Author: claimsbot

1. A hydrodynamic bearing assembly, comprising:
a support ring including a common slot; and
a plurality of discrete bearing elements distributed circumferentially about an axis and brazed to the support ring within the common slot with a braze alloy, each of the discrete bearing elements including a superhard bearing surface and extending beyond the common slot and the support ring, the plurality of discrete bearing elements defining a plurality of gaps, each of the gaps being located between circumferentially-adjacent discrete bearing elements of the plurality of discrete bearing elements with the braze alloy at least partially filling each of the gaps, at least a portion of the gaps being about 0.0051 mm to about 2.54 mm.
2. The hydrodynamic bearing assembly of claim 1 wherein the at least a portion of the gaps is about 0.0051 mm to about 0.051 mm.
3. The hydrodynamic bearing assembly of claim 1 wherein each of the discrete bearing elements comprises a first end region and a second end region with a respective one of the superhard bearing surfaces extending therebetween.
4. The hydrodynamic bearing assembly of claim 3 wherein the first end region and the second end region of each of the discrete bearing elements each comprises a substantially planar side surface.
5. The hydrodynamic bearing assembly of claim 4 wherein the substantially planar side surface is substantially oriented in a reference plane in which the axis substantially lies.
6. The hydrodynamic bearing assembly of claim 3 wherein the first end region and the second end region of each of the discrete bearing elements each exhibits a selected non-planar geometry.
7. The hydrodynamic bearing assembly of claim 6 wherein the selected non-planar geometry comprises a serrated geometry.
8. The hydrodynamic bearing assembly of claim 1 wherein at least a portion of the discrete bearing elements comprises a curved radial inner surface, a curved radial outer surface, a first substantially planar side surface extending between the curved radial inner surface and the curved radial outer surface, a second substantially planar side surface extending between the curved radial inner surface and the curved radial outer surface, with a respective one of the superhard bearing surfaces extending between the curved radial inner surface, the curved radial outer surface, the first substantially planar side surface, and the second substantially planar side surface.
9. The hydrodynamic bearing assembly of claim 1 wherein the superhard bearing surfaces form a substantially continuous bearing surface.
10. The hydrodynamic bearing assembly of claim 1 wherein the axis is a thrust axis.
11. The hydrodynamic bearing assembly of claim 1 wherein the axis is a rotation axis.
12. The hydrodynamic bearing assembly of claim 1 wherein each of the discrete bearing elements comprises:
a substrate; and
a superhard table bonded to the substrate, the superhard table including a respective one of the superhard bearing surfaces.
13. The hydrodynamic bearing assembly of claim 12 wherein the superhard table comprises at least one material selected from the group consisting of polycrystalline diamond, cubic boron nitride, and a diamond-silicon carbide composite.
14. The hydrodynamic bearing assembly of claim 1 wherein the braze alloy substantially fills each of the gaps.
15. A hydrodynamic bearing apparatus, comprising:
a rotor including a plurality of circumferentially-spaced bearing elements each of which includes a first bearing surface; and
a stator including a support ring including a common slot, the stator including a plurality of discrete bearing elements distributed circumferentially about an axis and brazed to the support ring within the single slot with a braze alloy, each of the discrete bearing elements including a superhard bearing surface and extending beyond the common slot and the support ring, the superhard bearing surfaces of the discrete bearing elements oriented to generally oppose the first bearing surfaces of the plurality of circumferentially-spaced bearing elements of the rotor, the plurality of discrete bearing elements defining a plurality of gaps, each of the gaps being located between circumferentially-adjacent discrete bearing elements of the plurality of discrete bearing elements with the braze alloy at least partially filling each of the gaps, at least a portion of the gaps being about 0.0051 mm to about 2.54 mm.
16. The hydrodynamic bearing assembly of claim 15 wherein the braze alloy substantially fills each of the gaps.
17. A motor assembly for use in drilling subterranean formations, comprising:
a motor operable to apply torque to a rotary drill bit, the motor operably coupled to a hydrodynamic bearing apparatus, the hydrodynamic bearing apparatus including a rotor and a stator; and
wherein at least one of the stator or the rotor comprises a hydrodynamic bearing assembly including:
a plurality of discrete bearing elements distributed circumferentially about an axis, the plurality of discrete bearing elements brazed to a support ring within a common slot thereof, each of the discrete bearing elements including a superhard bearing surface and extending beyond the common slot and the support ring, the plurality of discrete bearing elements defining a plurality of gaps, each of the gaps being located between circumferentially-adjacent discrete bearing elements of the plurality of discrete bearing elements with the braze alloy at least partially filling each of the gaps, at least a portion of the gaps being about 0.0051 mm to about 2.54 mm.
