Apparatus and methods for impingement cooling of a side wall of a turbine nozzle segment
Abstract
A gas turbine nozzle segment has outer and inner bands and a vane therebetween. Each band includes a nozzle wall, a side wall, a cover and an impingement plate between the cover and the 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 and inturned flange define with the nozzle wall an undercut region. The impingement plate has a turned flange welded to the inturned flange. A backing plate overlies the turned flange and aligned apertures are formed through the backing plate and turned flange to direct and focus cooling flow onto the side wall of the nozzle segment.
- Inventors:
-
- Schenectady, NY
- Issue Date:
- Research Org.:
- General Electric Co., Schenectady, NY (United States)
- OSTI Identifier:
- 874421
- Patent Number(s):
- 6386825
- 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
F - MECHANICAL ENGINEERING F05 - INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04 F05D - INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- DOE Contract Number:
- FC21-95MC31176
- Resource Type:
- Patent
- Country of Publication:
- United States
- Language:
- English
- Subject:
- apparatus; methods; impingement; cooling; wall; turbine; nozzle; segment; gas; outer; inner; bands; vane; therebetween; band; cover; plate; defining; cavities; opposite; steam; supplied; cavity; flow; apertures; cool; inturned; flange; define; undercut; region; welded; overlies; aligned; formed; direct; focus; gas turbine; turbine nozzle; nozzle segment; /415/
Citation Formats
Burdgick, Steven Sebastian. Apparatus and methods for impingement cooling of a side wall of a turbine nozzle segment. United States: N. p., 2002.
Web.
Burdgick, Steven Sebastian. Apparatus and methods for impingement cooling of a side wall of a turbine nozzle segment. United States.
Burdgick, Steven Sebastian. Tue .
"Apparatus and methods for impingement cooling of a side wall of a turbine nozzle segment". United States. https://www.osti.gov/servlets/purl/874421.
@article{osti_874421,
title = {Apparatus and methods for impingement cooling of a side wall of a turbine nozzle segment},
author = {Burdgick, Steven Sebastian},
abstractNote = {A gas turbine nozzle segment has outer and inner bands and a vane therebetween. Each band includes a nozzle wall, a side wall, a cover and an impingement plate between the cover and the 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 and inturned flange define with the nozzle wall an undercut region. The impingement plate has a turned flange welded to the inturned flange. A backing plate overlies the turned flange and aligned apertures are formed through the backing plate and turned flange to direct and focus cooling flow onto the side wall of the nozzle segment.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Jan 01 00:00:00 EST 2002},
month = {Tue Jan 01 00:00:00 EST 2002}
}