Author: claimsbot

1. A circuit for a compact and low power receiver, the circuit comprising:
a low-power low-noise amplifier (LNA) configured to amplify radio-frequency (RF) signals received from an RF antenna; and
a quadrature mixer coupled to a first and a second trans-impedance amplifiers (TIAs), wherein:
input and output nodes of the first and the second TIAs are cross-coupled via a first and a second resistor, and
the cross coupling is configured to create a complex impedance that replaces one or more LNA load inductors corresponding to one or more frequency bands of the receiver.
2. The circuit of claim 1, wherein the input and out nodes of the first cross coupled TIA are coupled to output and input nodes of the second cross coupled TIA, via the first and the second resistors, respectively.
3. The circuit of claim 1, wherein the created complex impedance is configured to replace the one or more LNA load inductors and to result in a substantial chip area reduction.
4. The circuit of claim 1, wherein the low power LNA comprises a complementary inverter-based LNA with no degeneration inductors.
5. The circuit of claim 4, wherein impedance matching is provided through one or more feedback capacitances including at least one of a parasitic capacitance or an additional on-chip feedback capacitance.
6. The circuit of claim 5, wherein the additional on-chip feedback capacitance is implemented parallel to the parasitic capacitance, and wherein the parasitic capacitance comprises a parasitic gate-drain capacitances.
7. The circuit of claim 5, wherein the low power LNA comprises a complementary inverter-based LNA, and wherein the parasitic capacitance comprises at least one of a parasitic gate-drain capacitance of NMOS or PMOS transistors of the complementary inverter-based LNA.
8. The circuit of claim 5, wherein the impedance matching comprises tunable matching and is provided through one or more programmable feedback capacitances.
9. The circuit of claim 1, wherein the LNA comprises a complementary inverter-based LNA, wherein the complementary inverter-based LNA is implemented on a substantially smaller area and is configured to consume approximately 50% less power, as compared to an inductor degenerated LNA.
10. A method for providing a compact and low power receiver, the method comprising:
providing a low-power low-noise amplifier (LNA);
configured the LNA to amplify radio-frequency (RF) signals received from an RF antenna;
coupling a quadrature mixer to a first and a second trans-impedance amplifiers (TIAs);
cross coupling input and output nodes of the first and the second TIAs via a first and a second resistor; and
configuring the cross coupling to create a complex impedance that replaces one or more LNA load inductors corresponding to one or more frequency bands of the compact and low power receiver.
11. The method of claim 10, further comprising coupling the input and out nodes of the first cross coupled TIA to output and input nodes of the second cross coupled TIA, via the first and the second resistors, respectively.
12. The method of claim 10, further comprising configuring the created complex impedance to substantially reduce chip area by replacing the one or more LNA load inductors.
13. The method of claim 10, further comprising implementing the low power LNA using a complementary inverter-based LNA with no degeneration inductors.
14. The method of claim 13, further comprising providing impedance matching through one or more feedback capacitances including at least one of a parasitic capacitance or an additional on-chip feedback capacitance.
15. The method of claim 14, further comprising implementing the additional on-chip feedback capacitance parallel to the parasitic capacitance, and wherein the parasitic capacitance comprises a parasitic gate-drain capacitances.
16. The method of claim 15, further comprising implementing the low power LNA using a complementary inverter-based LNA, and wherein the parasitic capacitance comprises at least one of a parasitic gate-drain capacitance of NMOS or PMOS transistors of the complementary inverter-based LNA.
17. The method of claim 10, further comprising providing impedance matching through a tunable matching provided through one or more programmable feedback capacitances.
18. The method of claim 10, further comprising:
implementing the low power LNA using a complementary inverter-based LNA; and
implementing the complementary inverter-based LNA on a substantially smaller area,
wherein the complementary inverter-based LNA is configured to consume approximately 50% less power, as compared to an inductor degenerated LNA.
19. A communication device comprising:
an radio-frequency (RF) antenna; and
a compact and low power receiver coupled to the RF antenna, the receiver comprising:
a low-power low-noise amplifier (LNA) configured to amplify RF signals received from the RF antenna; and
a quadrature mixer coupled to a first and a second trans-impedance amplifiers (TIAs),
wherein:
input and output nodes of the first and the second TIAs are cross-coupled via a first and a second resistor, and
the cross coupling is configured to create a complex impedance that replaces one or more LNA load inductors corresponding to one or more frequency bands of the receiver.
