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Title: Method of joining a vane cavity insert to a nozzle segment of a gas turbine

Abstract

An insert containing apertures for impingement cooling a nozzle vane of a nozzle segment in a gas turbine is inserted into one end of the vane. The leading end of the insert is positioned slightly past a rib adjacent the opposite end of the vane through which the insert is inserted. The end of the insert is formed or swaged into conformance with the inner margin of the rib. The insert is then brazed or welded to the rib.

Inventors:
 [1]
  1. Schenectady, NY
Issue Date:
Research Org.:
General Electric Co., Schenectady, NY (United States)
OSTI Identifier:
874744
Patent Number(s):
6453557
Assignee:
General Electric Company (Schenectady, NY)
Patent Classifications (CPCs):
F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
Y - NEW / CROSS SECTIONAL TECHNOLOGIES Y10 - TECHNICAL SUBJECTS COVERED BY FORMER USPC Y10T - TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
DOE Contract Number:  
FC21-95MC31176
Resource Type:
Patent
Country of Publication:
United States
Language:
English
Subject:
method; joining; vane; cavity; insert; nozzle; segment; gas; turbine; containing; apertures; impingement; cooling; inserted; leading; positioned; slightly; past; adjacent; opposite; formed; swaged; conformance; inner; margin; brazed; welded; gas turbine; nozzle segment; /29/

Citation Formats

Burdgick, Steven Sebastian. Method of joining a vane cavity insert to a nozzle segment of a gas turbine. United States: N. p., 2002. Web.
Burdgick, Steven Sebastian. Method of joining a vane cavity insert to a nozzle segment of a gas turbine. United States.
Burdgick, Steven Sebastian. Tue . "Method of joining a vane cavity insert to a nozzle segment of a gas turbine". United States. https://www.osti.gov/servlets/purl/874744.
@article{osti_874744,
title = {Method of joining a vane cavity insert to a nozzle segment of a gas turbine},
author = {Burdgick, Steven Sebastian},
abstractNote = {An insert containing apertures for impingement cooling a nozzle vane of a nozzle segment in a gas turbine is inserted into one end of the vane. The leading end of the insert is positioned slightly past a rib adjacent the opposite end of the vane through which the insert is inserted. The end of the insert is formed or swaged into conformance with the inner margin of the rib. The insert is then brazed or welded to the rib.},
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