The present invention relates generally to a cooling system for the nozzle segments of a gas turbine and particularly relates to a cooling system for cooling the adjoining edges of inner and outer platforms of adjacent nozzle segments arranged in an annular array about the axis of the turbine.
In gas turbines, annular arrays of nozzles are disposed in the hot gas path for turning and accelerating the gas flow for optimum performance of the buckets. In the first stage of a turbine, for example, there are a plurality of circumferentially spaced nozzle vanes which extend generally radially between inner and outer annular bands which serve to confine the gas flow to an annular configuration as the gas flows through the multiple stages of the turbine. A plurality of circumferentially spaced buckets mounted on the turbine rotor lie axially downstream of the annular array of nozzles and form a turbine stage with the nozzles. The nozzles, for example, of the first stage of the turbine, are typically provided in nozzle segments. Each nozzle segment includes an inner platform and an outer platform and at least one vane extending between the platforms. The nozzle segments are arranged in circumferential registration with one another. Particularly, the inner and outer platforms of each nozzle segment lie in circumferential registration with the inner and outer platforms of adjacent segments, respectively. In this arrangement, gaps are formed between adjoining segments along the platform edges. Prior nozzle platform edges have been uncooled, cooled by film cooling from adjacent nozzle segments or cooled by long holes that run from a large impingement cavity in the nozzle segment to the gaps between the nozzle segments. Film cooling from an adjacent nozzle to cool the platform edge, however, causes a debiting of the cooling effectiveness when the cooling film crosses the nozzle intersegment gap. When long holes running from an impingement cavity are utilized, the convective cooling of the edge by the holes is discrete rather than continuous and, therefore, less efficient.
Certain prior nozzle designs have adjacent platform edges configured such that the nozzle intersegment gaps are aligned parallel to the hot gas flow vector. Perfect alignment of the adjoining edges of the nozzle segments, however, is difficult to achieve and maintain as a result of manufacturing and thermomechanical problems. It will be appreciated that the core flow boundary layers of the hot gas along the platform surfaces may be tripped if the intersegment gap is not aligned with the flow direction. A boundary layer trip at the adjoining edges of the platforms results in a spike in heat transfer near the edge of the platform and also results in a debit to the cooling effectiveness of any film cooling medium that crosses the gap.
Notwithstanding the desirability of aligning the inner segment gaps parallel to the flow vector, it is beneficial for other reasons to provide nozzle platform edges which extend generally parallel to the axis of the rotor. This enables removal of the nozzles without removal of the top half of the turbine shell, resulting in less expensive and more flexible maintenance. Consequently, the intersegment gap is not aligned with the core flow downstream of the vane. Such design is more sensitive to any platform deformations that would cause a mismatch between the platform edges of adjacent nozzle segments and cause the core flow to “see” a facing step. Thus, the edges of nozzles segment platforms which extend generally parallel to the turbine axis are subject to severe thermal distress due to boundary layer trip. Accordingly, it has been found desirable to provide a cooling system which would minimize or eliminate the foregoing problems associated with cooling edges of nozzle segments wherein the edges lie generally parallel to the turbine axis.
In accordance with a preferred embodiment of the present invention, an elongated plenum is provided along at least one edge and, preferably, both edges of each of the inner and outer platforms. Each plenum is provided with a plurality of supply or inlet passages in communication between a source of a cooling medium, e.g., compressor discharge air. The supply passages communicate with the elongated plenum at spaced locations along the plenum. A plurality of outlet passages are provided in communication with each plenum at spaced locations therealong and have outlet openings through a corresponding side edge of the platform at spaced locations therealong. Additional passageways lie in communication with the plenum and terminate in a plurality of film cooling holes in the platform surface exposed to the hot gas path. Thus, cooling medium supplied from the plenum to the film cooling holes film cool the platform surfaces exposed in the hot gas path.
The outlet passages and passageways from each plenum are located such that each inlet passage does not have direct line-of-sight to the outlet passages and passageways. As a consequence, the cooling medium impinges on the walls of each plenum and provides additional internal convective cooling to the edges of the platform. Moreover, the cooling medium supply passages provide a substantially uniform pressure and flow of coolant along the length of the plenum, affording a continuous rather than discrete cooling effect. As a consequence of this arrangement, the edges of the platforms are cooled by (i) both conduction and convection due to the proximity of the plenum to the edge being cooled; (ii) cooling medium flowing through the outlet passages passing under the edge and into the intersegment gap through the outlet openings; (iii) impingement of the supplied cooling medium inside the plenum due to the lack of direct line-of-sight flow from the inlets to the outlets; and (iv) film cooling.
