Partially turbulated trailing edge cooling passages for gas turbine nozzles
Abstract
A plurality of passages are spaced one from the other along the length of a trailing edge of a nozzle vane in a gas turbine. The passages lie in communication with a cavity in the vane for flowing cooling air from the cavity through the passages through the tip of the trailing edge into the hot gas path. Each passage is partially turbulated and includes ribs in an aft portion thereof to provide enhanced cooling effects adjacent the tip of the trailing edge. The major portions of the passages are smooth bore. By this arrangement, reduced temperature gradients across the trailing edge metal are provided. Additionally, the inlets to each of the passages have a restriction whereby a reduced magnitude of compressor bleed discharge air is utilized for trailing edge cooling purposes.
- Inventors:
-
- Schenectady, NY
- Issue Date:
- Research Org.:
- General Electric Co., Schenectady, NY (United States)
- OSTI Identifier:
- 873559
- Patent Number(s):
- 6190120
- Assignee:
- General Electric Co. (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:
- partially; turbulated; trailing; edge; cooling; passages; gas; turbine; nozzles; plurality; spaced; length; nozzle; vane; lie; communication; cavity; flowing; air; tip; hot; path; passage; ribs; portion; provide; enhanced; effects; adjacent; major; portions; smooth; bore; arrangement; reduced; temperature; gradients; metal; provided; additionally; inlets; restriction; whereby; magnitude; compressor; bleed; discharge; utilized; purposes; nozzle vane; cooling passages; turbine nozzle; cooling air; temperature gradient; gas turbine; hot gas; major portion; trailing edge; reduced temperature; temperature gradients; provide enhanced; gas path; enhanced cooling; cooling purposes; discharge air; charge air; /415/416/
Citation Formats
Thatcher, Jonathan Carl, and Burdgick, Steven Sebastian. Partially turbulated trailing edge cooling passages for gas turbine nozzles. United States: N. p., 2001.
Web.
Thatcher, Jonathan Carl, & Burdgick, Steven Sebastian. Partially turbulated trailing edge cooling passages for gas turbine nozzles. United States.
Thatcher, Jonathan Carl, and Burdgick, Steven Sebastian. Mon .
"Partially turbulated trailing edge cooling passages for gas turbine nozzles". United States. https://www.osti.gov/servlets/purl/873559.
@article{osti_873559,
title = {Partially turbulated trailing edge cooling passages for gas turbine nozzles},
author = {Thatcher, Jonathan Carl and Burdgick, Steven Sebastian},
abstractNote = {A plurality of passages are spaced one from the other along the length of a trailing edge of a nozzle vane in a gas turbine. The passages lie in communication with a cavity in the vane for flowing cooling air from the cavity through the passages through the tip of the trailing edge into the hot gas path. Each passage is partially turbulated and includes ribs in an aft portion thereof to provide enhanced cooling effects adjacent the tip of the trailing edge. The major portions of the passages are smooth bore. By this arrangement, reduced temperature gradients across the trailing edge metal are provided. Additionally, the inlets to each of the passages have a restriction whereby a reduced magnitude of compressor bleed discharge air is utilized for trailing edge cooling purposes.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Mon Jan 01 00:00:00 EST 2001},
month = {Mon Jan 01 00:00:00 EST 2001}
}
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