18. The hydrodynamic bearing assembly of claim 17 wherein the braze alloy substantially fills each of the gaps.
19. A hydrodynamic bearing assembly, comprising:
a support ring including a common slot;
a plurality of discrete polycrystalline diamond bearing elements distributed circumferentially in a single substantially circular row about a thrust axis and brazed to the support ring within the common slot with a braze alloy, each of the discrete polycrystalline diamond bearing elements including a polycrystalline diamond bearing surface and extending beyond the common slot and the support ring, the plurality of discrete polycrystalline diamond bearing elements defining a plurality of gaps, each of the gaps being located between circumferentially-adjacent discrete polycrystalline diamond bearing elements of the plurality of discrete polycrystalline diamond bearing elements with the braze alloy at least partially filling each of the gaps, at least a portion of the gaps being about 0.0051 mm to about 2.54 mm; and
wherein each of the discrete bearing elements includes a curved radial inner surface, a curved radial outer surface, a first substantially planar side surface extending between the curved radial inner surface and the curved radial outer surface, a second substantially planar side surface extending between the curved radial inner surface and the curved radial outer surface, with a respective one of the polycrystalline diamond bearing surfaces extending between the curved radial inner surface, the curved radial outer surface, the first substantially planar side surface, and the second substantially planar side surface.
20. The hydrodynamic bearing assembly of claim 19 wherein the braze alloy substantially fills each of the gaps.

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 negative active material for a rechargeable lithium battery comprising:
particles of a carbonaceous material that are capable of reversibly intercalating and deintercalating lithium; and
particles of a metal or a metal compound or mixtures thereof, distributed within the particles of carbonaceous material, wherein the particles of the metal or the metal compound have an average particulate diameter of 20 to 500 nm, the metal or the metal compound forming an alloy with lithium during electrochemical charging and discharging.
2. The negative active material of claim 1, wherein the metal or the metal compound is represented by formula 1:
A1\u2212xBx\u2003\u2003(1)
where 0\u2266x\u22660.%
A is at least one selected from the group consisting of Sn, Si, Ag, Zn, Cd, Al, Ga, In, Ce, Pb, As, Bi, and Sb; and
B is at least one selected from the group consisting of Zr, Ti, Fe, Co, Ni, Cu, C, O, N, and S.
3. The negative active material of claim 2, wherein x is in the range of 0 to 0.5.
4. The negative active material of claim 2, wherein the metal compound is an oxide of Sn, an oxide of Si, or an oxide of Sb.
5. The negative active material of claim 1, wherein the metal or the metal compound has an amorphous or a crystalline structure.
6. The negative active material of claim 1, wherein the particles of carbonaceous material having the particles of the metal or the metal compound or mixtures thereof distributed within have an average particulate diameter of 10 to 100 \u03bcm.
7. The negative active material of claim 6, wherein the particles of carbonaceous material havina the particles of the metal or the metal compound or mixtures thereof distributed within have an average particulate diameter of 20 to 50 \u03bcm.
8. The negative active material of claim 1, wherein the particles of the metal or the metal compound have an average particulate diameter of 20 to 80 nm.
9. The negative active material of claim 1, wherein the negative active material includes 10 to 80 wt % of the metal or the metal compound.
10. The negative active material of claim 1, wherein the ratio of the diameter of the particles of the metal or the metal compound to the diameter of the particles of carbonaceous material having the particles of the metal or the metal compound or mixtures thereof distributed therein have is 20 or less.
11. The negative active material of claim 1, wherein the negative active material includes an oxide layer formed on the metal or the metal compound.
12. The negative active material of claim 11, wherein the oxide layer has a thickness of 10 \u212b or less.
13. The negative active material of claim 1, wherein the particles of carbonaceous material having the particles of the metal or the metal compound or mixtures thereof distributed therein have a spherical shape or an elliptical shape.
