Claims
- 1. A fuel injector for a combustor in a gas turbine engine, the injector having an injector tip assembly, the injector tip assembly having a tip axis and comprising a machined body having a central axial recess defining a fuel chamber, an insert member including an axial nozzle for passing fuel to the combustor, and a valve for metering the fuel through the axial nozzle, the valve comprising a spiral vane disposed within the fuel chamber to provide a spiral fuel flow path through a portion of the fuel chamber to the nozzle.
- 2. A fuel injector for a combustor in a gas turbine engine as defined in claim 1, wherein the injector tip protrudes within the combustor and the spiral vane is coaxial with the tip axis passing through the axial nozzle, the valve further including a stem which extends into the axial nozzle along the tip axis to block the axial nozzle when primary fuel is not required.
CROSS-REFERENCE TO RELATED APPLICATION
This application is a divisional application of Ser. No. 09/083,199, filed May 22, 1998, now U.S. Pat. No. 6,082,113.
US Referenced Citations (6)
Foreign Referenced Citations (1)
Number |
Date |
Country |
493434 |
Nov 1938 |
GB |