US20140356155A1

US20140356155A1 - Nozzle Insert Rib Cap

Info

Publication number: US20140356155A1
Application number: US13/908,039
Authority: US
Inventors: Charles Lewis Davis, III; Frederick James Brunner
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 2013-06-03
Filing date: 2013-06-03
Publication date: 2014-12-04
Also published as: CH708208A2; DE102014107022A1; CN104213942B; JP2014234823A; CN104213942A; JP6411774B2; DE102014107022B4

Abstract

The present application provides 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.

Description

TECHNICAL FIELD

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.

BACKGROUND OF THE INVENTION

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.

SUMMARY OF THE INVENTION

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.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic diagram of a gas turbine engine showing a compressor, a combustor, and a turbine.

FIG. 2 is a schematic diagram of a portion of a turbine.

FIG. 3 is a perspective view of a portion of a nozzle with a number of internal cavities and a rib.

FIG. 4 is a partial perspective view of a nozzle with a number of cavity inserts positioned therein.

FIG. 5 is a partial perspective view of a nozzle assembly as may be described herein with a nozzle having a rib cap and a number of modified nozzle inserts positioned therein.

DETAILED DESCRIPTION

Referring now to the drawings, in which like numerals refer to like elements throughout the several views, FIG. 1 shows a schematic view of gas turbine engine 10 as may be used herein. The gas turbine engine 10 may include a compressor 15. The compressor 15 compresses an incoming flow of air 20. The compressor 15 delivers the compressed flow of air 20 to a combustor 25. The combustor 25 mixes the compressed flow of air 20 with a pressurized flow of fuel 30 and ignites the mixture to create a flow of combustion gases 35. Although only a single combustor 25 is shown, the gas turbine engine 10 may include any number of combustors 25. The flow of combustion gases 35 is in turn delivered to a turbine 40. The flow of combustion gases 35 drives the turbine 40 so as to produce mechanical work. The mechanical work produced in the turbine 40 drives the compressor 15 via a shaft 45 and an external load 50 such as an electrical generator and the like.
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.
FIG. 2 shows is a schematic diagram of a portion of the turbine 40. By way of example only, the figure shows a first stage 55, a second stage 60, and a third stage 65 of the turbine 40. Any number of stages may be used herein. As described above, each stage may include a number of circumferentially spaced nozzles 70 and buckets 75. The buckets 75 are mounted on a turbine rotor 80 for rotation therewith. The nozzles 70 are circumferentially spaced from one another and fixed about an axis of the rotor 80. Each nozzle 70 may include a nozzle airfoil 82. The airfoils 82 extend from an inner band 84 to an outer band 86. Other components and other configurations may be used herein.
FIG. 3 shows an example of one of the nozzles 70. The nozzle 70 may include a number of cavities extending through the airfoil 82. In this example, an aft cavity 88 and a forward cavity 90 are shown. The cavities 88, 90 may be divided by a rib 92. Any number of the cavities 88, 90 and the ribs 92 may be used in any size, shape, or configuration. The turbine 40 may have nozzles 70 with different cavity configurations. As is shown in FIG. 4, each of the cavities may be filled with an insert. In this example, an aft insert 94 and a forward insert 96 are shown. The inserts may have different configurations depending upon the intended nozzle of use and the intended position therein. As described above, the inserts may be physically similar but functionally different.
FIG. 5 shows a portion of a nozzle assembly 100 as may be described herein. The nozzle assembly 100 may have a number of nozzles 105 with a number of nozzle cavities 110 therein. In this example, an aft cavity 120 and a forward cavity 130 are shown. Any number of the cavities 110 may be used herein in any size, shape, or configuration although the aft cavities 120 and the forward cavities 130 may be substantially uniform in the nozzles 105 herein. The cavities 120, 130 may be separated by a rib 140. Any number of ribs 140 may be used herein in any size, shape, or configuration. A modified insert 150 may be installed in each of the cavities 110. In this example, a modified aft insert 160 and a modified forward insert 170 may be used. The modified inserts 150 may have any size, shape, or configuration depending upon the intended nozzle 100 of use and the position therein. The modified inserts 150 may have a number of perforations 175 therein.
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.

Claims

We claim:

1. A nozzle assembly for use in a turbine engine, comprising:

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;

wherein the rib cap comprises 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.

2. The nozzle assembly of claim 1, wherein the first nozzle cavity comprises an aft nozzle cavity.

3. The nozzle assembly of claim 1, wherein the second nozzle cavity comprises a forward nozzle cavity.

4. The nozzle assembly of claim 1, wherein the first cavity insert comprises a modified aft cavity insert.

5. The nozzle assembly of claim 1, wherein the second cavity insert comprises a modified forward cavity insert.

6. The nozzle assembly of claim 1, further comprising a plurality of nozzles.

7. The nozzle assembly of claim 6, wherein the plurality of nozzles comprises a plurality of first nozzle cavities and a plurality of second nozzle cavities.

8. The nozzle assembly of claim 7, wherein the plurality of first nozzle cavities and the plurality of second nozzle cavities comprise a common configuration.

9. The nozzle assembly of claim 6, wherein the plurality of nozzles comprises a plurality of first cavity inserts and a plurality of second cavity inserts.

10. The nozzle assembly of claim 9, wherein the plurality of first cavity inserts comprises a plurality of different first cavity insert configurations and wherein the plurality of second cavity inserts comprises a plurality of different second cavity insert configurations.

11. The nozzle assembly of claim 1, wherein the rib cap comprises a cast rib cap.

12. The nozzle assembly of claim 1, wherein the rib cap comprises a brazed rib cap or a welded rib cap.

13. The nozzle assembly of claim 1, further comprising a plurality of rib cap configurations.

14. The nozzle assembly of claim 1, wherein the first cavity insert and the second cavity insert comprise a plurality of perforations.

15. A method of assembling a nozzle assembly, comprising:

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.

16. A nozzle assembly for use in a turbine engine, comprising:

a plurality of nozzles;

the plurality of nozzles comprising a first nozzle cavity, a second nozzle cavity, and a rib positioned therebetween;

a plurality of first cavity inserts with a plurality of first insert configurations;

a plurality of second cavity inserts with a plurality of second insert configurations; and

a plurality of rib caps with a plurality of rib cap configurations.

17. The nozzle assembly of claim 16, wherein the plurality of nozzles comprises a plurality of first nozzle cavities with a first common configuration and a plurality of second nozzle cavities with a second common configuration.

18. The nozzle assembly of claim 16, wherein the plurality of first insert configurations comprises a plurality of first different configurations and wherein the plurality of second insert configurations comprises a plurality of second different configurations.

19. The nozzle assembly of claim 16, wherein only a first rib cap configuration can be used with the plurality of first cavity inserts.

20. The nozzle assembly of claim 16, wherein the plurality of rib caps comprises a cast rib cap, a brazed rib cap, or a welded rib cap.