초록 ▼

The invention relates to a carrier ring for a high-pressure gas turbine of a gas turbine plant, which has a high-pressure combustion chamber upstream of the high-pressure gas turbine, a compressor upstream of the high-pressure combustion chamber, a low-pressure combustion chamber downstream of the h

The invention relates to a carrier ring for a high-pressure gas turbine of a gas turbine plant, which has a high-pressure combustion chamber upstream of the high-pressure gas turbine, a compressor upstream of the high-pressure combustion chamber, a low-pressure combustion chamber downstream of the high-pressure gas turbine, a low-pressure gas turbine downstream of the low-pressure combustion chamber, and a rotor that carries rotor blades for the compressor, for the high-pressure gas turbine, and for the low-pressure gas turbine. The carrier ring carries guide blades and/or heat shields of the high-pressure gas turbine and can be fastened to the high-pressure combustion chamber. The installation of the carrier ring can be simplified by segmenting the carrier ring at least in the area of the guide blades thereof and/or of the heat shields thereof in the circumferential direction, wherein the segmented carrier ring has at least two ring segments that carry the guide blades and/or the heat shields.

대표청구항 ▼

1. A carrier ring for a gas turbine installation, which gas turbine installation includes at least one compressor, at least one combustion chamber operated downstream of the at least one compressor and at least one turbine located downstream of the at least one combustion chamber arranged to be acte

1. A carrier ring for a gas turbine installation, which gas turbine installation includes at least one compressor, at least one combustion chamber operated downstream of the at least one compressor and at least one turbine located downstream of the at least one combustion chamber arranged to be acted upon by hot gases from the at least one combustion chamber, wherein rotor blades of the at least one compressor and of the at least one turbine are arranged on a common rotor shaft, said carrier ring comprising: a main ring configured to carry guide vanes and/or heat shields to be attached via the carrier ring to the at least one turbine, the main ring being segmented circumferentially into main ring segments having joints at least in a region configured to carry the guide vanes and/or the heat shields;at least two ring segments of the main ring configured to carry the guide vanes and/or the heat shields; andat least two side partial rings, each of the at least two side partial rings being circumferentially segmented into side partial ring segments having joints; each of the at least two side partial rings being positioned on opposite sides of the main ring, the at least two side partial rings being arranged to attach at least two ring segments of the main ring to one another,each joint of the at least two ring segments of the main ring are offset in the circumferential direction with respect to each joint of the side partial ring segments of the at least two side partial rings;wherein the at least two side partial rings are identical in size and shape. 2. The carrier ring as claimed in claim 1, in combination with a gas turbine installation which comprises: a compressor unit having the at least one compressor;a first combustion chamber operating downstream of the compressor unit as one of the at least one combustion chamber;a first turbine operating downstream of the first combustion chamber as one of the at least one turbine;a second combustion chamber operating downstream of the first turbine as another of the at least one combustion chamber;a second turbine operating downstream of the second combustion chamber as another of the at least one turbine; andwherein the carrier ring carries the guide vanes and/or the heat shields for at least the first turbine and is attached at least to the first combustion chamber. 3. The carrier ring as claimed in claim 1, wherein an axial wall thickness of the main ring is at least 50% greater than an axial wall thickness of each of the at least two side partial rings. 4. The carrier ring as claimed in claim 1, wherein each of the at least two side partial rings has exactly four ring segments and/or each of the at least two side partial rings is symmetrically segmented. 5. The carrier ring as claimed in claim 1, wherein the main ring has exactly four main ring segments wherein each joint of the four main ring segments are offset in the circumferential direction with respect to each joint of the side partial ring segments. 6. The carrier ring as claimed in claim 1, wherein the main partial ring is screwed to each of the at least two side partial rings. 7. A gas turbine installation with a carrier ring as claimed in claim 1 for driving a generator for generating electricity in a power plant installation, the gas turbine installation comprising: the at least one compressor;a first combustion chamber as one of the at least one combustion chamber arranged downstream of the compressor;a first turbine as one of the at least one turbine arranged downstream of the first combustion chamber;a second combustion chamber as another of the at least one combustion chamber arranged downstream of the first turbine; anda second turbine as another of the at least one turbine arranged downstream of the second combustion chamber, wherein at least the first turbine has the carrier ring as claimed in claim 1 which is attached at least to the first combustion chamber.