The present application and the resultant patent relate generally to gas turbine engines and more particularly relate to a contoured honeycomb seal for a shroud of a last stage of a turbine.
Generally described, a gas turbine engine includes a combustor to produce a flow of hot combustion gases. The hot combustion gases are directed towards a turbine. The hot combustion gases impart a rotational force on the turbine blades therein so as to create mechanical energy. The turbine blades include end portions that rotate in close proximity to a turbine casing and the like. The closer the tip portions of the turbine blades are to the turbine casing, the lower the energy loss therein. Specifically, when clearances between the tip portions and the turbine casing are relatively high, the high energy combustion gases may escape without producing useful work. Reducing the clearance therein ensures that a larger portion of the thermal energy of the combustion gases is converted to mechanical energy so as to provide increased output and overall efficiency.
There is thus a desire for improved sealing system for use in a gas turbine engine. Preferably, such improved sealing systems may provide increased efficiency in both a turbine and a downstream diffuser while also providing overall increased power output.
The present application and the resultant patent thus provide a stage of a turbine engine. The stage may include a bucket, a shroud facing the bucket, and a contoured honeycomb seal on the shroud. The contoured honeycomb seal may include a first step with a first shape and a second step with a contoured shape.
The present application and the resultant patent further may provide a turbine for a gas turbine engine. The turbine may include a number of stages, a number of buckets, a shroud surrounding the buckets, a contoured honeycomb seal positioned on the shroud and facing a bucket of a last turbine stage, and a diffuser downstream of the last turbine stage.
The present application and the resultant patent further may provide a stage of a gas turbine engine. The stage may include a bucket, a shroud facing the bucket, a contoured honeycomb seal on the shroud with a first step and a contoured second step, and a contoured shroud aft end downstream of the contoured honeycomb seal.
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 one of a number of different gas turbine engines offered by General Electric Company of Schenectady, N.Y., including, but not limited to, those such as a 7 or a 9 series heavy duty 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 bucket 70 may be enclosed within a shroud 90. A honeycomb seal member 92 may be mounted on the shroud 90 adjacent to the tip portion 80 of the bucket 70. The honeycomb seal 92 may be formed from a deformable material. The honeycomb seal 92 may have a substantial step-like shape with a first step 94 and a second step 96. The seal rail 85 may be positioned anywhere between the two steps 94, 96. The steps 94, 96 may have a substantially straight or linear shape 98. Other components and other configurations may be used herein.
A static shroud 170 may enclose the bucket 130. As is shown in
The second step 200 of the contoured honeycomb seal 180 may have a second shape 215. In this example, the second shape 215 may be a partially contoured shape 220. The partially contoured shape 220 may decrease in depth downstream about from the intersection 230 towards the diffuser 120 at an end of the contoured honeycomb seal 180. The partially contoured shape 220 may include a second step linear portion 240 about the intersection 230 that leads downstream to a second step contoured portion 250. The angle, depth, and curvature of the partially contoured shape 220 may vary. The second step 200 may be longer or shorter than the first step 190. Other components and other configurations may be used herein.
In use, the flow of combustion gases 35 extends between the tip portion 150 of the bucket 130 and the contoured honeycomb seal 180 of the shroud 170. The elimination of the second step 96 with the linear shape 98 in the contoured honeycomb seal 180 described herein provides an increase in performance in the turbine stage 100. Moreover, additional performance benefits are provided in the diffuser 120. Specifically, the use of the partially contoured shape 220 in the contoured honeycomb seal 180 alone or in combination with the shape of the diffuser 120 improves the flow condition for the diffuser. Improved flow condition for the diffuser 120 means improved radial and swirl flow angles and a total pressure favorable to diffuser performance. A higher inlet pressure (PTA) and radial flow angle (Phi) may reduce flow separation in the diffuser 120 during part load conditions and otherwise.
Although the turbine stage 100 has been described herein in terms of the last stage 110, the contoured honeycomb seal 180 with the partially contoured shape 220 may be applicable to other stages and other locations as well. The use of the partially contoured shape 220 thus improves stage efficiency, diffuser performance, and overall gas turbine performance. The contoured honeycomb seal 180 may be original equipment of part of a repair or a retrofit.
In addition to the contour of the contoured honeycomb seals 180,
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.
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Number | Date | Country | |
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20130170964 A1 | Jul 2013 | US |