초록 ▼

A ram air turbine power system includes a ram air turbine having a turbine shaft, turbine blades for rotating the turbine shaft; and an electrical generator or other power source device driven by a power shaft, for providing power. The power shaft has a generally hollow tubular shape, and the turbin

A ram air turbine power system includes a ram air turbine having a turbine shaft, turbine blades for rotating the turbine shaft; and an electrical generator or other power source device driven by a power shaft, for providing power. The power shaft has a generally hollow tubular shape, and the turbine shaft extends coaxially within the power shaft. The ram air turbine power system also includes a gearbox housing a planetary gear train, where one end of the gear train is a planetary sun gear spline coupled to the power shaft and the other end of the gear train is a planetary ring gear spline coupled to the turbine shaft so that the rotating turbine shaft drives the power shaft through the gear train increasing the speed of the power shaft over the speed of the turbine shaft.

대표청구항 ▼

A ram air turbine power system includes a ram air turbine having a turbine shaft, turbine blades for rotating the turbine shaft; and an electrical generator or other power source device driven by a power shaft, for providing power. The power shaft has a generally hollow tubular shape, and the turbin

A ram air turbine power system includes a ram air turbine having a turbine shaft, turbine blades for rotating the turbine shaft; and an electrical generator or other power source device driven by a power shaft, for providing power. The power shaft has a generally hollow tubular shape, and the turbine shaft extends coaxially within the power shaft. The ram air turbine power system also includes a gearbox housing a planetary gear train, where one end of the gear train is a planetary sun gear spline coupled to the power shaft and the other end of the gear train is a planetary ring gear spline coupled to the turbine shaft so that the rotating turbine shaft drives the power shaft through the gear train increasing the speed of the power shaft over the speed of the turbine shaft. seal land disposed between said rotatable engine member non-rotatable engine member. 8. A seal as claimed in claim 4 further comprising an auxiliary seal disposed across said leakage path radially inwardly of said inner and outer tooth rings, said auxiliary seal comprising an annular restrictor tooth radially spaced apart from and proximate to an annular seal land having an annular auxiliary seal surface circumscribed around said engine centerline. 9. A seal as claimed in claim 8 wherein said rotatable engine member is a side plate mounted on a rotor disk and said non-rotatable engine member is mounted on a translatable cylindrical piston which is circumferentially continuous and axially movably supported on a stationary face seal support structure. 10. A seal as claimed in claim 1 further comprising an auxiliary seal having a restrictor tooth radially spaced apart from and proximate to a seal land disposed between said rotatable engine member and non-rotatable engine member. 11. A seal as claimed in claim 10 wherein said rotatable engine member is a rotor disk. 12. A seal as claimed in claim 10 wherein said rotatable engine member is a side plate mounted on a rotor disk and said non-rotatable engine member is mounted on a translatable cylindrical piston which is circumferentially continuous and axially movably supported on a stationary face seal support structure. 13. A seal as claimed in claim 12 further comprising an auxiliary seal disposed across said leakage path radially inwardly of said inner and outer tooth rings, said auxiliary seal comprising an annular restrictor tooth radially spaced apart from and proximate to an annular seal land having an annular auxiliary seal surface circumscribed around said engine centerline. 14. A seal as claimed in claim 1 further comprising an auxiliary seal disposed across said leakage path radially inwardly of said inner and outer tooth rings, said auxiliary seal comprising an annular restrictor tooth radially spaced apart from and proximate to an annular seal land having an annular auxiliary seal surface circumscribed around said engine centerline. 15. A gas turbine engine seal assembly comprising: an aspirating face seal disposed between a relatively high pressure region and a relatively low pressure region at a juncture between a rotatable engine member and a stationary engine member, an annular generally planar non-rotatable gas bearing face surface circumscribed about a centerline and operably associated with said non-rotatable engine member, an annular generally planar rotatable gas bearing face surface circumscribed about said centerline and operably associated with said rotatable engine member, a leakage path in part axially extending between said gas bearing face surfaces, radially inner and outer tooth rings axially extending away from a first one of said gas bearing face surfaces across a portion of said leakage path and towards a second one of said gas bearing face surfaces, an annular plenum located between said inner and outer tooth rings and said first one of said gas bearing face surfaces, said inner and outer tooth rings having pointed ends proximate to said second one of said gas bearing face surfaces, and a biasing means for urging said inner and outer tooth rings axially away from said second one of said gas bearing face surfaces. 