Conjoined gas turbine interface seal

Abstract

A device including a conjoined laminate interface seal shaped for reducing inter-seal gap (e.g., an angled gap, an ‘L’-shaped gap, etc.) leakage in gas turbines is disclosed. In one embodiment, a seal device for a gas turbine includes: a first flange shaped to be disposed within a first slot of a first arcuate component and a first adjacent slot of a second arcuate component; a conjoined layer connected to a first surface of the first flange, the first surface configured to face a working fluid flow of the gas turbine; and a second flange shaped to be disposed within a second slot of the first arcuate component and a second adjacent slot of the second arcuate component, the second flange including a second surface connected to the conjoined layer.

Description

FIELD OF THE INVENTION[0001]This invention relates generally to power plant systems and, more particularly, to conjoined seal systems (e.g., a conjoined laminate seal system) and devices for reducing interface leakage losses in gas turbines.BACKGROUND OF THE INVENTION[0002]The operation of some power plant systems, for example certain simple-cycle and combined-cycle power plant systems, include the use of gas turbines. The operation of these gas turbines includes the use of pressurized fluid flows at extreme temperatures traveling through flowpaths of the gas turbine, these pressurized fluid flows regulating operation of the turbine and driving a rotor of the turbine (e.g., power generation). The working fluid flow path (e.g., the main gas-flow path) in a gas turbine commonly includes the operational components of a compressor inlet, a compressor, a turbine section and a gas outflow. There are also secondary flows that are used to cool the various heated components of the turbine, t...

AI Technical Summary

Benefits of technology

This patent describes a seal device for gas turbines that helps to improve cooling efficiency and reduce corrosion to the components. The seal device includes a flange that is placed within slots of adjacent components, with a conjoined layer that is connected to the flange and facing the direction of the working fluid flow. This arrangement helps to improve the sealing performance and protect the components from damage caused by the high temperatures and pressures of the gas turbine. Overall, this invention provides a more reliable and durable gas turbine that can operate with higher efficiency and reliability.

Problems solved by technology

Mixing of these flows and gas leakage in general, from or into the gas-flow path, may be detrimental to turbine performance.

However, this third seal may cover the gap from the high pressure side but not seal the gap between the set of planar seals.

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