Radial flow fuel nozzle for a combustor of a gas turbine
Abstract
A combustor for a gas turbine generally includes a radial flow fuel nozzle having a fuel distribution manifold, and a fuel injection manifold axially separated from the fuel distribution manifold. The fuel injection manifold generally includes an inner side portion, an outer side portion, and a plurality of circumferentially spaced fuel ports that extend through the outer side portion. A plurality of tubes provides axial separation between the fuel distribution manifold and the fuel injection manifold. Each tube defines a fluid communication path between the fuel distribution manifold and the fuel injection manifold.
- Inventors:
- Issue Date:
- Research Org.:
- General Electric Co., Schenectady, NY (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1260244
- Patent Number(s):
- 9383098
- Application Number:
- 13/664,705
- Assignee:
- General Electric Company
- Patent Classifications (CPCs):
-
F - MECHANICAL ENGINEERING F23 - COMBUSTION APPARATUS F23D - BURNERS
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:
- FC26-05NT42643
- Resource Type:
- Patent
- Resource Relation:
- Patent File Date: 2012 Oct 31
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 33 ADVANCED PROPULSION SYSTEMS; 42 ENGINEERING
Citation Formats
Means, Gregory Scott, Boardman, Gregory Allen, and Berry, Jonathan Dwight. Radial flow fuel nozzle for a combustor of a gas turbine. United States: N. p., 2016.
Web.
Means, Gregory Scott, Boardman, Gregory Allen, & Berry, Jonathan Dwight. Radial flow fuel nozzle for a combustor of a gas turbine. United States.
Means, Gregory Scott, Boardman, Gregory Allen, and Berry, Jonathan Dwight. Tue .
"Radial flow fuel nozzle for a combustor of a gas turbine". United States. https://www.osti.gov/servlets/purl/1260244.
@article{osti_1260244,
title = {Radial flow fuel nozzle for a combustor of a gas turbine},
author = {Means, Gregory Scott and Boardman, Gregory Allen and Berry, Jonathan Dwight},
abstractNote = {A combustor for a gas turbine generally includes a radial flow fuel nozzle having a fuel distribution manifold, and a fuel injection manifold axially separated from the fuel distribution manifold. The fuel injection manifold generally includes an inner side portion, an outer side portion, and a plurality of circumferentially spaced fuel ports that extend through the outer side portion. A plurality of tubes provides axial separation between the fuel distribution manifold and the fuel injection manifold. Each tube defines a fluid communication path between the fuel distribution manifold and the fuel injection manifold.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2016},
month = {7}
}
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