16. An assembly as claimed in claim 15 further comprising an auxiliary seal disposed across said leakage path radially inwardly of said inner and outer tooth rings, said auxiliary seal comprising an annular restrictor tooth radially spaced apart from and proximate to an annular seal land having an annular auxiliary seal surface circumscribed around said engine centerline. 17. An assembly as claimed in claim 15 wherein said rotatable engine member is a side plate mounted on a rotor disk and said non-rotatable engine member is a face seal ring mounted on a translatable cylindrical piston which is circumferentially continuous and a xially movably supported on a stationary face seal support structure. 18. An assembly as claimed in claim 17 further comprising an auxiliary seal disposed across said leakage path radially inwardly of said inner and outer tooth rings, said auxiliary seal comprising an annular restrictor tooth radially spaced apart from and proximate to an annular seal land having an annular auxiliary seal surface circumscribed around said engine centerline. 19. An assembly as claimed in claim 18 wherein said annular restrictor tooth is attached to said side plate and said annular seal land is attached to said face seal ring. 20. An assembly as claimed in claim 19 wherein said biasing means operably disposed between said cylindrical piston and said stationary face seal support structure. 21. An assembly as claimed in claim 20 wherein said biasing means includes a plurality of circumferentially spaced apart coil springs disposed within circumferentially spaced apart spring chambers formed in part by radially extending static and axially movable flanges attached to said face seal support structure and said translatable cylindrical piston respectively. 22. An assembly as claimed in claim 20 wherein said biasing means includes a wave spring disposed in a continuous annular spring chamber formed in part by radially extending static and axially movable flanges attached to said face seal support structure and said translatable cylindrical piston respectively. 23. An assembly as claimed in claim 20 wherein said said face seal ring has said radially inner and outer tooth rings extending axially away from said non-rotatable gas bearing face surface. 24. An assembly as claimed in claim 20 wherein said rotatable engine member has said radially inner and outer tooth rings extending axially away from said rotatable gas bearing face surface. 25. A gas turbine engine seal assembly comprising: an aspirating face seal disposed between a relatively high pressure region and a relatively low pressure region at a juncture between a rotatable engine member and a stationary engine member, said stationary structure depending from a turbine nozzle and supporting an inducer which is operable to direct a portion of high pressure compressor discharge air across said high pressure region, an annular generally planar non-rotatable gas bearing face surface circumscribed about a centerline and operably associated with said non-rotatable engine member, an annular generally planar rotatable gas bearing face surface circumscribed about said centerline and operably associated with said rotatable engine member, a leakage path in part axially extending between said gas bearing face surfaces, radially inner and outer tooth rings axially extending away from a first one of said gas bearing face surfaces across a portion of said leakage path and towards a second one of said gas bearing face surfaces, an annular plenum located between said inner and outer tooth rings and said first one of said gas bearing face surfaces, said inner and outer tooth rings having pointed ends proximate to said second one of said gas bearing face surfaces, and a biasing means for urging said inner and outer tooth rings axially away from said second one of said gas bearing face surfaces. 26. An assembly as claimed in claim 25 wherein said rotatable engine member is a side plate mounted on a rotor disk and said non-rotatable engine member is a face seal ring mounted on a translatable cylindrical piston which is circumferentially continuous and axially movably supported on a stationary face seal support structure. 27. An assembly as claimed in claim 26 further comprising an auxiliary seal disposed across said leakage path radially inwardly of said inner and outer tooth rings, said auxiliary seal comprising an annular restrictor tooth radially spaced apart from and proximate to an annular seal land having an annular auxiliary seal surface circumscribed around said engine centerline. 28. An assembly a