Patent Application
20080298956
In an industrial gas turbine, shroud segments are fixed to turbine shelf hooks in an annular array about the turbine rotor axis to form an annular shroud radially outwardly and adjacent the tips of buckets forming parts of the turbine rotor. The inner wall of the shroud defines part of the gas path. Conventionally, the shroud segments are comprised of inner and outer shrouds provided with complimentary hooks and grooves adjacent their leading and trailing edges for joining the inner and outer shrouds to one another. The outer shroud is, in turn, secured to the turbine shell or casing hooks. In an example configuration, each shroud segment has one outer shroud and two or three inner shrouds.
The invention uses the pressure gradient that exists between the flow path aft of the bucket and the shroud cooling air to allow the trailing edge hook to seal more effectively. More specifically, the invention takes the pressure gradient that would normally generate a force in the radial direction and transforms it to a force in the axial and radial directions through the use of at least on sloped surface. The slope is housed in the trailing edge of the inner shroud and outer shroud and is positioned in such a fashion, in an example embodiment, that the pressure gradient will force the inner shroud to move slightly in the direction of the gas path and towards the center of the engine. This movement will force the inner shroud to tightly seal the radial gap between the inner shroud and outer shroud.
Thus, the invention may be embodied in a stator shroud of a multi-stage gas turbine comprising: a shroud segment having a surface for in part defining a hot gas path through one stage and overlaying tips of buckets of said one stage forming part of the turbine rotor, said shroud segment having a leading, upstream edge and a trailing, downstream edge; said shroud segment comprising an outer shroud and at least one inner shroud connected thereto; said outer shroud having a groove defined adjacent and along each of said leading and trailing edges thereof, said groove along said trailing edge opening in an axially upstream direction; said inner shroud having a leading edge axially projecting hook portion and a trailing edge axially projecting hook portion for respectively engaging said grooves of said outer shroud, said engagement axially and radially locking said inner shroud to said outer shroud; and wherein at least one of said trailing edge hook of said inner shroud and said trailing edge groove of said outer shroud includes a sloped surface disposed at an angle to an axial direction of said rotor and to a radial direction of said rotor and facing the other of said inner shroud and outer shroud whereby a radial inward force on said inner shroud is transformed into a force in axial and radial directions to force the inner shroud to tightly seal a radial gap between said inner and outer shrouds.
These and other objects and advantages of this invention, will be more completely understood and appreciated by careful study of the following more detailed description of the presently preferred exemplary embodiments of the invention taken in conjunction with the accompanying drawings, in which:
Referring to
In the illustrated example, the outer shroud 116 has a radially outward dovetail 130 for engagement in a dovetail groove 132 defined by leading and trailing hooks 134,136 forming part of the fixed turbine shell or casing for securing the shroud segment to the casing. Known alternatives to the illustrated configuration would include an outer shroud provided with a radially outer dovetail groove for receiving a correspondingly shaped dovetail formed as a part of the turbine casing, as in
As in the structure shown in
Traditional shroud hooks use axial and radial (vertical and horizontal) hook components as in the shroud assemblies shown in
The invention uses the pressure gradient that exists between the flow path aft of the bucket and the shroud cooling air to allow the trailing edge hook to seal more effectively. The higher effectiveness seal decreases the gap between the inner and outer shrouds which in turn decreases the amount of cooling flow lost through this particular seal. More specifically, the invention takes the pressure gradient that would normally generate a force in the radial direction and transforms it to a force in the axial and radial directions through the use of the sloped surfaces. The slope is housed in the trailing edge of the inner shroud and outer shroud and is positioned in such a fashion, in an example embodiment, that the pressure gradient will force the inner shroud to move slightly in the direction of the gas path and towards the center of the engine. This movement will force the inner shroud to tightly seal the radial gap between the inner shroud and outer shroud.
Thus and more specifically, to ensure contact along the seal and an effective seal at the aft hook, in an example embodiment of the invention, a sloped, conical component is incorporated in the seal that transfers the pressure loading from purely a radial force to a radial and axial force. Thus, as an embodiment a stator shroud generally of the type illustrated in
In an example embodiment, as illustrated in
Thus, the invention transfers the loading from purely radial to a combination of axial and radial and forces the inner shroud to seal the radial gap between the inner and outer shrouds. In this way, the pressure gradient forces a tight seal in the radial direction (due to the axial force) instead of in the axial/circumferential direction. Seals in the axial/circumferential direction are not effective seals because of the chording effect of the inner and outer shroud as mentioned previously.
In the illustrated example, the trailing edge hook 218 of the inner shroud 214 comprises a radially outer circumferential surface 244 and a radially inner circumferential surface. The radially inner circumferential surface is comprised of the sloped surface 240 and a first surface 246 generally parallel to the axial direction of the rotor. In this example, the hook 218 further comprises a second surface 248 parallel to the axial direction and on an opposite axial side of the sloped surface 240 with respect to the first surface 246. On the other hand, the radially outer circumferential surface 244 of the hook 218 extends axially along substantially an entire axial length of the hook 218.
In the illustrated example, the trailing edge groove 222 of the outer shroud 212 comprises a radially outer circumferential surface 250 and a radially inner circumferential surface. The radially inner circumferential surface is comprised of the sloped surface 242 and a first surface 252 generally parallel to the axial direction of the rotor. In this example, the groove 222 further comprises a second surface 254 parallel to the axial direction and on an opposite axial side of the sloped surface 242 with respect to the first surface 252. On the other hand, the radially outer circumferential surface 250 of the groove 222 extends axially along substantially an entire axial length of the groove 222.
As will be appreciated, there are other possible geometries of the outer shroud and inner shroud interface that could use the sloped hook concept of the invention to seal the aft end of the shroud in addition to the illustrated embodiment. Thus, the invention is embodied in the use of a sloped seal to decrease the effective gap in the seal, but is not limited to the particular location or configuration of the sloped seal illustrated or the respective configurations of the inner and outer shroud hooks and grooves.
Thus, while the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.
