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Title: Method of controlling the side wall thickness of a turbine nozzle segment for improved cooling

Abstract

A gas turbine nozzle segment has outer and inner bands and a vane extending therebetween. Each band has a side wall, a cover and an impingement plate between the cover and nozzle wall defining two cavities on opposite sides of the impingement plate. Cooling steam is supplied to one cavity for flow through apertures of the impingement plate to cool the nozzle wall. The side wall of the band has an inturned flange defining with the nozzle wall an undercut region. The outer surface of the side wall is provided with a step prior to welding the cover to the side wall. A thermal barrier coating is applied in the step and, after the cover is welded to the side wall, the side wall is finally machined to a controlled thickness removing all, some or none of the coating.

Inventors:
 [1]
  1. Schenectady, NY
Issue Date:
Research Org.:
General Electric Co., Schenectady, NY (United States)
OSTI Identifier:
874574
Patent Number(s):
6418618
Assignee:
General Electric Company (Schenectady, NY)
Patent Classifications (CPCs):
Y - NEW / CROSS SECTIONAL TECHNOLOGIES Y10 - TECHNICAL SUBJECTS COVERED BY FORMER USPC Y10T - TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
DOE Contract Number:  
FC21-95MC31176
Resource Type:
Patent
Country of Publication:
United States
Language:
English
Subject:
method; controlling; wall; thickness; turbine; nozzle; segment; improved; cooling; gas; outer; inner; bands; vane; extending; therebetween; band; cover; impingement; plate; defining; cavities; opposite; steam; supplied; cavity; flow; apertures; cool; inturned; flange; undercut; region; surface; provided; step; prior; welding; thermal; barrier; coating; applied; welded; finally; machined; controlled; removing; gas turbine; turbine nozzle; nozzle segment; /29/

Citation Formats

Burdgick, Steven Sebastian. Method of controlling the side wall thickness of a turbine nozzle segment for improved cooling. United States: N. p., 2002. Web.
Burdgick, Steven Sebastian. Method of controlling the side wall thickness of a turbine nozzle segment for improved cooling. United States.
Burdgick, Steven Sebastian. Tue . "Method of controlling the side wall thickness of a turbine nozzle segment for improved cooling". United States. https://www.osti.gov/servlets/purl/874574.
@article{osti_874574,
title = {Method of controlling the side wall thickness of a turbine nozzle segment for improved cooling},
author = {Burdgick, Steven Sebastian},
abstractNote = {A gas turbine nozzle segment has outer and inner bands and a vane extending therebetween. Each band has a side wall, a cover and an impingement plate between the cover and nozzle wall defining two cavities on opposite sides of the impingement plate. Cooling steam is supplied to one cavity for flow through apertures of the impingement plate to cool the nozzle wall. The side wall of the band has an inturned flange defining with the nozzle wall an undercut region. The outer surface of the side wall is provided with a step prior to welding the cover to the side wall. A thermal barrier coating is applied in the step and, after the cover is welded to the side wall, the side wall is finally machined to a controlled thickness removing all, some or none of the coating.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2002},
month = {1}
}

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Works referenced in this record:

Development Requirements for an Advanced Gas Turbine System
journal, October 1995


Advances in Steam Path Technology
journal, April 1996