20. The communication device of claim 19, wherein:
the input and out nodes of the first cross coupled TIA are coupled to output and input nodes of the second cross coupled TIA, via the first and the second resistors, respectively, and
the low power LNA comprises a complementary inverter-based LNA with no degeneration inductors.

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

1-20. (canceled)
21. A film formation method comprising:
forming a film structure including a first metal contained film on a substrate;
processing the film structure to form a pattern of the film structure and a side wall on the substrate, the side wall contacting with a side surface of the first metal contained film in the pattern of the film structure; and
irradiating gas cluster ions into the side wall on the substrate.
22. The method according to claim 21, wherein
the film structure includes a second metal contained film, and the side wall contacts with the second metal contained film.
23. The method according to claim 21, wherein
the side wall where the gas cluster ions are irradiated is an insulating film.
24. The method according to claim 21, wherein
the gas cluster ions include nitrogen.
25. The method according to claim 21, wherein
the gas cluster ions include oxygen.
26. The method according to claim 21, wherein
the side wall is modified by irradiating the gas cluster ions into the side wall.
27. The method according to claim 21, wherein
an electrical insulation property of the side wall is improved by irradiating the gas cluster ions into the side wall.
28. The method according to claim 21, wherein
a number of atoms contained in the gas cluster ions is not less than 100 and not more than 20,000.
29. The method according to claim 21, wherein
a kinetic energy per atom contained in the gas cluster ions immediately before the irradiation is not less than 1 eV and not more than 30 eV.
30. The method according to claim 21, wherein
the first metal contained film is a lower electrode, the second metal contained film is an upper electrode in a memory unit of a resistance change memory.
31. The method according to claim 22, wherein
the pattern of the film structure further includes a metal oxide film between the first metal contained film and the second metal contained film.
32. The method according to claim 21, wherein
the pattern of the film structure includes a memory cell.
33. The method according to claim 22, wherein
the memory cell is a MTJ element unit of a resistance change memory or a memory unit of a resistance change memory,
the MTJ element unit including:
a lower electrode;
an alloy layer provided on the lower electrode;
a recording layer provided on the alloy layer, the recording layer including CoFeB;
a metal oxide film provided on the recording layer, the metal oxide film including MgO; and
a reference layer including CoFeB, or

the memory unit including:
a lower electrode;
a metal oxide film provided on lower electrode, the metal oxide film including at least one of MgO, TiO2, ZrO2, V2O5, Nb2O5, Ta2O5, TiO2, ZrO, VO, NbO, and TaO; and
an upper electrode provided on the metal oxide film.
34. The method according to claim 21, wherein
the film structure is processed by reactive ion etching to form the pattern of the film structure.
35. A memory device comprising:
a substrate;
a memory cell including a first metal contained film on a substrate; and
a side wall contacting with a side surface of the first metal contained film, and the side wall being irradiated by gas cluster ions.
36. The device according to claim 35, wherein
the memory cell includes a second metal contained film, and the side wall contacts with the second metal contained film.
37. The device according to claim 35, wherein
the side wall where the gas cluster ions are irradiated is an insulating film.
38. The device according to claim 35, wherein
the gas cluster ions include at least one of nitrogen and oxygen.
39. The device according to claim 36, wherein
the memory cell further includes a metal oxide film between the first metal contained film and the second metal contained film.
40. The device according to claim 35, further comprising:
a metal film electrically connected to the first metal contained film.

1. A method for maintaining an aircraft engine, comprising:
inputting a modification scope of at least one maintenance operation for at least one part of an aircraft engine;
generating an expected bill of material comprising said at least one part for said aircraft engine;
tearing down said aircraft engine;
populating an as-received configuration database with at least one part for said aircraft engine;
finding an unexpected part in said aircraft engine;
determining whether to reconfigure said modification scope of said at least one maintenance operation for said aircraft engine based upon finding said unexpected part;
dispositioning said unexpected part;
modifying said as-received configuration database for said aircraft engine based upon the disposition of said unexpected part;
generating for said unexpected part a tag comprising at least a part status;
routing said unexpected part based upon said part status;
generating a should-build database for said aircraft engine based upon the disposition of said unexpected part;
reassembling said aircraft engine; and
generating an as-shipped bill of material comprising said at least one part for a reassembled aircraft engine based upon at least the disposition of said unexpected part.
