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Liquid fuel from a rotary fluid trap is atomized by a sharp edge on an inside surface of an aft cavity of a bladed rotor of a gas turbine engine and directed into each of a plurality of associated hollow blades through corresponding blade inlet ducts that are in fluid communication with correspondin

Liquid fuel from a rotary fluid trap is atomized by a sharp edge on an inside surface of an aft cavity of a bladed rotor of a gas turbine engine and directed into each of a plurality of associated hollow blades through corresponding blade inlet ducts that are in fluid communication with corresponding aft hollow interior portions of each blade. A radially-extending central rib within each blade partitions the hollow interior thereof into aft and forward hollow interior portions that are in fluid communication through an associated opening in the central rib and through a radially-extending gap between the central rib and the interior surface of the blade. A blade outlet duct provides for fluid communication between the forward hollow interior portion and a forward cavity of the bladed rotor, and a rotor outlet duct provides for discharging the fuel from a radially-inboard portion of the forward cavity.

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1. A bladed rotor for use in a gas turbine engine, comprising: a. a rotor, wherein said rotor is configured to be operatively coupled to or a part of a hollow shaft assembly of the as turbine engine, and during operation of said gas turbine engine, said rotor rotates with said hollow shaft assembly

1. A bladed rotor for use in a gas turbine engine, comprising: a. a rotor, wherein said rotor is configured to be operatively coupled to or a part of a hollow shaft assembly of the as turbine engine, and during operation of said gas turbine engine, said rotor rotates with said hollow shaft assembly about a common axis of rotation of said gas turbine engine;b. a rotary fluid trap comprising at least one net port, a trap portion, and an outlet port, each of which rotate with the bladed rotor during operation of said gas turbine engine, wherein at least one of said at least one net port is in fluid communication with a source of liquid fuel from an interior portion of said hollow shaft assembly;c. an aft cavity, wherein said aft cavity is in fluid communication with said outlet port of said rotary fluid trap, said aft cavity is aft of a medial plane of said rotor; and said medial plane is transverse to said common axis of rotation and is medial with respect to forward and aft sides of said rotor;d. a sharp edge on an inside surface of said aft cavity over which said liquid fuel flows during operation of said gas turbine engine, so as to provide for atomization of said liquid fuel flowing thereover during operation of said gas turbine engine;e. a forward cavity, wherein said forward cavity is forward of said medial plane of said rotor;f. a plurality of hollow blades arranged along a periphery of said rotor; wherein each hollow blade of said plurality of hollow blades comprises: i. a blade inlet duct, wherein said blade inlet duct provides for fluid communication between said aft cavity and an aft hollow interior portion of said hollow blade;ii. a radially-extending central rib within and generally circumferentially across a hollow interior of said hollow blade and between opposing sides of said hollow blade that partitions said hollow interior of said hollow blade into said aft hollow interior portion and a forward hollow interior portion, wherein said forward hollow interior portion of said hollow blade is internally adjacent to a leading edge of said hollow blade, said aft hollow interior portion of said hollow blade is internally adjacent to a trailing edge of said hollow blade; a radially-inboard portion of said radially-extending central rib is continuous with a rim portion of said rotor within a hoop portion of said hollow blade, and a radial extent of said radially-extending central rib is less than a corresponding radial extent of said hollow interior of said hollow blade so as to provide a corresponding radially-extending gap therebetween that provides for fluid communication between said aft and forward hollow interior portions of said hollow blade;iii. an opening in said radially-extending central rib located radially outboard of said hoop portion of said hollow blade, wherein said opening in said radially-extending central rib provides for fluid communication between said aft and forward hollow interior portions of said hollow blade; andiv. a blade outlet duct, wherein said blade outlet duct provides for fluid communication between said forward hollow interior portion of said hollow blade and said forward cavity; andg. a rotor outlet duct, wherein said rotor outlet duct is in fluid communication with said forward cavity and provides for discharging said fuel from a radially-inboard portion thereof during operation of said gas turbine engine. 2. A bladed rotor for use in a gas turbine engine as recited in claim 1, wherein for at least one radial cross-section of said trap portion of said rotary fluid trap, every point in said at least one radial cross-section is radially further distant from said axis of rotation than every point in an inlet to said at least one inlet port and an outlet from said outlet port so that during rotation of said rotary fluid trap during operation of said gas turbine engine, a portion of said liquid fuel supplied to said rotary fluid trap is retained within said trap portion responsive to the action of associated centrifugal forces. 3. A bladed rotor for use in a gas turbine engine as recited in claim 1, wherein said at least one inlet port comprises at least first and second inlet ports, said first inlet port is in fluid communication with said source of liquid fuel from an interior portion of said hollow shaft assembly, and when installed in said gas turbine engine, said second inlet port is in fluid communication with a cavity containing a bearing that supports said hollow shaft assembly and through which a portion of said liquid fuel is directed so as to provide for cooling said bearing during operation of said gas turbine engine. 