Gas turbine blade assembly having retainer assembling structure, and gas turbine having same

Abstract

A gas turbine blade assembly, which is as an assembly provided with a plurality of gas turbine blades on an outer circumferential surface of a rotating disk along a circumferential direction to be spaced apart from each other at predetermined intervals, includes: a retainer insertion hole provided in a blade-fixing end, and depressed by a predetermined depth to correspond to a lower end of a retainer; a retainer coupler provided at a lower end of each of the gas turbine blades, and depressed by a predetermined depth to correspond to an upper end of the retainer; and a coupling member coupled at a location adjacent to the retainer coupler to couple the retainer and each of the gas turbine blades together.

Description

CROSS REFERENCE TO RELATED APPLICATION[0001]The present application claims priority to Korean Patent Application No. 10-2017-0047337, filed Apr. 12, 2017, the entire contents of which is incorporated herein by reference.BACKGROUND[0002]The present disclosure relates generally to a gas turbine blade assembly having retainer assembling structure, and a gas turbine having the same. More particularly, the present disclosure relates to a gas turbine blade assembly having a structure capable of being easily disassembled and assembled and achieving sealing, and a gas turbine having the same.[0003]Generally, a turbine is a mechanical device that obtains torque by impulsive force or reaction force using flow of compressible fluid such as steam or gas. It is called as a steam turbine when steam is used and a gas turbine when combustion gas is used.[0004]A thermodynamic cycle of the gas turbine is the Brayton Cycle, which is as follows: a compressor for sucking and boosting air from the atmosp...

AI Technical Summary

Benefits of technology

[0037]Further, according to an exemplary gas turbine blade assembly of the present disclosure in which the lower end of the retainer is spaced apart from a bottom surface of the retainer insertion hole at a predetermined distance, and the depth of the retainer coupler is equal to or less than the distance between the lower end of the retainer and the bottom surface of the retainer insertion hole, assembly and disassembly of the retainer may be performed more easily than the related art.

[0038]Further, according to an exemplary gas turbine blade assembly of the present disclosure that includes a coupling member insertion hole, a coupling member, and a retainer coupler having predetermined structures, it is possible to easily assemble and disassemble the retainer, and possible to achieve a stable coupling structure.

[0039]Further, according to an exemplary gas turbine blade assembly of the present disclosure that includes a slot groove in a predetermined shape provided between the coupling member insertion hole and the retainer coupler, and the retainer and the gas turbine blade are coupled together after the coupling member is mounted by using the slot groove, it is possible to perform easy assembly, and possible to achieve a stable coupling structure.

[0040]Further, according to an exemplary gas turbine blade assembly of the present disclosure in which the gas turbine blade is locked by using a nut formed with a curved surface continuous with an outer surface of the lower end of each of the gas turbine blades, it is possible to achieve a stable coupling structure.

[0041]Further, according to an exemplary gas turbine blade assembly of the present disclosure that includes a sealing protrusion, an auxiliary sealing protrusion, a support protrusion, and a sealing wire having predetermined structures, it is possible to provide a structure capable of facilitating easy assembly and disassembly and may achieve complete sealing.

[0042]Further, according to an exemplary gas turbine of the present disclosure that includes a gas turbine blade assembly having a predetermined structure, it is possible to provide a gas turbine having a structure capable of being easily disassembled and assembled and may achieve complete sealing.

Problems solved by technology

However, the above method is problematic in that a large number of members to be prepared for assembly are required, and the assembling process and the disassembling process are very complicated, whereby work efficiency is remarkably low.

The retainer according to the related art is problematic in that it requires a very complicated structure to form the cooling gas sealing and the flow path, so it is not easy to manufacture and install.

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