FIELD: machine building.
SUBSTANCE: gas turbine comprises an exhaust diffuser installed downstream after the last turbine stage and comprising a jet passing section and a pole. The jet passing section comprises parts of the first and the second walls, and the pole is fitted by a front edge passing between the part of the first wall and the part of the second wall. The pole's front edge comprises the first and the second parts, and the second part of the front edge is located between the first part of the front edge and the part of the second wall. The front edge of the pole is also fitted by the third straight part set between the fisrt and the second parts of the front edge. The first part of the front edge passes at 20-40% of the distance between the first front extreme point in which the front edge touches the part of the first wall, and the second front extreme point in which the front edge touches the part of the second wall. The first part of the front edge is inclined to the section outlet in relation to the direction of the normal line perpendicular to the part of the first wall in the first front extreme point, thus allowing for the reduction of Mach number in the direction perpendicular to the front edge. The second part of the front edge is inclined to the section outlet in relation to the direction of the normal line perpendicular to the part of the second wall in the second front extreme point, in which the front edge touches the part of the second wall.
EFFECT: invention allows for the increased efficiency of a turbine due to the reduction of losses in a diffuser.
21 cl, 16 dwg
