Nozzle Insert Rib Cap

Inactive Publication Date: 2014-12-04
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The patent describes a nozzle assembly for a turbine engine. The assembly includes a first nozzle cavity, a second nozzle cavity, a rib positioned between the two cavities, and two cavity inserts with different configurations. There are also rib caps with different configurations, which can only fit with the corresponding cavity insert. The technical effect is the creation of a nozzle assembly that allows for more flexibility in the design of the nozzle in order to improve performance and efficiency.

Problems solved by technology

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.
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.

Method used

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Experimental program
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Embodiment Construction

[0014]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.

[0015]The gas turbine engine 10 may us...

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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[0001]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[0002]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.[0003]The nozzle cooling schemes may use internal nozzle cavity inserts of va...

Claims

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Application Information

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IPC IPC(8): F01D9/02
CPCF01D9/02F01D5/189F01D9/065Y10T29/49323
InventorDAVIS, III, CHARLES LEWISBRUNNER, FREDERICK JAMES
OwnerGENERAL ELECTRIC CO