Abstract:
A method of manufacturing reaction nozzles for a turbine comprising (a) providing a piece of flat plate stock of predetermined size and thickness; and (b) machining the piece of flat plate stock to form a unitary, arcuate reaction nozzle segment including at least two adjacent nozzle airfoils.

Description:
BACKGROUND OF THE INVENTION  
       [0001]     This invention relates to a method of producing steam turbine components and, specifically, dovetailed reaction nozzle segments.  
         [0002]     Current fixed reaction nozzle stages that are located between rotating turbine stages (or wheels) are made up of individual nozzles that are individually inserted within a dovetail slot in a fixed nozzle carrier or turbine casing. The nozzles are formed with integral dovetails at their radially outer ends and integral tip shrouds at their radially inner ends. These nozzles are designed to maintain tip shroud contact throughout operation by incorporating appropriate cover or tip shroud interference along with a pre-twisted cold airfoil portions. During assembly of such nozzles, it has been difficult to confirm that the required cover or tip shroud interference has been obtained. In addition, the process of pre-twisting the nozzle airfoils at assembly causes the airfoils to deviate from the “design” airfoil shape. This can potentially reduce the efficiency of the airfoil.  
       BRIEF DESCRIPTION OF THE INVENTION  
       [0003]     The present invention substantially eliminates many issues relating to individually formed nozzle airfoils. In accordance with an exemplary embodiment, a plurality of nozzles are manufactured by machining from a single piece of flat plate stock. For example, in one exemplary embodiment, a single solid donut-shaped ring is cut from flat plate stock and then cut into two 180° segments. The cut ends of the segments may then be configured for temporary attachment to a machining jig or the like, or the segments may be temporarily joined together (by, e.g., bolts) on a jig and subsequently machined to include integral shroud covers, airfoils and dovetails. After machining, the two 180° segments are loaded into the nozzle carrier or casing dovetail in the usual manner.  
         [0004]     In another arrangement, four 90° segments may be cut from the solid ring and subsequently machined to each include 25% of the required nozzles. Alternatively, arcuately shorter segments may be machined to include as few as two integral nozzle airfoils, thus still reducing the nozzle components by half.  
         [0005]     In all cases, proper spacing between arcuate nozzle segments can be maintained through the utilization of shims of appropriate thickness placed between the segments and the carrier or casing dovetail.  
         [0006]     Accordingly, in one aspect, the invention relates to a method of manufacturing reaction nozzles for a turbine comprising (a) providing a piece of flat plate stock of predetermined size and thickness; and (b) machining the piece of flat plate stock to form a unitary, arcuate reaction nozzle segment including at least two adjacent nozzle airfoils.  
         [0007]     In another aspect, the invention relates to a method of manufacturing reaction nozzles for a turbine comprising (a) providing a single piece of flat plate stock of predetermined size and thickness; and (b) cutting the flat plate stock to form a 360° ring; (c) cutting the 360° ring into two or more arcuate segments; and (d) machining each of the segments to include a plurality of nozzle airfoils.  
         [0008]     In still another aspect, the invention relates to a reaction nozzle component for a steam turbine comprising a unitary arcuate segment formed to include a plurality of adjacent nozzle airfoils.  
         [0009]     The invention will now be described in connection with the drawings identified below. 
     
    
     BRIEF DESCRIPTION OF THE DRAWINGS  
       [0010]      FIG. 1  is a perspective view of a known steam turbine reaction nozzle;  
         [0011]      FIG. 2  is a perspective view of a unitary arcuate reaction nozzle segment in accordance with an exemplary embodiment of this invention;  
         [0012]      FIG. 3  is a plan view of a piece of flat plate stock marked for cutting a 360° ring from the stock;  
         [0013]      FIG. 4  is a plan view of the ring removed from the plate stock of  FIG. 3  and cut to form two 180° arcuate segments;  
         [0014]      FIG. 5  is an exploded view of the two 180° arcuate segments of  FIG. 4  modified for temporary attachment to a jig or to each other for machining; and  
         [0015]      FIG. 6  is a plan view of a solid ring cut into four 90° segments for subsequent machining in accordance with another embodiment of the invention. 
     