2. The method of claim 1, wherein finding comprises finding a part not listed on said expected bill of material for said aircraft engine.
3. The method of claim 1, wherein dispositioning comprises the steps of:
determining whether said unexpected part is a planned part of said aircraft engine; and
determining said unexpected part is said planned part.
4. The method of claim 3, further comprising generating for said unexpected part a new tag that indicates said unexpected part is said planned part.
5. The method of claim 1, wherein dispositioning comprises the steps of:
determining whether said unexpected part is a planned part of said aircraft engine;
determining said unexpected part is not said planned part;
determining whether said unexpected part is reoperable to produce said planned part; and
reoperating said unexpected part to produce said planned part.
6. The method of claim 5, further comprising generating for said planned part a new tag that indicates said planned part comprises a reoperated unexpected part.
7. The method of claim 5, wherein reoperating comprises performing an internal repair, an external repair or both said internal repair and said external repair upon said unexpected part.
8. The method of claim 1, wherein dispositioning comprises the steps of:
determining whether said unexpected part is a planned part of said aircraft engine;
determining said unexpected part is not said planned part;
determining said unexpected part is not reoperable to produce said planned part; and
removing said unexpected part from said as-received configuration database.
9. The method of claim 8, further comprising generating for said unexpected part a new tag that indicates said unexpected part has been removed.
10. The method of claim 1, wherein routing comprises the steps of:
generating at least one work instruction for said unexpected part;
determining at least one location where said at least one work instruction is performed; and
routing said unexpected part to said at least one location.
11. The method of claim 10, further comprising generating for said unexpected part a new tag that indicates at least one routing instruction for said unexpected part.
12. The method of claim 1, wherein dispositioning comprises the steps of:
determining whether said unexpected part is a planned part of said aircraft engine;
determining said unexpected part is not said planned part;
comparing said unexpected part with at least one replacement part of said aircraft engine;
matching said unexpected part with said at least one replacement part; and
replacing said unexpected part with said replacement part.
13. The method of claim 12, further comprising generating for said replacement part a new tag that indicates said replacement part replaced said unexpected part.
14. The method of claim 12, wherein comparing comprises comparing a first location identifier of said unexpected part to a second location identifier of said at least one replacement part using at least one service bulletin of said aircraft engine.
15. A system for maintaining an aircraft engine, comprising:
means for inputting in a computer readable storage device a modification scope of at least one maintenance operation for at least one part of an aircraft engine;
means for generating in said computer readable storage device an expected bill of material comprising said at least one part for said aircraft engine;
means for populating in said computer readable storage device an as-received configuration database with at least one part for said aircraft engine;
means for determining whether to reconfigure said modification scope of said at least one maintenance operation for said aircraft engine based upon an unexpected part;
means for dispositioning in said computer readable storage device said unexpected part;
means for modifying in said computer readable storage device said as-received configuration database for said aircraft engine based upon the disposition of said unexpected part;
means for generating in said computer readable storage device a tag comprising at least a part status of said unexpected part;
means for routing said unexpected part based upon said part status;
means for generating in said computer readable storage device a should-build database for said aircraft engine based upon the disposition of said unexpected part; and
means for generating in said computer readable storage medium an as-shipped bill of material comprising said at least one part for a reassembled aircraft engine based upon at least the disposition of said unexpected part.
16. The system of claim 15, wherein means for dispositioning comprises:
means for determining whether said unexpected part is a planned part of said aircraft engine; and
means for determining said unexpected part is said planned part.
17. The system of claim 16, further comprising means for generating for said unexpected part a new tag that indicates said unexpected part is said planned part.
