Blade ring arrangement, gas turbine and gas turbine overhaul methods

Abstract

Blade ring arrangement (WS) comprising: a turbine blade ring (70) extending in a circumferential direction (Dc) about an axis (Ar); a cooling target component (46a1) arranged on an inner circumferential surface (70i) of the turbine blade ring (70);and a dust separator (90) arranged on an outer circumferential surface (70o) of the turbine blade ring (70), wherein the turbine blade ring (70) includes a cooling medium inlet port (72) leading from an outer circumferential surface (70o) of the turbine blade ring (70) to an inner circumferential surface (70i) of the turbine blade ring (70), and the dust separator (90) includes: a ceiling wall (91) covering at least a section of the cooling medium inlet port (72) from the outer circumferential surface (70o) of the turbine blade ring (70) and extending such that it is closer to an axial downstream side (Dad), which is one of the two sides in an axial direction (Da) in which the axis (Ar) extends, than the cooling medium inlet port (72), and which is parallel to the outer circumferential surface (70o) of the turbine blade ring (70) extends;a rear wall (92) extending from an end section of the ceiling wall (91) on the axial downstream side (Dad) to the outer circumferential surface (70o) of the turbine blade ring (70) and in contact with the turbine blade ring (70) and covering at least one section of an interior space (S) between the ceiling wall (91) and the cooling medium inlet connection (72) from the axial downstream side (Dad); a first side wall (93) extending from an end section of the ceiling wall (91) located on one side in the circumferential direction (Dcn) to the outer circumferential surface (70o) of the turbine blade ring (70) and in contact with the turbine blade ring (70) and covering at least one section of the interior space (S) from one side in the circumferential direction (Dcn);and a second side wall (94) extending from an end section of the ceiling wall (91), which lies on a second side in the circumferential direction (Dcp), to the outer circumferential surface (70o) of the turbine blade ring (70) and being in contact with the turbine blade ring (70) and covering at least a section of the interior (S) from the second side in the circumferential direction (Dcp), wherein the interior (S) of the dust separator (90) is surrounded by the ceiling wall (91), the rear wall (92), the first side wall (93) and the second side wall (94) and is open to an axial upstream side (Dau), which is one of both sides in the axial direction (Da).