Nozzle cavity impingement/area reduction insert
Abstract
A turbine vane segment is provided that has inner and outer walls spaced from one another, a vane extending between the inner and outer walls and having leading and trailing edges and pressure and suction sides, the vane including discrete leading edge, intermediate, aft and trailing edge cavities between the leading and trailing edges and extending lengthwise of the vane for flowing a cooling medium; and an insert sleeve within at least one of the cavities and spaced from interior wall surfaces thereof. The insert sleeve has an inlet for flowing the cooling medium into the insert sleeve and has impingement holes defined in first and second walls thereof that respectively face the pressure and suction sides of the vane. The impingement holes of at least one of those first and second walls are defined along substantially only a first, upstream portion thereof, whereby the cooling flow is predominantly impingement cooling along a first region of the insert wall corresponding to the first, upstream portion and the cooling flow is predominantly convective cooling along a second region corresponding to a second, downstream portion of the at least one wall of the insert sleeve.
- Inventors:
-
- Simpsonville, SC
- East Thetford, VT
- Issue Date:
- Research Org.:
- General Electric Co., Schenectady, NY (United States)
- OSTI Identifier:
- 874818
- Patent Number(s):
- 6468031
- 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:
- nozzle; cavity; impingementarea; reduction; insert; turbine; vane; segment; provided; inner; outer; walls; spaced; extending; leading; trailing; edges; pressure; suction; including; discrete; edge; intermediate; cavities; lengthwise; flowing; cooling; medium; sleeve; interior; wall; surfaces; inlet; impingement; holes; defined; substantially; upstream; portion; flow; predominantly; region; convective; downstream; cooling medium; turbine vane; /415/416/
Citation Formats
Yu, Yufeng Phillip, Itzel, Gary Michael, and Osgood, Sarah Jane. Nozzle cavity impingement/area reduction insert. United States: N. p., 2002.
Web.
Yu, Yufeng Phillip, Itzel, Gary Michael, & Osgood, Sarah Jane. Nozzle cavity impingement/area reduction insert. United States.
Yu, Yufeng Phillip, Itzel, Gary Michael, and Osgood, Sarah Jane. Tue .
"Nozzle cavity impingement/area reduction insert". United States. https://www.osti.gov/servlets/purl/874818.
@article{osti_874818,
title = {Nozzle cavity impingement/area reduction insert},
author = {Yu, Yufeng Phillip and Itzel, Gary Michael and Osgood, Sarah Jane},
abstractNote = {A turbine vane segment is provided that has inner and outer walls spaced from one another, a vane extending between the inner and outer walls and having leading and trailing edges and pressure and suction sides, the vane including discrete leading edge, intermediate, aft and trailing edge cavities between the leading and trailing edges and extending lengthwise of the vane for flowing a cooling medium; and an insert sleeve within at least one of the cavities and spaced from interior wall surfaces thereof. The insert sleeve has an inlet for flowing the cooling medium into the insert sleeve and has impingement holes defined in first and second walls thereof that respectively face the pressure and suction sides of the vane. The impingement holes of at least one of those first and second walls are defined along substantially only a first, upstream portion thereof, whereby the cooling flow is predominantly impingement cooling along a first region of the insert wall corresponding to the first, upstream portion and the cooling flow is predominantly convective cooling along a second region corresponding to a second, downstream portion of the at least one wall of the insert sleeve.},
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}
}
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