14. The negative active material of claim 1, wherein the carbonaceous material is amorphous carbon.
15. The negative active material of claim 1, wherein the particles of carbonaceous material having the particles of the metal or the metal compound or mixtures thereof distributed therein have a core-shell structure, and the shell has a higher intensity ratio of Raman Spectroscopy peak intensity than the core.
16. The negative active material of claim 15, wherein the shell has an intensity ratio Ra I(1360)1(1580) of a Raman Spectroscopy peak intensity I(1360) at a (1360) plane to an Raman Spectroscopy peak intensity I(1580) at a (1580) plane of 0.2 to 1.5.
17. A rechargeable lithium battery comprising:
a positive electrode comprising a positive active material which reversibly intercalates and deintercalates lithium;
a negative electrode including a negative active material;
a separator interposed between the positive electrode and the negative electrode; and
an electrolyte comprising a non-aqueous organic solvent and a lithium salt; and wherein the negative active material comprises:
particles of a carbonaceous material that reversibly intercalate and deintercalate lithium, and
a plurality of particles of a metal or a metal compound or mixtures thereof, distributed within the particles of the carbonaceous material, wherein the particles of the metal or the metal compound have an average particulate diameter of 20 to 500 nm, the metal or the metal compound being capable of forming an alloy with lithium during electrochemical charging and discharging.
18. The rechargeable lithium battery of claim 17, wherein the non-aqueous organic solvent is at least one selected from the group consisting of carbonates, esters, ethers, and ketones.
19. The rechargeable lithium battery of claim 17, wherein the metal or the metal compound is represented by formula 1:
A1\u2212xBx\u2003\u2003(1)
where 0\u2266x\u22660.9;
A is at least one selected from the group consisting of Sn, Si, Ag, Zn, Cd, Al, Ga, In, Ce, Pb, As, Bi, and Sb; and
B is at least one selected from the group consisting of Zr, Ti, Fe, Co, Ni, Cu, C, O, N, and S.
20. The rechargeable lithium battery of claim 19, wherein x is in the range of 0 to 0.5.
21. The rechargeable lithium battery of claim 19, wherein the metal compound is an oxide of Sn, an oxide of Si, or an oxide of Sb.
22. The rechargeable lithium battery of claim 17, wherein the metal or the metal compound has an amorphous or a crystalline structure.
23. The rechargeable lithium battery of claim 17, wherein the particles of carbonaceous material having the particles of the metal or the metal compound or mixtures thereof distributed within have an average particulate diameter of 10 to 100 \u03bcm.
24. The rechargeable lithium battery of claim 23, wherein the particles of carbonaceous material having the particles of the metal or the metal compound or mixtures thereof distributed within have an average particulate diameter of 20 to 50 \u03bcm.
25. The rechargeable lithium battery of claim 17, wherein the particles of the metal or the metal compound have an average particulate diameter of 20 to 80 nm.
26. The rechargeable lithium battery of claim 17, wherein the negative active material includes 10 to 80 wt % of the metal or the metal compound.
27. The rechargeable lithium battery of claim 17, wherein the ratio of the diameter of the particles of the metal or the metal compound to the diameter of the particles of carbonaceous material having the particles of the metal or the metal compound or mixtures thereof distributed within is 20 or less.
28. The rechargeable lithium battery of claim 17, wherein the negative active material includes an oxide layer formed on the metal or the metal compound.
29. The rechargeable lithium battery of claim 28, wherein the oxide layer has a thickness of 10 \u212b or less.
30. The rechargeable lithium battery of claim 17, wherein the particles of carbonaceous material having the particles of the metal or the metal compound or mixtures thereof distributed within have spherical shape or elliptical shape.
31. The rechargeable lithium battery of claim 17, wherein the carbonaceous material is amorphous carbon.
32. The rechargeable lithium battery of claim 17, wherein the particles of carbonaceous material having the particles of the metal or the metal compound or mixtures thereof distributed within have a core-shell structure, and the shell has a higher intensity ratio of Raman Spectroscopy peak intensity than the core.
33. The rechargeable lithium battery of claim 32, wherein the shell has an intensity ratio Ra I(1360)1(1580) of a Raman Spectroscopy peak intensity I(1360) at a (1360) plane to an Raman Spectroscopy peak intensity I(1580) at a (1580) plane of 0.2 to 1.5.

