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Turbine Nozzle-To-Shroud Interface

Inactive Publication Date: 2018-11-29
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

This patent describes a new design for a gas turbine and turbine that improve efficiency and performance. The design includes a nozzle, a compressor, a combustor, and a turbine section. The nozzle has an inner platform and an outer platform with an airfoil between them. The airfoil has a leading edge and a trailing edge, and a hook on the outer platform engages with a hook on the nozzle for support. The turbine section includes a radially outward sealing interface with an axial clearance between the nozzle and the turbine. This design improves sealing, reduces leakage, and increases efficiency of the gas turbine and turbine.

Problems solved by technology

Turbine efficiency may be reduced when some of the hot gas flowing through the turbine hot gas path is lost before it can produce work.

Method used

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  • Turbine Nozzle-To-Shroud Interface
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  • Turbine Nozzle-To-Shroud Interface

Examples

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Embodiment Construction

[0015]Reference will now be made in detail to present embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and description have been used to refer to like or similar parts of the invention.

[0016]As used herein, the terms “first”, “second”, and “third” may be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components. The terms “upstream” and “downstream” refer to the relative direction with respect to fluid flow in a fluid pathway. For example, “upstream” refers to the direction from which the fluid flows, and “downstream” refers to the direction to which the fluid flows. The term “radially” refers to the relative direction that is substantially perpendicular to an axial centerline of a particular co...

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PUM

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Abstract

A turbomachine includes a compressor, a combustor, and a turbine. The turbine includes a nozzle, a shroud, and an axial cavity defined between the nozzle and the shroud. The nozzle includes an inner platform, an outer platform spaced apart from the inner platform along a radial direction, and an airfoil extending therebetween. The outer platform extends axially between a forward sidewall and an aft sidewall. The nozzle also includes an aft hook radially outward of the outer platform and axially forward of the aft sidewall of the outer platform. The shroud includes a forward end adjacent to the aft sidewall of the outer platform. A sealing interface is positioned within the cavity, radially outward of the outer platform of the nozzle and axially forward of the aft sidewall of the outer platform of the nozzle.

Description

FIELD[0001]The present disclosure generally relates to a turbine for a turbomachine. More particularly, this disclosure relates to a turbine nozzle-to-shroud interface for a turbomachine.BACKGROUND[0002]A gas turbine, such as an industrial, aircraft, or marine gas turbine generally includes, in serial flow order, a compressor, a combustor and a turbine. The turbine has multiple stages with each stage including a row of turbine nozzles and an adjacent row of turbine rotor blades disposed downstream from the turbine nozzles. The turbine nozzles are held stationary within the turbine and the turbine rotor blades rotate with a rotor shaft. The various turbine stages define a hot gas path through the turbine.[0003]During operation, the compressor provides compressed air to the combustor. The compressed air is mixed with fuel and burned in a combustion chamber defined within the combustor to produce a high velocity stream of hot gas. The hot gas flows from the combustor into the hot gas p...

Claims

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Application Information

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IPC IPC(8): F01D11/00
CPCF01D11/005F01D9/042Y02T50/60
Inventor ROBERTS, JR., FREDERIC WOODROWVEDHAGIRI, SIVARAMAN
Owner GENERAL ELECTRIC CO