4. A bladed rotor for use in a gas turbine engine as recited in claim 1, wherein said aft cavity is bounded between an aft surface of said rotor and a forward surface of an aft cover plate, and a periphery of said aft cover plate is sealed at an aft rim portion of said rotor. 5. A bladed rotor for use in a gas turbine engine as recited in claim 4, wherein said periphery of said aft cover plate is welded to said aft rim portion of said rotor. 6. A bladed rotor for use in a gas turbine engine as recited in claim 4, wherein a radially-central portion of said aft cover plate is axially supported from a portion of said hollow shaft assembly of said gas turbine engine. 7. A bladed rotor for use in a gas turbine engine as recited in claim 6, wherein said rotary fluid trap is incorporated in said hollow shaft assembly of said gas turbine engine, and said radially-central portion of said aft cover plate is axially supported from a portion of said rotary fluid trap by at least one dowel within and extending across said outlet port of said rotary fluid trap. 8. A bladed rotor for use in a gas turbine engine as recited in claim 1, wherein said aft cavity comprises an axially-aftward-extending hollow interior portion proximate to an aft rim portion of said rotor, wherein said axially-aftward-extending hollow interior portion is in fluid communication with said aft cavity, further comprising at least one labyrinth seal element located on an exterior of a wall portion that bounds said axially-aftward-extending hollow interior portion of said aft cavity. 9. A bladed rotor for use in a gas turbine engine as recited in claim 1, wherein said sharp edge undercuts said inside surface of said aft cavity and defines a circumferential local radial extremum. 10. A bladed rotor for use in a gas turbine engine as recited in claim 1, wherein said inside surface of said aft cavity is forward facing on an aft side of said aft cavity, and a portion of said inside surface of said aft cavity radially-inward of said sharp edge is a sloped surface that is sloped aftward so that a radially-inward portion of said sloped surface of said aft cavity radially inward of said sharp edge is aftward of said sharp edge. 11. A bladed rotor for use in a gas turbine engine as recited in claim 1, wherein said forward cavity is bounded between a forward surface of said rotor and an aft surface of a forward cover plate, and a periphery of said forward cover plate is sealed at a forward rim portion of said rotor. 12. A bladed rotor for use in a gas turbine engine as recited in claim 11, wherein said periphery of said forward cover plate is welded to said forward rim portion of said rotor. 13. A bladed rotor for use in a gas turbine engine as recited in claim 1, wherein said forward cavity comprises an axially-forward-extending hollow interior portion proximate to a forward rim portion of said rotor, wherein said axially-forward-extending hollow interior potion is in fluid communication with said forward cavity, further comprising at least one labyrinth seal element located on an exterior of a wall portion that bounds said axially-forward-extending hollow interior portion of said forward cavity. 14. A bladed rotor for use in a gas turbine engine as recited in claim 1, wherein a radially-medial portion of said forward cavity incorporates a plurality of radially-extending guide vanes radially outboard of said rotor outlet duct, wherein said plurality of radially-extending guide vanes provide for imposing a forced vortex flow on said fuel in an atomized, vaporous or gaseous state flowing through said forward cavity during operation of said gas turbine engine. 15. A bladed rotor for use in a gas turbine engine as recited in claim 14, wherein said plurality of radially-extending guide vanes provide for forming associated radially-extending channels therebetween that are substantially radially directed. 16. A bladed rotor for use in a gas turbine engine as recited in claim 14, wherein said plurality of radially-extending guide vanes provide for associated radially-extending channels therebetween that are swept in a direction of rotation of said gas turbine engine during operation thereof. 17. A bladed rotor for use in a gas turbine engine as recited in claim 14, wherein said plurality of radially-extending guide vanes provide for associated radially-extending channels therebetween that are swept in a direction that is opposite to a direction of rotation of said gas turbine engine during operation thereof. 18. A bladed rotor for use in a gas turbine engine as recited in claim 14, wherein said forward cavity is bounded between a forward surface of said rotor and an aft surface of a forward cover plate, a periphery of said forward cover plate is sealed at a forward rim portion of said rotor, and said plurality of radially-extending guide vanes are incorporated onto an aft surface of said forward cover plate. 19. A bladed rotor for use in a gas turbine engine as recited in claim 1, wherein a path of said blade inlet duct is contoured so that an exit portion thereof into said hollow interior of said hollow blade is more radially directed than an entrance portion thereof from said aft cavity, so as to provide for said fuel in an atomized, vaporous or gaseous state from said aft cavity to be directed at least partially axially aftwards from said aft cavity into said blade inlet duct, and at least partially radially outward into an aft hollow interior portion of said hollow blade from said blade inlet duct, during the operation of said gas turbine engine. 20. A bladed rotor for use in a gas turbine engine as recited in claim 19, wherein said path of said blade inlet duct is contoured so as to provide for said fuel in said atomized, vaporous or gaseous state from said aft cavity to be directed substantially radially outward into an aft hollow interior portion of said hollow blade during the operation of said gas turbine engine. 21. A bladed rotor for use in a gas turbine engine as recited in claim 1, wherein said opening in said radially-extending central rib is radially proximate to said hoop portion of said hollow blade. 22. A bladed rotor for use in a gas turbine engine as recited in claim 1, wherein said opening in said radially-extending central rib is elliptically shaped, for which an associated major axis thereof is generally oriented in a radial direction. 