Method and apparatus for regulating fluid flow through a turbine engine
A method for regulating fluid flow through a gas turbine engine is provided. The method includes coupling an outer fairing to a radially outer duct wall and coupling an inner fairing to a radially inner duct wall. An annular valve is coupled between the radially outer and the radially inner duct walls such that an outer bypass flow area is at least partially defined between the annular valve and the outer fairing, and such that an inner bypass flow area is at least partially defined between the annular valve and the inner fairing. The annular valve is selectively positioned between a first operational position and a second operational position, such that at least one of the outer bypass and the inner bypass flow areas is varied during a transition from a first turbine operation to a second turbine operation.
1. A method for regulating fluid flow through a gas turbine engine, said method comprises:
coupling an outer fairing to a radially outer duct wall;
coupling an inner fairing to a radially inner duct wall;
coupling an annular valve between the radially outer and radially inner duct walls such that an outer bypass flow area is at least partially defined between the annular valve and the outer fairing, and such that an inner bypass flow area is at least partially defined between the annular valve and the inner fairing; and
selectively positioning the annular valve between a first operational position and a second operational position, such that at least one of the outer bypass and the inner bypass flow areas is varied during a transition from a first turbine operation to a second turbine operation.
2. A method in accordance with claim 1 further comprising coupling an actuator to the annular valve to control movement of the valve relative to the outer and inner fairings.
3. A method in accordance with claim 1 further comprising:
coupling an actuation system including at least one crank to the annular valve; and
selectively positioning the annular valve using the at least one crank.
4. A method in accordance with claim 1 wherein selectively positioning the annular valve between a first operational position and a second operational position further comprises selectively positioning the annular valve to facilitate discharging fluid flow from the engine in a direction that is substantially perpendicular to a centerline of the turbine engine.
5. A method in accordance with claim 1 wherein selectively positioning the annular valve between a first operational position and a second operational position further comprises selectively positioning the annular valve to facilitate discharging fluid flow from the turbine engine in a direction that is substantially parallel to a centerline of the turbine engine.
6. A method in accordance with claim 1 wherein selectively positioning the annular valve between a first operational position and a second operational position further comprises selectively positioning the annular valve at a predetermined location wherein the flow areas of the outer bypass and the inner bypass are facilitated to be minimized.
7. A method in accordance with claim 1 wherein selectively positioning the annular valve between a first operational position and a second operational position further comprises selectively positioning the annular valve at a predetermined location wherein the flow areas of the outer bypass and the inner bypass are facilitated to be maximized.
8. A valve assembly for a gas turbine engine, said valve assembly comprising:
an outer fairing coupled to a radially outer duct wall;
an inner fairing coupled to a radially inner duct wall; and
an annular valve slidably coupled between said radially outer and said radially inner duct walls such that an outer flow area is at least partially defined between said annular valve and said outer fairing, and such that an inner flow area is at least partially defined between said annular valve and said inner fairing, said annular valve is selectively positionable between a first operational position and a second operational position to vary a flow through at least one of said outer and said inner flow areas.
9. A valve assembly in accordance with claim 8 further comprising a crank assembly coupled to said annular valve to facilitate displacing said annular valve relative to said outer and said inner fairings.
10. A valve assembly in accordance with claim 9 further comprising an actuator coupled to said crank assembly to facilitate positioning said annular valve relative to said outer and said inner fairings.
11. A valve assembly in accordance with claim 8 wherein said annular valve is selectively positionable to facilitate discharging a fluid flow from the turbine engine in a direction that is substantially perpendicular to a centerline of the turbine.
12. A valve assembly in accordance with claim 8 wherein said annular valve is selectively positionable to facilitate discharging a fluid flow from the turbine engine in a direction that is substantially parallel to a centerline of the turbine.
13. A valve assembly in accordance with claim 8 wherein said inner fairing comprises contours that facilitate varying said inner flow area, and said outer fairing comprises contours that facilitate varying said outer flow area.
14. A gas turbine engine comprising:
a fan assembly;
a fan bypass duct coupled to the fan assembly; and
an augmentor valve assembly coupled downstream from the fan assembly within said fan bypass duct, said augmentor valve assembly comprising:
an outer fairing coupled to a radially outer fan bypass duct wall;
an inner fairing coupled to a radially inner fan bypass duct wall; and
an annular valve slidably coupled between said radially outer and said radially inner fan bypass duct walls, said annular valve is selectively positionable between a first operational position and a second operational position to vary a flow through at least one of an outer bypass flow area and an inner bypass flow area.
15. A gas turbine engine in accordance with claim 14 wherein said outer bypass flow area is at least partially defined between said annular valve and said outer fairing, and said inner bypass flow area is at least partially defined between said annular valve and said inner fairing.
16. A gas turbine engine in accordance with claim 15 wherein said annular valve is selectively positionable to facilitate discharging a fluid flow from the gas turbine engine in a direction that is substantially perpendicular to a centerline of the turbine engine.
17. A gas turbine engine in accordance with claim 15 said annular valve is selectively positionable to facilitate discharging a fluid flow from the gas turbine engine in a direction that is substantially parallel to a centerline of the turbine engine.
18. A gas turbine engine in accordance with claim 15 wherein said inner fairing comprises contours that facilitate varying said inner bypass flow area, and said outer fairing comprises contours that facilitate varying said outer bypass flow area.
19. A gas turbine engine in accordance with claim 14 wherein said augmentor valve assembly further comprises a crank assembly coupled to said annular valve to facilitate displacing said annular valve relative to said outer and said inner fairings.
20. A gas turbine engine in accordance with claim 19 wherein said augmentor valve assembly further comprises an actuator coupled to said crank assembly to facilitate positioning said annular valve relative to said outer and said inner fairings.