1. A capacitor comprising:
a dielectric film; and
a first electrode and second electrode formed sandwiching said dielectric film and facing each other,
wherein said dielectric film has a density exceeding 72% of the theoretical density calculated based on the lattice constant,
wherein either or both of said first electrode and said second electrode contain at least one metal selected from the group consisting of Cu, Ni, Al, stainless steel and a nickel-based alloy, and
wherein said dielectric film comprises particles with a mean particle size of more than 40 nm and less than or equal to 70 nm.
2. A capacitor according to claim 1,
wherein said dielectric film contains at least one compound selected from the group consisting of barium titanate, strontium titanate and barium strontium titanate.
3. A capacitor according to claim 1, wherein the dielectric film has a dielectric constant of from 900 to 2463.
4. A capacitor according to claim 1, wherein the dielectric film comprises particles with a mean particle size of more than 40 nm and less than or equal to 50 nm.
5. A capacitor according to claim 4, wherein the dielectric film has a dielectric constant of from 900 to 2206.
6. A dielectric film production process which comprises:
a precursor layer-forming step in which a precursor layer containing a dielectric material is formed on a metal layer; and
an annealing step in which said precursor layer is heated for crystallization of said dielectric material in said precursor layer to form a dielectric film,
wherein during at least part of said annealing step, said precursor layer is heated to 550 to 1000\xb0 C. in a reduced pressure atmosphere with a pressure of 1\xd710\u22129 to 1\xd7103 Pa as measured with an ionization vacuum gage,
wherein the dielectric film has a density exceeding 72% of the theoretical density calculated based on the lattice constant, and
wherein the dielectric film comprises particles with a mean particle size of more than 40 nm and less than or equal to 70 nm.
7. A dielectric film production process according to claim 6,
wherein said metal layer includes at least one metal selected from the group consisting of Cu, Ni, Al, stainless steel and a nickel-based alloy.
8. A dielectric film production process according to claim 6,
wherein said metal layer comprises Cu,
and said precursor layer is heated in said annealing step in a reduced pressure atmosphere with a pressure of 4\xd710\u22121 to 8\xd710\u22121 Pa as measured with an ionization vacuum gage.
9. A dielectric film production process according to claim 6,
wherein said metal layer comprises Ni,
and said precursor layer is heated in said annealing step in a reduced pressure atmosphere with a pressure of 2\xd710\u22123 to 8\xd710\u22121 Pa as measured with an ionization vacuum gage.

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. Bypass turbine engine (1), in particular for an aircraft, in which air flows circulate from upstream to downstream, the turbine engine (1) extending axially and comprising:
an inner casing (11), an inter-duct casing (12) and an outer casing (13) so as to define a primary duct (V1) between the inter-duct casing (12) and the inner casing (11), and a secondary duct (V2) between the inter-duct casing (12) and the outer casing (13),
a rotary shaft (BP) comprising, at the upstream end, a movable fan (2) comprising radial blades (20) of which the free ends face the outer casing (13) of the turbine engine so as to compress an air flow at least in the secondary duct (V2),

said turbine engine (1) is characterised in that it comprises
a plurality of variable-pitch radial stator vanes (5) mounted upstream of the movable fan (2), said variable-pitch vanes being configured to deflect the axial incident air (F) and the movable fan being configured to axially rectify said deflected air into the secondary duct (V2), and
means for individually adjusting the pitch of the variable-pitch radial vanes (5) so as to allow an adaptive pitch to be provided depending on the configuration of the turbine engine.
2. Turbine engine according to claim 1, wherein the means for individually adjusting the pitch of the radial vanes (5) comprise a single control ring (24) and rods (25, 30) for connecting said control ring (24) to each of said radial vanes (5).
3. Turbine engine according to claim 1, wherein the inner casing (11), the inter-duct casing (12) and the outer casing (13) are at a radial distance from one another in the turbine engine (1) so as to define a turbine engine (1) having a bypass ratio (BPR) that is greater than or equal to 15.
4. Turbine engine according to claim 1, wherein the rotational speed of the free ends of the blades (20) of the movable fan (2) is less than 340 ms.
5. Turbine engine according to claim 1, wherein the plurality of variable-pitch radial vanes (5) extend in the same plane which is transverse to the axis of the turbine engine (1).
