All The Claims

1. A method for channelizing a Passive Optical Network (PON) Media Access Controller (MAC) comprising:
receiving network traffic data through a network switch;
transmitting the network traffic data to one or more PON MAC(s) from the network switch; and
increasing a clock rate of each of the one or more PON MAC(s) to channelize the one or more PON MAC(s) according to NX, where N>1 and equals a number of ports supported by each of the one or more PON MAC(s) and X equals a designated operating PON MAC clocking rate.
2. A method according to claim 1, wherein the channelizing of one or more PON MAC(s) includes error correction and encryption.
3. A method according to claim 2, wherein the encryption and the one or more PON MAC(s) are channelized on a per frame basis.
4. A method according to claim 2, wherein the error correction comprises Forward Error Correction (FEC) and the channelization occurs in multiple stages such that the Forward Error Correction (FEC) may be channelized on a per FEC code block.
5. A method according to claim 1, wherein the channelization occurs on a word, byte, or bandwidth basis.
6. A method according to claim 1, wherein the one or more PON MAC(s) are utilized within an Ethernet Passive Optical Network (EPON), Gigabyte Passive Optical Network (GPON) or a combination thereof.
7. A method according to claim 1, wherein the PON MAC is integrated within an Optical Line Terminal (OLT).
8. A system incorporating one or more channelized Passive Optical Network (PON) Media Access Controllers (MACs), the system comprising:
a PON network switch;
one or more channelized MAC(s) connected to the PON network switch, each of the one or more channelized MAC(s) supporting N channels, where N>1;
one or more error correction modules connected to the one or more channelized MAC(s);
a plurality of physical coding sublayers (PCSs) forming a PON lane comprising the N channels; and
a serializerdeserializer (SERDES) interfacing with the PON lane.
9. A system incorporating one or more channelized Passive Optical Network (PON) Media Access Controllers (MACs), as per claim 8, wherein the one or more channelized MACs comprise at least a low-speed and a high-speed MAC connected to the PON network switch.
10. A system incorporating one or more channelized Passive Optical Network (PON) Media Access Controllers (MACs), as per claim 9, wherein the low-speed MAC comprises at least one 1G Ethernet Passive Optical Network (EPON) MAC and the high-speed MAC comprises at least one 10G EPON MAC.
11. A system incorporating one or more channelized Passive Optical Network (PON) Media Access Controllers (MACs), as per claim 8, wherein the one or more channelized MACs comprise any of, or a combination of one or more of: 1 Gbps Ethernet Passive Optical Network (EPON) MACs, 10 Gbps EPON MACs, Gigabyte Passive Optical Network (GPON), 2G MACs, XGPON 10G MACs, and AE P2P 10G MACs.
12. A system incorporating one or more channelized Passive Optical Network (PON) Media Access Controllers (MACs), as per claim 8, further comprising one or more encryption modules working in conjunction with the one or more error correction modules.
13. A system incorporating one or more channelized Passive Optical Network (PON) Media Access Controllers (MACs), as per claim 12, wherein the one or more encryption modules utilizes an Advanced Encryption Standard 128b (AES-128) andor China Telecom Triple Churning (Chrn) Standard.
14. A system incorporating one or more channelized Passive Optical Network (PON) Media Access Controllers (MACs), as per claim 12, wherein encryption and the one or more channelized Passive Optical Network (PON) Media Access Controllers (MACs) are channelized on a per frame basis.
15. A system incorporating one or more channelized Passive Optical Network (PON) Media Access Controllers (MACs), as per claim 8, wherein the one or more channelized MACs further share common IP modules including, but not limited to: scheduling (SCH), dynamic bandwidth allocator (DBA) and statistics memory.
16. A system incorporating one or more channelized Passive Optical Network (PON) Media Access Controllers (MACs), as per claim 8, wherein the one or more error correction modules uses Forward Error Correction (FEC) and the channelization occurs in multiple stages such that the Forward Error Correction (FEC) may be channelized on a per FEC code block.
17. A system incorporating one or more channelized Passive Optical Network (PON) Media Access Controllers (MACs), as per claim 8, wherein the one or more channelized MAC(s) are utilized within an EPON, a Gigabyte Passive Optical Network (GPON) or a combination thereof.
18. A system incorporating one or more channelized Passive Optical Network (PON) Media Access Controllers (MACs), as per claim 8, wherein the one or more channelized MAC(s) are integrated within an Optical Line Terminal (OLT).
19. A multi-port Optical Line Terminal (OLT) incorporating one or more channelized Passive Optical Network (PON) Media Access Controllers (MACs) comprising:
a PON network switch;
one or more channelized MACs connected to the PON network switch, each of the one or more channelized MACs supporting N channels, where N>1;
one or more error correction and encryption modules connected to the one or more channelized MACs;
a plurality of physical coding sublayers (PCSs) forming one or more PON lane(s) comprising the N channels for each of the one or more channelized MACs; and
a serializerdeserializer (SERDES) interfacing with each of the one or more PON lane(s).
