초록 ▼

A gas turbine engine includes a non-rotatable member that includes a honeycomb seal that reduces wear to rotor seal teeth disposed within the gas turbine engine. The gas turbine engine also includes a rotatable annular member including a sealing assembly disposed between rotor and stator components.

A gas turbine engine includes a non-rotatable member that includes a honeycomb seal that reduces wear to rotor seal teeth disposed within the gas turbine engine. The gas turbine engine also includes a rotatable annular member including a sealing assembly disposed between rotor and stator components. The rotatable annular member includes seal teeth that extend radially outward from the rotatable annular member. The stator components include a non-rotatable member that includes a honeycomb seal that extends radially inward. The honeycomb seal is fabricated from a material that has a melting temperature less than approximately 2000° F.

대표청구항 ▼

1. A method for assembling a gas turbine engine, said method comprising the steps of: fabricating a honeycomb seal from a material having a melting temperature less than approximately 2000° F. and securing the seal within the gas turbine engine. 2. A method in accordance with claim 1 wherein s

1. A method for assembling a gas turbine engine, said method comprising the steps of: fabricating a honeycomb seal from a material having a melting temperature less than approximately 2000° F. and securing the seal within the gas turbine engine. 2. A method in accordance with claim 1 wherein said step of fabricating a honeycomb seal further comprises the step of fabricating a honeycomb seal from a material having a melting temperature greater than approximately 1600° F. 3. A method in accordance with claim 1 wherein the gas turbine engine includes a plurality of rotor seal teeth, said step of fabricating a honeycomb seal further comprises the step of fabricating a honeycomb seal from a material having a reduced propensity to crack initiation of the rotor seal teeth. 4. A method in accordance with claim 1 wherein said step of fabricating a honeycomb seal further comprises the step of fabricating a honeycomb seal from a material having a melting temperature approximately equal 1050° F. 5. A honeycomb seal for a gas turbine engine, said seal comprising a material having a melting temperature less than approximately 2000° F., the gas turbine engine including a plurality of seal teeth, said honeycomb seal configured to reduce an operating temperature of the seal teeth as the seal teeth rub said honeycomb seal. 6. A honeycomb seal in accordance with claim 5 wherein the gas turbine engine includes a plurality of seal teeth, said honeycomb seal configured to reduce wear of the seal teeth as the seal teeth rub said honeycomb seal. 7. A honeycomb seal in accordance with claim 5 wherein the gas turbine engine includes a plurality of rotor seal teeth, said material configured to facilitate reducing a propensity of crack initiation within the gas turbine engine rotor seal teeth. 8. A honeycomb seal in accordance with claim 7 wherein said material further configured to facilitate reducing fatigue degradation of rotor seal teeth. 9. A honeycomb seal in accordance with claim 5 wherein said material has a melting temperature greater than approximately 1600° F. 10. A honeybcomb seal in accordance with claim 5 wherein the gas turbine engine includes a plurality of seal teeth, said honeycomb seal configured to reduce an operating clearance between said honeycomb seal and the seal teeth. 11. A gas turbine engine comprising a rotor assembly and a stator assembly comprising a honeycomb seal fabricated from a material having a melting temperature less than approximately 2000° F., said rotor assembly comprising a plurality of seal teeth, said honeycomb seal condfigured to reduce an operating temperature of each of said rotor seal teeth as said seal teeth rub said honeybomb seal. 12. A gas turbine engine in accordance with claim 11 wherein said honeycomb seal configured to reduce an operating clearance between said seal teeth and said honeycomb seal. 13. A gas turbine engine in accordance with claim 11 wherein said honeycomb seal configured to reduce wear of said seal teeth as said seal teeth rub said honeycomb. 14. A gas turbine engine in accordance with claim 11 wherein said material has a melting temperature approximately equal 1930° F. 15. A gas turbine engine in accordance with claim 11 wherein said material has a melting temperature greater than approximately 1600° F. 16. A gas turbine engine in accordance with claim 11 wherein said material has a melting temperature approximately equal 1050° F. 17. A gas turbine engine in accordance with claim 11 wherein said rotor assembly comprises a plurality of rotor seal teeth, said material configured to reduce crack initiation of said rotor seal teeth. 18. A gas turbine engine in accordance with claim 17 wherein said material further configured to reduce fatigue degradation of said rotor seal teeth.