In a preferred embodiment according to the present invention, there is provided a nozzle segment for a turbine having an axis, comprising inner and outer platforms and at least one nozzle vane extending therebetween, the platforms having side edges extending generally parallel to the axis, a cooling system for at least one of the platforms including a source of a cooling medium, a first elongated plenum extending along at least one of the side edges of the one platform, a plurality of inlet passages in communication between the source and the plenum at spaced locations along the plenum, a plurality of outlet passages in communication with the plenum at spaced locations along the plenum and having outlet openings through one side edge of one platform at spaced locations therealong, and passageways in communication with the plenum and a plurality of film cooling holes disposed along a surface of one platform for supplying the cooling medium along and film cooling the platform surface, the inlet passages, the outlet passages and the passageways being arranged such that the inlet passages do not have direct line-of-sight flow of the cooling medium into the outlet passages and the passageways.
In a further preferred embodiment according to the present invention, there is provided in a turbine having an axis, a plurality of nozzle segments arranged in a circumferential array about the axis, each of the nozzle segments including inner and outer platforms and at least one nozzle vane extending therebetween, the platforms having side edges extending generally parallel to the axis and in generally circumferential registration with the side edges of platforms of adjacent nozzle segments, a cooling system for at least one of the platforms of each segment including a source of a cooling medium, a first elongated plenum extending along at least one of the side edges of one platform, a plurality of inlet passages in communication between the source and the plenum at spaced locations along the plenum, a plurality of outlet passages in communication with the plenum at spaced locations along the plenum and having outlet openings through one side edge of one platform at spaced locations therealong for flowing the cooling medium toward the side edge of a platform of an adjacent nozzle segment, and passageways in communication with the plenum and a plurality of film cooling holes disposed along a surface of the platform for supplying the cooling medium along and film cooling the platform surface, the inlet passages, the outlet passages and the passageways being arranged such that the inlet passages do not have direct line-of-sight flow of the cooling medium into the outlet passages and the passageways.
In a further preferred embodiment according to the present invention, there is provided a nozzle segment for a turbine having an axis, comprising inner and outer platforms and at least one nozzle vane extending therebetween, the platforms having opposite side edges adjacent respective suction and pressure sides of the vane, a cooling system for at least one of the platforms including a source of a cooling medium, first and second elongated plenums extending along the opposite side edges of one platform, a plurality of first and second inlet passages in communication between the source and the first and second plenums, respectively, at spaced locations therealong, a plurality of first and second outlet passages in communication with the first and second plenums, respectively, at spaced locations along the plenums and having outlet openings through respective opposite side edges of one platform at spaced locations therealong, and a plurality of first and second passageways in communication with the first and second plenums, respectively, and a plurality of film cooling holes disposed along a surface of one platform for supplying the cooling medium along and film cooling the platform surface, the first and second plenums extending along respective side edges of the platform adjacent suction and pressure sides of the vane with the first plenum spaced closer to a side edge of the platform on the suction side of the vane than the second plenum is spaced from the side edge of the platform on the pressure side of the vane.
Referring now to the drawings, particularly to
Referring to
Referring now to
The cooling system hereof includes a first plenum 48 extending generally parallel along the suction side edge 42 of the platform and below the surface of the platform exposed to the hot gas in the hot gas path. The plenum 48 is closed at both ends. The plenum may be integrally cast with the nozzle or may be drilled and plugged at one end. The tapered enlarged ends illustrated in
Further, first passageways 56 communicate the cooling medium between the plenum 48 and film cooling holes 58 formed in the surface of the platform for film cooling the surface exposed to the hot gas path. The inlet passages 50, the outlet passages 52 and the passageways 56 are arranged such that the inlet passages 50 do not have direct line-of-sight flow of the cooling medium into the outlet passages 52 and the passageways 56 as the cooling medium flows into the plenum 48. Consequently, impingement cooling of the surfaces of the plenum is effected, affording enhanced internal convective cooling. It will be appreciated that the proximity of the cooling medium in the plenum 48 affords conductive and convective cooling of the side edge 42 of the platform. Additionally, the passages 52 and outlets 54 transmit cooling medium into the intersegment gap, between adjacent platforms, providing cooling of the side edge of the adjacent nozzle. On the suction side of the platform, it will be appreciated that the film cooling holes 58 are arranged to direct film cooling medium generally in the direction of the flow along the platform, i.e., extending in the general direction of the suction side of the vane.
Referring to
To minimize any thermal spike or trip of flow between the pressure side of the platform and the suction side of the adjacent platform, a platform edge portion 88 adjacent the trailing edge and along the suction side edge of the platform is slightly recessed, as in
With the foregoing cooling scheme, it will be appreciated that the proximity of the cooling medium in the first and second plenums of each platform affords conductive and convective cooling of the edges of the platform. Further, the second film cooling holes 84 afford film cooling along downstream portions of the pressure side of the segment, as well as along the suction side of the adjacent segment. The film cooling holes 58 film cool the platform surface along the suction side of the segment. The first and second cooling holes 54 and 80 lie just under the platform surface exposed to the hot gas path and provide cooling medium into the intersegment gap to cool the edges. Finally, the arrangement of the inlet passages vis-a-vis the outlet passages and passageways is such that direct line-of-sight flow of cooling medium does not occur, and consequently affords enhanced conductive and convective cooling of the edges.
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.