20. A multi-port Optical Line Terminal (OLT) incorporating one or more channelized Passive Optical Network (PON) Media Access Controllers (MACs), as per claim 19, wherein the one or more channelized MACs comprise at least a low-speed and a high-speed MAC connected to the PON network switch.

The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.

1. A turbine balance assembly comprising:
a turbine rotor connected to drive a turbine shaft;
bearings positioned radially outwardly of said turbine shaft;
a bearing sleeve positioned radially outwardly of said bearings, and supporting said bearings, said bearing sleeve extending along an axial length defined by a rotational axis of said shaft, and said bearing sleeve having a turbine rotor end adjacent to said turbine rotor, and a remote end;
a radially outwardly extending flange on said bearing sleeve extending radially outwardly of a support portion of said bearing sleeve and at said turbine rotor end, and said flange having a nominal outer radius, and including a slot for receiving an anti-rotation tab over a limited circumferential extent;
a ratio between a distance from a center line of said bearing sleeve to a tangent point for a flat surface on a radially inner end of said slot relative to said nominal radius of the flange is between 0.92 and 0.95; and
said slot extends for a distance along said flat surface between two sides, and a ratio of the distance between said two sides to said nominal radius is between 0.09 and 0.22.
2. The turbine balance assembly as set forth in claim 1, wherein said slot extends over an angle of between 4\xb0 and 12\xb0 to define said limited circumferential extent.
3. An air turbine starter comprising:
a turbine rotor connected to drive a turbine shaft;
bearings positioned radially outwardly of said turbine shaft;
a bearing sleeve positioned radially outwardly of said bearings, and supporting said bearings, said bearing sleeve extending along an axial length defined by a rotational axis of said shaft, and said bearing sleeve having a turbine rotor end adjacent to said turbine rotor, and a remote end;
a radially outwardly extending flange on said bearing sleeve extending radially outwardly of a support portion of said bearing sleeve and at said turbine rotor end, and said flange having a nominal outer diameter, and including a slot for receiving an anti-rotation tab over a limited circumferential extent;
a gear cage radially outwardly of said bearing sleeve, and including an anti-rotation tab extending into said slot to resist rotation of said bearing sleeve relative to said gear cage; and
said gear cage is formed of an outer aluminum member having an inner bore, and a steel liner force fit into said inner bore, said tab being part of said steel liner.
4. The air turbine starter as set forth in claim 3, wherein said slot extends over an angle of between 4\xb0 and 12\xb0 to define said limited circumferential extent.
5. The air turbine starter as set forth in claim 3, wherein a ratio between a distance from a center line of said bearing sleeve to a tangent point for a flat surface on a radially inner end of said slot relative to said nominal radius of the flange is between 0.92 and 0.95.
6. The air turbine starter as set forth in claim 5, wherein said slot extends for a distance along said flat surface between two sides, and a ratio of the distance between said two sides to said nominal radius is between 0.09 and 0.22.
7. The air turbine starter as set forth in claim 3, wherein said tab and said outer aluminum member extend along the axial dimension closer to said rotor over a limited circumferential extent associated with said slot, and said steel liner and said gear cage having surfaces that are more removed from said turbine rotor at locations other than said limited circumferential extent.
8. The air turbine starter as set forth in claim 3, wherein said steel liner has the tab formed in an axially forward end spaced more toward said turbine rotor than a remote end, and there being an outer diameter of said steel liner, and a ratio of an inner diameter of said forward end to said outer diameter is between 0.92 and 0.98.
9. The air turbine starter as set forth in claim 8, wherein a ratio of said inner diameter of said forward end to an axial length of the entire steel liner is between 12.5 and 4.5.
10. A gear cage comprising:
an outer aluminum member having a cylindrical inner bore;
a steel liner force fit into said inner bore, a tab being formed as part of said steel liner, and said tab and said outer aluminum member extending along an axial dimension more forwardly than a nominal face of said liner and said outer aluminum member, and over a limited circumferential extent;
wherein said steel liner has the tab formed in an axially forward end that is to be spaced more toward a turbine rotor than a remote end, and there being an outer diameter of said steel liner, and a ratio of an inner diameter of said forward end to said outer diameter is between 0.92 and 0.98; and
a ratio of said inner diameter of said forward end to an axial length of the entire steel liner is between 12.5 and 4.5.
11. A bearing sleeve comprising:
a support portion extending along a central axis, and having a flange at a turbine end extending radially outwardly;
said flange having a nominal outer radius, and a slot for receiving an anti-rotation lock over a limited circumferential extent, said slot extending over an angle of between 4\xb0 and 12\xb0 to define said limited circumferential extent; and
said slot extends for a distance along said flat surface between two sides, and a ratio of the distance between said two sides to said nominal radius is between 0.09 and 0.22.
