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Title: Steam exit flow design for aft cavities of an airfoil

Abstract

Turbine stator vane segments have inner and outer walls with vanes extending therebetween. The inner and outer walls have impingement plates. Steam flowing into the outer wall passes through the impingement plate for impingement cooling of the outer wall surface. The spent impingement steam flows into cavities of the vane having inserts for impingement cooling the walls of the vane. The steam passes into the inner wall and through the impingement plate for impingement cooling of the inner wall surface and for return through return cavities having inserts for impingement cooling of the vane surfaces. A skirt or flange structure is provided for shielding the steam cooling impingement holes adjacent the inner wall aerofoil fillet region of the nozzle from the steam flow exiting the aft nozzle cavities. Moreover, the gap between the flash rib boss and the cavity insert is controlled to minimize the flow of post impingement cooling media therebetween. This substantially confines outflow to that exiting via the return channels, thus furthermore minimizing flow in the vicinity of the aerofoil fillet region that may adversely affect impingement cooling thereof.

Inventors:
 [1];  [2]
  1. Clifton Park, NY
  2. Simpsonville, SC
Issue Date:
Research Org.:
General Electric Co., Schenectady, NY (United States)
OSTI Identifier:
874478
Patent Number(s):
6398486
Assignee:
General Electric Company (Schnectady, NY)
Patent Classifications (CPCs):
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
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:
steam; exit; flow; design; cavities; airfoil; turbine; stator; vane; segments; inner; outer; walls; vanes; extending; therebetween; impingement; plates; flowing; wall; passes; plate; cooling; surface; spent; flows; inserts; return; surfaces; skirt; flange; structure; provided; shielding; holes; adjacent; aerofoil; fillet; region; nozzle; exiting; moreover; gap; flash; boss; cavity; insert; controlled; minimize; post; media; substantially; confines; outflow; via; channels; furthermore; minimizing; vicinity; adversely; affect; steam flow; vanes extend; /415/416/

Citation Formats

Storey, James Michael, and Tesh, Stephen William. Steam exit flow design for aft cavities of an airfoil. United States: N. p., 2002. Web.
Storey, James Michael, & Tesh, Stephen William. Steam exit flow design for aft cavities of an airfoil. United States.
Storey, James Michael, and Tesh, Stephen William. Tue . "Steam exit flow design for aft cavities of an airfoil". United States. https://www.osti.gov/servlets/purl/874478.
@article{osti_874478,
title = {Steam exit flow design for aft cavities of an airfoil},
author = {Storey, James Michael and Tesh, Stephen William},
abstractNote = {Turbine stator vane segments have inner and outer walls with vanes extending therebetween. The inner and outer walls have impingement plates. Steam flowing into the outer wall passes through the impingement plate for impingement cooling of the outer wall surface. The spent impingement steam flows into cavities of the vane having inserts for impingement cooling the walls of the vane. The steam passes into the inner wall and through the impingement plate for impingement cooling of the inner wall surface and for return through return cavities having inserts for impingement cooling of the vane surfaces. A skirt or flange structure is provided for shielding the steam cooling impingement holes adjacent the inner wall aerofoil fillet region of the nozzle from the steam flow exiting the aft nozzle cavities. Moreover, the gap between the flash rib boss and the cavity insert is controlled to minimize the flow of post impingement cooling media therebetween. This substantially confines outflow to that exiting via the return channels, thus furthermore minimizing flow in the vicinity of the aerofoil fillet region that may adversely affect impingement cooling thereof.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2002},
month = {1}
}

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