smooth outer profile and an inwardly bulging inner profile. 
     
     
         8 . The combustor for a gas turbine engine according to  claim 6 , wherein the thick wall portion defines an outwardly bulging outer profile and a substantially smooth inner profile. 
     
     
         9 . The combustor for a gas turbine engine according to  claim 1 , wherein the second cooling air holes include a part that is flared from a side of the cooling air chamber to a side of the combustion chamber. 
     
     
         10 . The combustor for a gas turbine engine according to  claim 9 , wherein the second cooling air holes each include an upstream portion having a substantially constant inner diameter, and a downstream portion that is flared from a side of the cooling air chamber to a side of the combustion chamber. 
     
     
         11 . The combustor for a gas turbine engine according to  claim 10 , wherein the downstream portion of each second cooling air hole has a cross-sectional shape that is elongated in a radial direction. 
     
     
         12 . The combustor for a gas turbine engine according to  claim 1 , wherein the second cooling air holes are inclined in a circumferential direction.