    
     DETAILED DESCRIPTION OF THE INVENTION  
       [0016]     With reference initially to  FIG. 1 , a conventional steam turbine reaction nozzle  10  includes an airfoil  12  and an integral radially inner tip shroud or cover  14 . The radially outer end of the nozzle is formed with a base  16  having a dovetail configuration. Specifically, the base or dovetail  16  is provided with a pair of flanges  18  and  20  projecting in both axially upstream and downstream directions, defining recesses  22  therebetween. It will be appreciated that the nozzle casing or carrier (not shown) is provided with generally correspondingly shaped dovetail grooves which allow the nozzles  10  to be individually loaded into the carrier or casing at a conventional notched cut-out. Thus, each nozzle can be loaded into the dovetail slot in the carrier until the entire row of nozzles has been assembled. It will also be appreciated that the dovetail arrangement may be reversed, with the dovetail groove component formed in the nozzle and the dovetail hook component formed on the carrier or casing.  
         [0017]      FIG. 2  illustrates a unitary arcuate dovetail reaction nozzle component or segment manufactured in accordance with an exemplary embodiment of the invention. The segment  24  is machined from a single piece of flat metal plate stock and includes a plurality of adjacent airfoil portions (or simply “airfoils”)  26  with an integral, common tip shroud or cover  28  at the radially inner ends of the airfoils, and an integral, common dovetail hook  30  at the radially inner ends of the airfoils. As will be described further below, the arcuate length of the segments may be varied as desired to include as few as two airfoils or as many as 50% of the airfoils required for a full 360° reaction nozzle ring. In one embodiment, the common dovetail comprises a centerline support mechanism for a 180° segment.  
         [0018]     Turning to  FIG. 3 , a donut-shaped ring  36  is initially cut from a single piece of flat plate stock  38 , using any conventional cutting technique, for example, wire electrical discharge machining (EDM). With the ring  36  removed from the plate stock as shown in  FIG. 4 , the ring is cut into two 180° segments  40  and  42 , again using conventional cutting processes. The separated segments  40  and  42  may be provided with any suitable end flanges as shown at  44 ,  46  that permit the segments to be bolted to a machining jig in alignment with each other, similar to their alignment when assembled in upper and lower carrier or casing components. Alternatively, the segments  38 ,  40  may be temporarily bolted together and otherwise secured to the jig for machining. The segments  38  and  40  are then machined to include the airfoils  26 , integral tip shrouds or tip covers  28 , and dovetail hooks  30  as shown in  FIG. 2 , but noting that  FIG. 2  illustrates an arcuately shorter segment. After machining, the segments  38  and  40  are disassembled or removed from the jig and are ready for insertion into the carrier or casing dovetail groove.  
         [0019]     In an alternative arrangement as shown in  FIG. 6 , a solid ring  48  may be cut from the flat plate stock into four individual 90° segments  50 ,  52 ,  54  and  56  and machined to each include 25% of the required airfoils. In other embodiments, the arcuate length of the airfoil segments may be altered as desired with each segment including at least two airfoils.  
         [0020]     In the exemplary embodiment, the flat plate stock  38  may be high grade 400 Series stainless steel with 12% chromium, or other suitable material.  
         [0021]     In order to maintain proper circumferential spacing of the airfoils, shims of appropriate thickness may be placed between the segments at the dovetail. The segments may be held in place in the dovetail via conventional radial end or axial shims which eliminate the radial end or axial gap between the segment dovetail and the dovetail groove in the casing or carrier.  
         [0022]     By machining airfoils in this fashion, a number of issues associated with the current individual reaction nozzle design can be substantially eliminated or at least minimized including: 
        tip shroud interference and associated manufacturing and assembly difficulties;     untwist of shrouds and airfoils during operation;     axial clearance issues related to the piece-part twist variation at assembly and during operation;     assembling individual nozzle/pins for each stage;     the need to perform in-process assembly checks such as twist, shingling and throat area measurements;     the need for standing assembled modal tests and associated costs and scheduling impacts of each test;     ergonomic concerns related to assembling individual loading pins for individual nozzles.        
 
         [0030]     In addition to eliminating the issues above, the machined segment concept in accordance with this invention also improves the ability to service/repair rows relative to current practice; creates a known/repeatable/unvarying boundary condition; reduces the number of parts per stage; and insures that segments are assembled in the correct location/direction.  
         [0031]     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.