Patent Application
20130108420
The present application and the resultant patent relate generally to gas turbine engines and more particularly relate to layered spline seal assemblies having non-metallic layers for improved temperature resistance.
Leakage of cooling flows between turbine components generally causes reduced power output and lower efficiency. For example, the hot combustion gases may be contained within the turbine by providing pressurized compressor air around the hot gas path contained by seals. Leaks may be caused by thermal expansion of certain components and relative movement between components during operation of the gas turbine. Leakage of high pressure cooling flows into the hot gas path thus may lead to detrimental parasitic losses. Overall efficiency thus may be improved by blocking the leakage locations while providing cooling flows only as required.
For example, spline seals may be used between adjacent stator parts in a ring assembly of a gas turbine. Current gas turbine spline seals use many different combinations and configurations of metal shims and metal wire mesh. Moreover, the lowest leakage rates may be achieved by using only thin metal shims without the wire mesh that may permit leakage therethrough. Although these thin metal shims may be appropriate for use in aviation engines, such spline seals may not be considered sufficiently robust for extended use in heavy duty gas turbine engines under full speeds and loads.
There is thus a desire for an improved spline seal for use in heavy duty gas turbine engines. Such a spline seal should be high temperature resistant, wear resistant, and sufficiently flexible so as to provide adequate sealing with a long component lifetime.
The present application and the resultant patent thus provide a seal assembly for a turbine. The seal assembly may include a number of metal shim layers and a number of non-metallic layers. A pair of the non-metallic layers surrounds each metal shim layer.
The present application and the resultant patent further provide a turbine. The turbine may include a first stator, a second stator, and a seal assembly positioned between the first stator and the second stator. The seal assembly may include a number of metal shim layers and a number of non-metallic layers.
The present application and the resultant patent further provide a turbine. The turbine may include a first stator, a second stator, and a seal assembly positioned between the first stator and the second stator. The seal assembly may include a number of metal shim layers and a number of mica layers such that a pair of the mica layers surrounds each metal shim layer.
These and other features and improvements of the present application and the resultant patent will become apparent to one of ordinary skill in the art upon review of the following detailed description when taken in conjunction with the several drawings and the appended claims.
Referring now to the drawings, in which like numerals refer to like elements throughout the several views,
The gas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels. The gas turbine engine 10 may be any type of land based gas turbine engine and the like. The gas turbine engine 10 may have different configurations and may use other types of components. Other types of gas turbine engines also may be used herein. Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together.
The turbine 100 may include a seal assembly 160 positioned between the components 110, 120. The seal assembly 160 may extend from a first seal slot 170 in the first turbine component 110 to a second seal slot 180 in the second turbine component 120. The seal assembly 160 may include a spline seal 190 for use between the diaphragms 130, 140 and the like. The seal assembly 160 blocks a gap 200 between the components 110, 120 so as to prevent the escape of the cooling air flows 20 therethrough and the like. Other locations may be used herein.
In the example of
The non-metallic layers 220, 230 provide high temperature resistance and wear resistance in a flexible sealing medium. The metal shim layer 210 provides backing and support as well as a failsafe in case the non-metallic layers 220, 230 rupture or otherwise fail. The use of the two non-metallic layers 220, 230 on either side of the metal shim layer 210 provides for ease of manufacture and installation. Additional metal shim layers also may be used. The metal shim layer 210 and the non-metallic layers 220, 230 may be coupled via high temperature adhesives, high strength fasteners, welding, and other types of conventional means. Other components and other configurations may be used herein.
The seal assemblies 160, 260 described herein thus provide the performance of a thin sheet spine seal while providing a robust seal in the context of the operation of a heavy duty gas turbine. The non-metallic layers described herein provide high temperature resistance, wear resistance, and flexibility while the metal shim layers provide backing and support while also providing a failsafe layer. The seal assemblies 160, 180 also provide for ease of installation in the seal assemblies 160, 260 may be installed in either direction. In other words, any of the non-metallic layers may act as a seal surface 370 facing the gap 200. The seal assemblies 160, 180 may be original equipment or part of a retrofit.
It should be apparent that the foregoing relates only to certain embodiments of the present application and the resultant patent. Numerous changes and modifications may be made herein by one of ordinary skill in the art without departing from the general spirit and scope of the invention as defined by the following claims and the equivalents thereof.