6. Turbine engine according to claim 1, wherein the axial distance between the plurality of variable-pitch radial vanes (5) and the movable fan (2) is between 0.1 and 10 times the mean chord of a variable-pitch radial vane (5).
7. Turbine engine according to claim 1, wherein the blades (20) of the movable fan (2) extend between the inner casing (11) and the outer casing (13) of the turbine engine (1).
8. Turbine engine according to claim 1, wherein each variable-pitch radial vane (5) has an aerodynamic profile so as to accelerate the incident air flow in accordance with a laminar flow.
9. Turbine engine according to claim 1, wherein each variable-pitch radial vane (5) has a body which is movable in rotation about a radial axis.
10. Turbine engine according to claim 1, wherein each variable-pitch radial vane (5\u2032) has a fixed body (50\u2032) and a movable flap (51\u2032).
11. Turbine engine according to claim 1, wherein each variable-pitch radial vane (5) is configured to ensure an air-brake function in a given pitch position.
12. Turbine engine according to claim 2, wherein the control ring (24) is movably mounted in rotation about a longitudinal axis (X-X) of the turbine engine, on a fixed casing (13, 21) which extends radially on the inside or on the outside of the radial vanes (5).
13. Turbine engine according to claim 12, wherein the adjustment means are mounted on the fixed casing (13, 21) and comprise, for each radial vane (5):
a first connecting rod (25) which is movably mounted in rotation about a first substantially radial pivot pin (29), which is mounted on the control ring (24), and about a second substantially radial pivot pin (27), which is mounted on the fixed casing (13, 21), and
a second connecting rod (30) which is pivotally mounted about a third substantially radial pivot pin (33), which is connected to the vane (5) and offset along the longitudinal axis (X-X) in relation to a pitch pin (23) of said radial vane (5),

the second connecting rod (30) being articulated to the first connecting rod (25) so as to be able to pivot about a substantially radial hinge pin (31) which is at a distance from the second pivot pin (27).
14. Turbine engine according to claim 13, wherein said second connecting rod (30) comprises means for modifying a first distance (d1), between the third pivot pin (33) and said hinge pin (31).
15. Turbine engine according to claim 13, wherein the hinge pin (31) is connected to the first connecting rod (25) by connection means (32) which are configured so as to be able to modify a second distance (d2), between said hinge pin (31) and the second pivot pin (27).
16. Turbine engine according to claim 13, wherein at least one of the parameters selected from a first distance (d1), between the third pivot pin (33) and said hinge pin (31), and a second distance (d2), between said hinge pin (31) and the second pivot pin (27), is different between at least two radial vanes (5).
17. Turbine engine according to claim 13, wherein, for each radial vane (5), the second pivot pin (27) and the pitch pin (23) of said vane are located on the same side relative to the second connecting rod (30), in the direction of the longitudinal axis (X-X) of the turbine engine.
18. Turbine engine according to claim 17, wherein the first pivot pin (29) is located on the opposite side relative to the second connecting rod (30), in the direction of the longitudinal axis (X-X) of the turbine engine.
19. Turbine engine according to claim 13, wherein the second connecting rod (30) is substantially perpendicular to the first connecting rod (25) for at least one position of the control ring (24).
20. Method for adjusting the pitch of radial stator vanes of a turbine engine according to claim 13, when carrying out a maintenance operation or an adjustment of the turbine engine, comprising a step a) consisting in modifying, for at least one vane (5), a first distance (d1), between the third pivot pin (33) and said hinge pin (31).
21. Method according to claim 20, comprising a step b) consisting in modifying, for at least one vane (5), a second distance (d2), between said hinge pin (31) and the second pivot pin (27).
22. Method according to claim 21, wherein, a first position (Ga1) and a second position (Ga2) of the control ring (24) being defined so as to correspond to a first (\u03b81) and a second (\u03b82) pitch angle of each vane (5), as a result of operating conditions of said turbine engine, a preliminary step consists in defining, for each vane (5), the values of said first (d1) and second (d2) distances, making it possible to obtain the first (\u03b81) and second (\u03b82) pitch angles respectively for the first (Ga1) and second (Ga2) positions of the control ring (24), said method then comprising for each vane (5) a step a) and a step b) using the values defined in the preliminary step.