The present invention is directed to turbine shroud assemblies. More particularly, the present invention is directed to turbine shroud assemblies having spline seals.
Hot gas path components of gas turbines, which include metal and ceramic matrix composite (“CMC”) components that are positioned adjacent to each other, are subjected to elevated temperatures and harsh environments during operation. For example, turbine shrouds include a hot gas path-facing sub-component which is not fully secured to, but in contact with, a non-hot gas path-facing sub-component. These sub-components have different rates of thermal expansion, and utilize a spline seal that is positioned between these sub-components to maintain a seal during gas turbine operation. However, during non-operation of the gas turbine, with sub-components returning to ambient temperatures, the spline seal is susceptible to a loss of positive retention between the sub-components, possibly resulting in inadvertent removal from the gas turbine.
In an exemplary embodiment, a turbine shroud assembly includes an outer shroud arranged within a turbine and further comprising opposed extending portions. The turbine shroud assembly further includes an inner shroud shielding the outer shroud from a gas flowing along a gas path within the turbine during operation of the turbine and comprising opposed first and second arcuate portions extending around and in direct contact with a corresponding extending portion of the outer shroud for supporting the inner shroud from the outer shroud. The turbine shroud assembly further includes a spline seal extending between the first and second arcuate portions and positioned between the inner shroud and the outer shroud. The turbine shroud assembly further includes at least one of the inner shroud, the outer shroud and the spline seal including at least one protrusion for maintaining positive retention of the spline seal during non-operation of the turbine.
In another exemplary embodiment, a turbine shroud assembly includes an outer shroud arranged within a turbine and further comprising opposed extending portions, and an inner shroud shielding the outer shroud from a gas flowing along a gas path within the turbine during operation of the turbine and comprising opposed first and second arcuate portions extending around and in direct contact with a corresponding extending portion of the outer shroud for supporting the inner shroud from the outer shroud. The turbine shroud assembly further includes a length of a spline seal extending between the first and second arcuate portions and positioned between the inner shroud and the outer shroud. The outer shroud includes a first outer shroud segment and a second outer shroud segment having respective first and second outer shroud segment surfaces facing each other and separated by an outer shroud gap. The inner shroud includes a first inner shroud segment and a second inner shroud segment having respective first and second inner shroud segment surfaces facing each other and separated by an inner shroud gap. The first inner shroud segment includes a first recess portion at the first inner shroud segment surface. The second inner shroud segment includes a second recess portion at the second inner shroud segment surface, the first recess portion and the second recess portion forming a recess for receiving a width of the spline seal. The width of the spline seal spans the outer shroud gap and the inner shroud gap, the width of the spline seal having opposed edges facing corresponding surfaces of the recess. At least one of the first outer shroud near the first outer shroud surface and the spline seal include at least one first protrusion. At least one of the second outer shroud near the second outer shroud surface and the spline seal include at least one second protrusion, and the at least one first protrusion and the at least one second protrusion maintaining positive retention of the spline seal during non-operation of the turbine.
Other features and advantages of the present invention will be apparent from the following more detailed description of the preferred embodiment, taken in conjunction with the accompanying drawings, which illustrate, by way of example, the principles of the invention.
Wherever possible, the same reference numbers will be used throughout the drawings to represent the same parts.
Provided are exemplary turbine components, such spline seals and turbine shroud assemblies. Embodiments of the present disclosure, in comparison to articles not utilizing one or more features disclosed herein, increase component life, decrease maintenance requirements, decrease cost, improve sealing or combinations thereof.
Referring to
As further shown in
Spline seal 34 (
Inner shroud 22 may include any suitable material composition, including, but not limited to, CMC material such as, but not limited to, aluminum oxide-fiber-reinforced aluminum oxides (Ox/Ox), carbon-fiber-reinforced silicon carbides (C/SiC), silicon-carbide-fiber-reinforced silicon carbides (SiC/SiC), carbon-fiber-reinforced silicon nitrides (C/Si3N4), or silicon-carbide-fiber-reinforced silicon nitrides (SiC/Si3N4), or superalloy material, such as, but not limited to, nickel-based superalloys, cobalt-based superalloys, René 108, René N5, INCONEL 738 or combinations thereof.
As used herein, “INCONEL 738” refers to an alloy including a composition, by weight, of about 0.17% carbon, about 16% chromium, about 8.5% cobalt, about 1.75% molybdenum, about 2.6% tungsten, about 3.4% titanium, about 3.4% aluminum, about 0.1% zirconium, about 2% niobium, and a balance of nickel.
As used herein, “HAYNES 188” refers to an alloy including a composition, by weight, of about 22% chromium, about 22% nickel, about 0.1% carbon, about 3% iron, about 1.25% manganese, about 0.35% silicon, about 14% tungsten, about 0.03% lanthanum, and a balance of cobalt.
As used herein, “René N5” refers to an alloy including a composition, by weight, of about 7.5% cobalt, about 7.0% chromium, about 6.5% tantalum, about 6.2% aluminum, about 5.0% tungsten, about 3.0% rhenium, about 1.5% molybdenum, about 0.15% hafnium, and a balance of nickel.
As used herein, “René 108” refers to an alloy including a composition, by weight, of about 8.4% chromium, about 9.5% cobalt, about 5.5% aluminum, about 0.7% titanium, about 9.5% tungsten, about 0.5% molybdenum, about 3% tantalum, about 1.5% hafnium, and a balance of nickel.
Outer shroud 14 may include any suitable material composition, including, but not limited to, iron alloys, steels, stainless steels, carbon steels, nickel alloys, superalloys, nickel-based superalloys, cobalt-based superalloys, or combinations thereof.
While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from the essential scope thereof. Therefore, it is intended that the invention not be limited to the particular embodiment disclosed as the best mode contemplated for carrying out this invention, but that the invention will include all embodiments falling within the scope of the appended claims.
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Number | Date | Country | |
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20180363485 A1 | Dec 2018 | US |