Apparatus and method for a gas turbine nozzle
A nozzle includes an inlet, an outlet, and an axial centerline. A shroud surrounding the axial centerline extends from the inlet to the outlet and defines a circumference. The circumference proximate the inlet is greater than the circumference at a first point downstream of the inlet, and the circumference at the first point downstream of the inlet is less than the circumference at a second point downstream of the first point. A method for supplying a fuel through a nozzle directs a first airflow along a first path and a second airflow along a second path separate from the first path. The method further includes injecting the fuel into at least one of the first path or the second path and accelerating at least one of the first airflow or the second airflow.
- Research Organization:
- General Electric Co., Schenectady, NY (United States)
- Sponsoring Organization:
- USDOE
- DOE Contract Number:
- FC26-05NT42643
- Assignee:
- General Electric Company (Schenectady, NY)
- Patent Number(s):
- 8,365,532
- Application Number:
- 12/570,678
- OSTI ID:
- 1083236
- Country of Publication:
- United States
- Language:
- English
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