Method for forming a coating matrix on a shaft and disk assembly for a turbine

Abstract

A method for forming a coating matrix on a bore surface of a turbine disk wherein the coating matrix is applied at an interface between the disk and a turbine shaft. The coating matrix enhances thermal conductivity to increase heat transfer from the disk. The method includes providing a receiving surface on the bore surface. The receiving surface is then heated to melt the receiving surface. Next, at least one coating matrix layer is deposited on the receiving surface. The coating matrix layer includes a graphene layer. A pulsed laser system or a robot welding system may be used to melt the receiving section.

Description

FIELD OF THE INVENTION[0001]This invention relates to shrink fit arrangements for turbine components, and more particularly, to a method for forming a thermal conductivity coating matrix on a component of the shrink fit arrangement.BACKGROUND OF THE INVENTION[0002]Renewable energies and their inherent intermittent character require faster start-up times for conventional power generation methods, which use gas or steam turbines. However, conventional shrink fit arrangements used to fasten or attach components in such turbines limit start-up speed. Referring to FIG. 1, a partial cross sectional view of an exemplary compressor section 10 of a gas turbine is shown. Air enters an inlet 12 and is guided to the compressor section 10 by inlet guide vanes 14. The compressor section 10 includes one or more disks 16 each including a plurality of outwardly extending compressor blades 18. The disks 16 are each attached to a rotor shaft 20 of the gas turbine.[0003]Referring to FIG. 2, a partial c...

AI Technical Summary

Benefits of technology

The patent describes a method of applying a coating matrix to a component in a shrink fit arrangement to enhance heat transfer. The coating matrix is applied at an interface between the first component and a second component. The method involves heating the receiving section of the first component and depositing at least one coating matrix layer on it, which includes a graphene layer. The technique can be used on the bore surface of a turbine disk, turbine shaft, or on the outer diameter and grooves of the disk used to attach associated blades. The technical effect is an improvement in heat transfer through the coating matrix, which helps to improve the overall performance of the component.

Problems solved by technology

However, conventional shrink fit arrangements used to fasten or attach components in such turbines limit start-up speed.

When this occurs, heat cannot be transferred from the disk 16 at a sufficient rate to provide adequate shrink fit stress to keep the disk 16 attached to the shaft 20, resulting in possible turbine failure.

However, this increases costs and results in an extended down time in order to implement the bolted design for turbines, which are already in use.

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