12. The bearing sleeve as set forth in claim 11, wherein a ratio between a distance from a center line of said bearing sleeve to a tangent point for a flat surface on a radially inner end of said slot relative to said nominal radius of the flange is between 0.92 and 0.95.
13. A method of assembling an air turbine starter comprising the steps of:
inserting a turbine rotor and shaft, and bearings supporting said shaft into a bearing sleeve to form a turbine balance assembly, and said bearing sleeve having a slot to receive an anti-rotation structure at an end of said bearing sleeve positioned toward said turbine rotor;
moving said turbine balance assembly into a gear cage, said gear cage having an anti-rotation tab and said tab being moved into said slot; and
said gear cage is formed of an outer member having inner bore, and a liner force fit into said inner bore, with said liner providing the tab.
14. The method as set forth in claim 13, wherein said outer member and said liner initially have cylindrical forward surfaces, and said cylindrical forward surfaces of said outer aluminum member and said liner are machined away to leave said tab, and a portion of said cylindrical forward surfaces of said outer member over a limited circumferential extent prior to said turbine balance assembly being inserted within said gear cage.
15. The method as set forth in claim 14, wherein said liner is machined away to leave said tab, after said liner has been force fit into said gear cage.
16. The gear cage as set forth in claim 10, the tab has an inner diameter that is greater than an inner diameter of a cylindrical portion of the liner connecting the tab to an inner end of the liner, and wherein the inner end of liner defining an inner bore, and the tab having an inner face spaced from a center axis of the liner, and wherein the tab inner face is spaced further from the center axis than the inner surface of the cylindrical portion, and the inner face of the cylindrical portion is spaced from the center axis by a greater distance than is the inner bore of the inner end.
17. The air turbine starter as set forth in claim 3, the tab has an inner diameter that is greater than an inner diameter of a cylindrical portion of the liner connecting the tab to an inner end of the liner, and wherein the inner end of liner defining an inner bore, and the tab having an inner face spaced from a center axis of the liner, and wherein the tab inner face is spaced further from the center axis than the inner surface of the cylindrical portion, and the inner face of the cylindrical portion is spaced from the center axis by a greater distance than is the inner bore of the inner end.

1. A photoelectric conversion element package retaining unit comprising:
a photoelectric conversion element package including electrodes formed on a rear surface of a light-receiving surface;
a printed circuit board electrically connected to the electrodes of the photoelectric conversion element package, wherein the printed circuit board has a first opening formed in an area corresponding to an inside of the electrodes of the photoelectric conversion element package; and
a retaining member configured to retain the photoelectric conversion element package, wherein the retaining member includes:
a positioning unit configured to position the photoelectric conversion element package in an axial direction orthogonal to the light-receiving surface by abutting on the photoelectric conversion element package outside the electrodes of the photoelectric conversion element package; and
a second opening formed to pour an adhesive into the area corresponding to the inside of the electrodes of the photoelectric conversion element package.
2. The photoelectric conversion element package retaining unit according to claim 1, wherein the second opening is smaller than the first opening.
3. The photoelectric conversion element package retaining unit according to claim 1, wherein the electrodes of the photoelectric conversion element package are arranged on the rear surface of the light-receiving surface in a doughnut shape.
4. The photoelectric conversion element package retaining unit according to claim 1, wherein the photoelectric conversion element package is a ball grid array (BGA) type package.
5. The photoelectric conversion element package retaining unit according to claim 1, wherein the photoelectric conversion element package is a land grid array (LGA) type package.
6. An imaging apparatus comprising:
a photographic lens barrel unit including a photographic lens optical system;
a photoelectric conversion element package including electrodes formed on a rear surface of a light-receiving surface;
a printed circuit board electrically connected to the electrodes of the photoelectric conversion element package, wherein a first opening is formed in an area corresponding to an inside of the electrodes of the photoelectric conversion element package in the printed circuit board; and
a retaining member configured to retain the photoelectric conversion element package so that the light-receiving surface of the photoelectric conversion element package is arranged perpendicular to an optical axis of the photographic lens optical system, wherein the retaining member includes:
a positioning unit configured to position the photoelectric conversion element package in an axial direction orthogonal to the light-receiving surface by abutting on the photoelectric conversion element package outside the electrodes of the photoelectric conversion element package; and
a second opening formed to pour an adhesive into the area corresponding to the inside of the electrodes of the photoelectric conversion element package.
7. The imaging apparatus according to claim 6, wherein the second opening is smaller than the first opening.
8. The imaging apparatus according to claim 6, wherein the electrodes of the photoelectric conversion element package are arranged on the rear surface of the light-receiving surface in a doughnut shape.
