Fuel nozzle for a combustor of a gas turbine engine
Patent
·
OSTI ID:1243327
A fuel nozzle for a gas turbine generally includes a main body having an upstream end axially separated from a downstream end. The main body at least partially defines a fuel supply passage that extends through the upstream end and at least partially through the main body. A fuel distribution manifold is disposed at the downstream end of the main body. The fuel distribution manifold includes a plurality of axially extending passages that extend through the fuel distribution manifold. A plurality of fuel injection ports defines a flow path between the fuel supply passage and each of the plurality of axially extending passages.
- Research Organization:
- GENERAL ELECTRIC COMPANY, Schenectady, NY (United States)
- Sponsoring Organization:
- USDOE
- DOE Contract Number:
- FC26-05NT42643
- Assignee:
- GENERAL ELECTRIC COMPANY (Schenectady, NY)
- Patent Number(s):
- 9,291,103
- Application Number:
- 13/705,443
- OSTI ID:
- 1243327
- Country of Publication:
- United States
- Language:
- English
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