23. A bladed rotor for use in a gas turbine engine as recited in claim 1, wherein a path of said blade outlet duct is contoured so that an entrance portion thereof from said forward hollow interior portion is more radially directed than an exit portion thereof into said forward cavity, so as to provide for said fuel in an atomized, vaporous or gaseous state from said forward hollow interior portion of said hollow blade to be directed at least partially radially inward into said blade outlet duct and from said blade outlet duct at least partially axially aftward into said forward cavity during the operation of said gas turbine engine. 24. A bladed rotor for use in a gas turbine engine as recited in claim 1, wherein each said hollow blade of said plurality of hollow blades further comprises at least one first transverse rib within and generally circumferentially across said aft hollow interior portion of said hollow blade and between corresponding opposing sides of said hollow blade. 25. A bladed rotor for use in a gas turbine engine as recited in claim 24, wherein a radially-inboard end of said at least one first transverse rib extends into an exit portion of a corresponding blade inlet duct. 26. A bladed rotor for use in a gas turbine engine as recited in claim 1, wherein each said hollow blade of said plurality of hollow blades further comprises at least one second transverse rib within and generally circumferentially across said forward hollow interior portion of said hollow blade and between corresponding opposing sides of said hollow blade. 27. A bladed rotor for use in a gas turbine engine as recited in claim 26, wherein a radially-inboard end of said at least one second transverse rib extends into an entrance portion of a corresponding blade outlet duct. 28. A bladed rotor for use in a gas turbine engine as recited in claim 24, wherein each said hollow blade of said plurality of hollow blades further comprises at least one second transverse rib within and generally circumferentially across said forward hollow interior portion of said hollow blade and between corresponding opposing sides of said hollow blade, wherein said at least one first transverse rib is shorter in a radial dimension than said at least one second transverse rib. 29. A bladed rotor for use in a gas turbine engine as recited in claim 1, wherein each said hollow blade of said plurality of hollow blades further comprises: a. at least one first transverse rib within and generally circumferentially across said aft hollow interior portion of said hollow blade and between corresponding opposing sides of said hollow blade; andb. at least one second transverse rib within and generally circumferentially across said forward hollow interior portion of said hollow blade and between corresponding opposing sides of said hollow blade, wherein a radially-inboard portion of at least one of said at least one first transverse rib or said at least one second transverse rib is continuous with said rim portion of said rotor within said hoop portion of said hollow blade. 30. A bladed rotor for use in a gas turbine engine as recited in claim 1, wherein each said hollow blade of said plurality of hollow blades further comprises: a. at least one first transverse rib within and generally circumferentially across said aft hollow interior portion of said hollow blade and between corresponding opposing sides of said hollow blade; andb. at least one second transverse rib within and generally circumferentially across said forward hollow interior portion of said hollow blade and between corresponding opposing sides of said hollow blade, wherein a radial extent of at least one of said at least one first transverse rib or said at least one second transverse rib is less than a corresponding radial extent of said hollow interior of said hollow blade so as to provide a corresponding radially-extending gap therebetween that provides for fluid communication through said corresponding radially-extending gap. 31. A bladed rotor for use in a gas turbine engine as recited in claim 1, wherein each said hollow blade of said plurality of hollow blades further comprises a plurality of transverse pedestals located in a corresponding said aft hollow interior portion of said hollow blade, wherein each transverse pedestal of said plurality of transverse pedestals extends generally circumferentially across said aft hollow interior portion and between corresponding opposing sides of said hollow blade, in thermal communication with said corresponding opposing sides of said hollow blade. 32. A bladed rotor for use in a gas turbine engine as recited in claim 31, wherein said plurality of transverse pedestals are arranged within each said hollow blade in a plurality of columns, with a plurality of radially-separated said transverse pedestals within each column of said plurality of columns. 33. A bladed rotor for use in a gas turbine engine as recited in claim 1, wherein each said hollow blade of said plurality of hollow blades further comprises a plurality of blade-centric internally-peripheral ribs, wherein each blade-centric internally-peripheral rib of said plurality of blade-centric internally-peripheral ribs extends around at least a portion of a periphery of said hollow interior of said hollow blade and is peripheral with respect to a radial axis of said hollow blade, and said plurality of blade-centric internally-peripheral ribs are radially separated from one another within said hollow interior of said hollow blade. 34. A bladed rotor for use in a gas turbine engine as recited in claim 33, wherein said at least said portion of said periphery of said hollow interior of said hollow blade is on an interior of a suction side portion of said hollow blade. 35. A bladed rotor for use in a gas turbine engine as recited in claim 33, wherein said at least said portion of said periphery of said hollow interior of said hollow blade comprises an entire periphery of said hollow interior of said hollow blade for at least one said blade-centric internally-peripheral rib. 36. A bladed rotor for use in a gas turbine engine as recited in claim 11, wherein said rotor outlet duct is annularly located between a forward extension of said forward cover plate and either a forward extension of said rotor or a portion of said hollow shaft assembly.