Patent Application
20140356155
The present application and the resultant patent relate generally to gas turbine engines and more particularly relate to a turbine nozzle with a rib cap to ensure the installation and use of an appropriately sized and shaped cavity insert in each nozzle cavity.
Generally described, a heavy duty gas turbine includes alternating rows of stationary nozzles and rotating blades positioned along the hot gas path. Specifically, each turbine stage includes an array of circumferentially spaced, radially extending nozzle vanes. The nozzle vanes include vane airfoils that extend between inner and outer bands. The vane airfoils may be partially hollow and may form a part of a cooling circuit therein. Overall nozzle cooling schemes, however, may be somewhat complex given the three-dimensional aerodynamic profile of the vane airfoils and the varying heat loads therein.
The nozzle cooling schemes may use internal nozzle cavity inserts of varying configurations for use in different locations. The various nozzle inserts may be functionally different but may be physically similar. Attention must be paid to ensure the use of the correct cavity insert because the installation of the wrong insert could have a significant negative impact on overall nozzle cooling and performance.
There is thus a desire for an improved turbine nozzle design. Such an improved nozzle design may prevent the installation of physically similar but functionally different nozzle cavity inserts in each nozzle cavity for improved overall cooling and performance.
The present application and the resultant patent thus provide a nozzle assembly for use in a turbine engine. The nozzle assembly may include a first nozzle cavity, a second nozzle cavity, a rib positioned between the first nozzle cavity and the second nozzle cavity, a first cavity insert with a first cavity insert configuration, a second cavity insert with a second cavity insert configuration, and a rib cap positioned on the rib. The rib cap may include a rib cap configuration such that only the first cavity insert with the first cavity insert configuration fits within the first nozzle cavity and only the second cavity insert with the second cavity insert configuration fits within the second nozzle cavity.
The present application and the resultant patent further provide a method of assembling a nozzle assembly. The method may include the steps of providing a first nozzle with a first cavity having a first cavity configuration, providing a second nozzle with a second cavity having the first cavity configuration, positioning a first rib cap about the first cavity such that only a first cavity insert with a first cavity insert configuration fits therein, and positioning a second rib cap about the second cavity such that only a second cavity insert with a second cavity insert configuration fits therein.
The present application and the resultant patent further may provide a nozzle assembly for use in a turbine engine. The nozzle assembly may include a number of nozzles with a first nozzle cavity, a second nozzle cavity, and a rib positioned therebetween, a number of first cavity inserts with a number of first insert configurations, a number of second cavity inserts with a number of second insert configurations, and a number of rib caps with a number of rib cap configurations.
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 liquid fuels, 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.
A rib cap 180 may be positioned on the rib 140 and between the modified inserts 150. The rib cap 180 may have any size, shape, or configuration depending upon the intended nozzle 100 of use and the position therein. A number of differently sized and shaped rib caps 180 thus may be used herein. The rib cap 180 may be attached to the rib 140 via welding, brazing, and the like. The rib cap 180 also may be a cast feature. The rib cap 180 may be installed as original equipment or as part of a repair or retro-fit. Other components and other configurations may be used herein.
The use of the rib cap 180 thus modifies the size and shape of the cavities 110. The use of the rib cap 180 ensures that only the correct modified inserts 150 may be positioned in any given cavity 110. The rib cap 180 thus largely “murphy” proofs each nozzle 105 in that only the correct modified insert 150 will fit therein. Moreover, the overall size and shape of the cavities 110 may remain common across the nozzles 100 while utilizing different types of modified inserts 150 so as to achieve functionally different overall nozzle assemblies 100. A common nozzle casting thus may be used herein for reduced overall manufacturing costs. The use of the rib cap 180 prevents the installation of functionally different but physically similar inserts while enhancing overall manufacturing/product reliability.
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.