9. The imaging apparatus according to claim 6, wherein the photoelectric conversion element package is a ball grid array (BGA) type package.
10. The imaging apparatus unit according to claim 6, wherein the photoelectric conversion element package is a land grid array (LGA) type package.

The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.

1. A blade root shim comprising
a base extending longitudinally between a leading shim end and trailing shim end;
a suction side shim wall extending along the base, the suction side shim wall corresponding to a suction side blade root bearing surface;
a pressure side shim wall spaced circumferentially apart from the suction shim wall, the pressure side shim wall corresponding to a pressure side blade bearing surface; and
a contact relief region formed into an upper wall portion of either the suction side shim wall or the pressure side shim wall.
2. The shim of claim 1, wherein the contact relief region is formed into the upper wall portion of at least one of the leading shim end and the trailing shim end.
3. The shim of claim 1, comprising a plurality of contact relief regions, each contact relief region formed into the upper wall portion of at least one of the pressure side shim wall, and the suction side shim wall.
4. The shim of claim 1, wherein the base is curved transversely to the longitudinal direction between the suction side shim wall and pressure side shim wall.
5. The shim of claim 1, wherein at least one of the pressure side shim wall and the suction side shim wall includes a lower wall portion curved upwardly and outwardly from the base, and the upper wall portion is curved upwardly and inwardly from the lower wall portion.
6. The shim of claim 5, wherein the contact relief region includes at least one cutout formed into both the upper wall portion and the lower wall portion.
7. The shim of claim 5, wherein the contact relief region includes at least one cutout having a longitudinal dimension of at least about 5% of a longitudinal distance between the leading shim end and the trailing shim end.
8. The shim of claim 1, wherein the pressure side shim wall and the suction side shim wall are arranged at a shim broach angle of at least about 5\xb0.
9. A blade assembly comprising:
a blade having an airfoil section and a root section; and
a shim disposed over the blade root section, the shim comprising a base, suction side and pressure side shim walls extending from the base, and a contact relief region aligned with a portion of the blade root section.
10. The blade assembly of claim 9, wherein the contact relief region is aligned with a high load portion of the blade root section.
11. The blade assembly of claim 10, wherein the blade airfoil section and root section each comprise a ceramic matrix composite (CMC) substrate.
12. The blade assembly of claim 11, wherein the CMC substrate comprises woven silicon carbide fibers coated with boronitride particles and retained in a silicon carbide matrix.
13. The blade assembly of claim 11, further comprising at least one protective coating layer disposed over the root section comprising the CMC substrate.
14. The blade assembly of claim 9, wherein the shim comprises a resilient metal substrate with a low friction coating layer disposed on at least one shim surface.
15. The blade assembly of claim 9, wherein the blade airfoil section and root section each comprise a organic matrix composite (OMC) substrate.
16. A gas turbine rotor assembly comprising:
a plurality of rotor blades each including an airfoil section, and a root section;
a rotor disc including a plurality of circumferentially distributed blade retention slots corresponding to the plurality of rotor blades, each retention slot having at least one bearing surface mating with a bearing surface disposed on the blade root sections; and
a blade root shim disposed between one of the plurality of rotor blades and a corresponding blade retention slot, the blade root shim including a contact relief region formed into at least an upper portion of the blade root shim and aligned with a portion of the blade root section.
17. The rotor assembly of claim 16, wherein the contact relief region is aligned with a high load portion of the blade root section.
18. The rotor assembly of claim 16, further comprising a retention ring secured around an longitudinal face of the rotor disc, and including at least one portion disposed immediately adjacent a longitudinal bearing face of the at least one blade root portion.
19. The rotor assembly of claim 16, wherein the plurality of blades and the corresponding plurality of radial retention slots are disposed at a broach angle of at least about 5\xb0 relative to an axial centerline of the rotor assembly.
20. A gas turbine engine comprising a rotor assembly as recited in claim 16, wherein the rotor assembly is disposed in a fan section of the gas turbine engine
21. A gas turbine engine comprising a plurality of rotor assemblies as recited in claim 16, wherein at least one of the plurality of rotor assemblies is disposed in a turbine section of the gas turbine engine.
22. A method of assembling a turbine rotor assembly, the method comprising:
placing a blade root shim having at least one contact relief region over root section of a ceramic matrix composite (CMC) rotor blade;
inserting the shim and the rotor blade root section into a rotor disc radial retention slot; and
securing the shim and the rotor blade root section into the retention slot with the at least one contact relief region aligned with a corresponding at least one location of the blade root section.
23. The method of claim 22, wherein the at least one high load portion of the root section is located proximate an intersection of adjacent root bearing surfaces.
24. The method of claim 22, wherein the blade root section is inserted at a broach angle of at least about 5\xb0 relative to an axial orientation of the rotor disc.