Rapid-quench axially staged combustor
Abstract
A combustor cooperating with a compressor in driving a gas turbine includes a cylindrical outer combustor casing. A combustion liner, having an upstream rich section, a quench section and a downstream lean section, is disposed within the outer combustor casing defining a combustion chamber having at least a core quench region and an outer quench region. A first plurality of quench holes are disposed within the liner at the quench section having a first diameter to provide cooling jet penetration to the core region of the quench section of the combustion chamber. A second plurality of quench holes are disposed within the liner at the quench section having a second diameter to provide cooling jet penetration to the outer region of the quench section of the combustion chamber. In an alternative embodiment, the combustion chamber quench section further includes at least one middle region and at least a third plurality of quench holes disposed within the liner at the quench section having a third diameter to provide cooling jet penetration to at least one middle region of the quench section of the combustion chamber.
- Inventors:
-
- Niskayuna, NY
- Clifton Park, NY
- Issue Date:
- Research Org.:
- General Electric Co., Boston, MA (United States)
- OSTI Identifier:
- 872722
- Patent Number(s):
- 5996351
- Assignee:
- General Electric Company (Schenectady, NY)
- Patent Classifications (CPCs):
-
F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23R - GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- DOE Contract Number:
- AC21-87MC23170
- Resource Type:
- Patent
- Country of Publication:
- United States
- Language:
- English
- Subject:
- rapid-quench; axially; staged; combustor; cooperating; compressor; driving; gas; turbine; cylindrical; outer; casing; combustion; liner; upstream; rich; section; quench; downstream; lean; disposed; defining; chamber; core; region; plurality; holes; diameter; provide; cooling; jet; penetration; alternative; embodiment; middle; third; provide cooling; cylindrical outer; combustion chamber; gas turbine; alternative embodiment; core region; holes disposed; combustor casing; stream rich; combustion liner; third plurality; /60/
Citation Formats
Feitelberg, Alan S, Schmidt, Mark Christopher, and Goebel, Steven George. Rapid-quench axially staged combustor. United States: N. p., 1999.
Web.
Feitelberg, Alan S, Schmidt, Mark Christopher, & Goebel, Steven George. Rapid-quench axially staged combustor. United States.
Feitelberg, Alan S, Schmidt, Mark Christopher, and Goebel, Steven George. Fri .
"Rapid-quench axially staged combustor". United States. https://www.osti.gov/servlets/purl/872722.
@article{osti_872722,
title = {Rapid-quench axially staged combustor},
author = {Feitelberg, Alan S and Schmidt, Mark Christopher and Goebel, Steven George},
abstractNote = {A combustor cooperating with a compressor in driving a gas turbine includes a cylindrical outer combustor casing. A combustion liner, having an upstream rich section, a quench section and a downstream lean section, is disposed within the outer combustor casing defining a combustion chamber having at least a core quench region and an outer quench region. A first plurality of quench holes are disposed within the liner at the quench section having a first diameter to provide cooling jet penetration to the core region of the quench section of the combustion chamber. A second plurality of quench holes are disposed within the liner at the quench section having a second diameter to provide cooling jet penetration to the outer region of the quench section of the combustion chamber. In an alternative embodiment, the combustion chamber quench section further includes at least one middle region and at least a third plurality of quench holes disposed within the liner at the quench section having a third diameter to provide cooling jet penetration to at least one middle region of the quench section of the combustion chamber.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Fri Jan 01 00:00:00 EST 1999},
month = {Fri Jan 01 00:00:00 EST 1999}
}
Works referenced in this record:
Environmental aspects of low Btu gas combustion
journal, January 1977
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- Symposium (International) on Combustion, Vol. 16, Issue 1
Low NO/sub x/ Heavy Fuel Combustor Concept Program. Phase I. Final report
report, October 1981
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Design and Performance of Low Heating Value Fuel Gas Turbine Combustors
conference, February 2015
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