초록 ▼

A method of assembling a seal assembly for a turbine engine is provided, wherein the method includes providing a seal ring having an arcuate inner ring portion, an arcuate outer ring portion, and a neck portion extending therebetween, and forming at least one recess within at least one of the outer

A method of assembling a seal assembly for a turbine engine is provided, wherein the method includes providing a seal ring having an arcuate inner ring portion, an arcuate outer ring portion, and a neck portion extending therebetween, and forming at least one recess within at least one of the outer ring portion and the neck portion. The method also includes extending a biasing mechanism across the seal ring such that the biasing mechanism is positively retained within the at least one recess.

대표청구항 ▼

What is claimed is: 1. A method of assembling a seal assembly for a turbine engine, said method comprising: providing a seal ring having an arcuate inner ring portion, an arcuate outer ring portion, and a neck portion extending therebetween; forming at least one recess within at least one of the ou

What is claimed is: 1. A method of assembling a seal assembly for a turbine engine, said method comprising: providing a seal ring having an arcuate inner ring portion, an arcuate outer ring portion, and a neck portion extending therebetween; forming at least one recess within at least one of the outer ring portion and the neck portion, wherein a first aperture and a second aperture that are formed are each sized to receive a tab extending from each end of a biasing mechanism; and extending the biasing mechanism across the seal ring such that the biasing mechanism is positively retained within the at least one recess. 2. A method in accordance with claim 1 wherein forming at least one recess comprises forming a cavity having a pair of opposed side walls, wherein extending a biasing mechanism across the seal ring further comprises extending the biasing mechanism between the pair of sidewalls. 3. A method in accordance with claim 2 further comprising retaining the biasing mechanism within the cavity with at least one of a pin, a screw, glue, and a tack weld. 4. A method in accordance with claim 2 wherein said forming a cavity further comprises forming a notch within each of the two side walls, wherein extending the biasing mechanism between the pair of sidewalls comprises inserting a first end of the biasing mechanism in a first notch and a second end of a biasing mechanism in a second notch such that the biasing mechanism is retained between the notches. 5. A method in accordance with claim 4 wherein each end of the biasing mechanism is formed with a tab extending therefrom, said positively retaining the biasing mechanism further comprises configuring each notch to receive one of the tabs. 6. A method in accordance with claim 1 wherein said forming at least one recess comprises forming a pair of threaded apertures that are each sized to receive a threaded fastener therein for securing the biasing mechanism therebetween. 7. A seal assembly for a turbine engine, said seal assembly comprising: a seal ring comprising an arcuate inner ring portion, an arcuate outer ring portion, and a neck portion extending therebetween; at least one recess formed within at least one of said seal ring outer ring portion and said seal ring neck portion, said at least one recess comprises a first aperture and a second aperture; and a biasing mechanism extending chordially across said seal ring, a first end of said biasing mechanism received within said first aperture, a second end of said biasing mechanism received within said second aperture such that said biasing mechanism is retained within said at least one recess. 8. A seal assembly in accordance with claim 7 wherein said recess comprises a cavity having two side walls, said biasing mechanism extends between said two side walls. 9. A seal assembly in accordance with claim 8 wherein said biasing mechanism is retained within said cavity by at least one of a pin, a screw, glue, and a tack weld. 10. A seal assembly in accordance with claim 8 wherein said cavity further comprises a notch formed within each of said two side walls, each said notch sized to receive an end of said biasing mechanism such that said biasing mechanism is suspended between said notches. 11. A seal assembly in accordance with claim 10 wherein said biasing mechanism comprises a tab extending from each end, each said notch sized to receive one of said tabs. 12. A seal assembly in accordance with claim 7 wherein said at least one recess comprises a pair of threaded apertures that are each sized to receive a threaded fastener therein for securing the biasing mechanism therebetween. 13. A turbine engine comprising: a seal assembly configured to reduce steam leakage within the turbine engine, said seal assembly comprising: a seal ring comprising an arcuate inner ring portion, an arcuate outer ring portion, and a neck portion extending therebetween; at least one recess formed within at least one of said seal ring outer ring portion and said seal ring neck portion, said at least one recess comprises a first aperture and a second aperture; and a biasing mechanism extending chordially across said seal ring, a first end of said biasing mechanism received within said first aperture, a second end of said biasing mechanism received within said second aperture such that said biasing mechanism is retained within said at least one recess. 14. A turbine engine in accordance with claim 13 wherein said recess comprises a cavity having two side walls, said biasing mechanism extends between said two side walls. 15. A turbine engine in accordance with claim 14 wherein said biasing mechanism is retained within said cavity by at least one of a pin, a screw, glue, and a tack weld. 16. A turbine engine in accordance with claim 14 wherein said cavity further comprises a notch formed within each of said two side walls, each said notch sized to receive an end of said biasing mechanism such that said biasing mechanism is suspended between said notches. 17. A turbine engine in accordance with claim 16 wherein said biasing mechanism comprises a tab extending from each end, each said notch sized to receive one of said tabs.