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:
-
- 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
- Bannister, R. L.; Cheruvu, N. S.; Little, D. A.
- Journal of Engineering for Gas Turbines and Power, Vol. 117, Issue 4
Advances in Steam Path Technology
journal, April 1996
- Cofer, J. I.
- Journal of Engineering for Gas Turbines and Power, Vol. 118, Issue 2