18. The system of claim 15, wherein means for dispositioning comprises:
means for determining whether said unexpected part is a planned part of said engine;
means for determining said unexpected part is not said planned part;
means for determining whether said unexpected part is reoperable to produce said planned part; and
means for reoperating said unexpected part to produce said planned part.
19. The system of claim 18, further comprising means for generating for said planned part a new tag that indicates said planned part comprises a reoperated unexpected part.
20. The system of claim 15, wherein dispositioning comprises:
means for determining whether said unexpected part is a planned part of said engine;
means for determining said unexpected part is not said planned part;
means for determining said unexpected part is not reoperable to produce said planned part; and
means for removing said unexpected part from said as-recieved configuration database.
21. The system of claim 20, further comprising means for generating for said unexpected part a new tag that indicates said unexpected part has been removed.
22. The system of claim 15, wherein means for routing comprises:
means for generating at least one work instruction for said unexpected part;
means for determining at least one location where said at least one work instruction is performed; and
means for routing said unexpected part to said at least one location.
23. The system of claim 22, further comprising means for generating for said unexpected part a new tag that indicates at least one routing instruction for said unexpected part.
24. The system of claim 15, wherein means for dispositioning comprises:
means for determining whether said unexpected part is a planned part of said engine;
means for determining said unexpected part is not said planned part;
means for comparing said unexpected part with at least one replacement part of said engine;
means for matching said unexpected part with said at least one replacement part; and
means for replacing said unexpected part with said replacement part.
25. The system of claim 24, further comprising means for generating for said replacement part a new tag that indicates said replacement part replaced said unexpected part.
26. The system of claim 24, wherein means for comparing comprises means for comparing a first location identifier of said unexpected part to a second location identifier of said at least one replacement part using at least one service bulletin of said engine.

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. An assembly for a turbocharger, comprising:
a turbine comprising a turbine housing and a turbine wheel mounted in the turbine housing and connected to a rotatable shaft for rotation therewith;
a center housing for containing a bearing for the shaft, the center housing defining a generally planar first surface facing generally axially toward and axially spaced from a generally planar opposing surface of the turbine housing, the first surface being spaced axially from the turbine wheel by a first axial distance;
the turbine housing further comprising a generally cylindrical surface facing radially inwardly and located radially inwardly relative to said opposing surface; and
a heat shield disposed between the center housing and the turbine housing, the heat shield having an outer portion captured between the first surface of the center housing and the opposing surface of the turbine housing, and a centering portion extending from the outer portion generally axially toward the turbine wheel, the centering portion passing directly radially inwardly of the generally cylindrical surface of the turbine housing, the centering portion having a non-axisymmetric configuration characterized by a plurality of relatively smaller-radius portions alternating in a circumferential direction with a plurality of relatively larger-radius portions, radial clearances existing between the smaller-radius portions and the generally cylindrical surface of the turbine housing, the larger-radius portions engaging the generally cylindrical surface of the turbine housing so as to locate the heat shield substantially coaxially with respect to a central longitudinal axis of the turbine housing.
2. The assembly of claim 1, wherein the heat shield includes an inner portion joined with the centering portion and extending radially inwardly therefrom, and the inner portion is axially spaced from the center housing.
3. The assembly of claim 1, wherein the center housing includes a generally cylindrical surface facing radially outwardly and located radially outwardly relative to the first surface and spaced axially from the turbine wheel by a distance greater than the first axial distance, the generally cylindrical surface of the center housing being substantially coaxial with a central longitudinal axis of the center housing, and the turbine housing includes a second generally cylindrical surface facing radially inwardly and engaged with the generally cylindrical surface of the center housing for coaxially locating the turbine housing relative to the center housing.
4. The assembly of claim 3, wherein a juncture extends between the second generally cylindrical surface of the turbine housing and said opposing surface of the turbine housing, the juncture comprising a smoothly curved radius.
5. The assembly of claim 4, wherein a radially outermost edge of the heat shield is spaced radially inward of the juncture.
6. The assembly of claim 1, wherein the heat shield has four of the relatively larger-radius portions spaced about a circumference of the heat shield.
7. A heat shield for being disposed between a center housing and a turbine housing of a turbocharger, the heat shield comprising:
a generally annular body having an annular outer portion that extends generally radially and a centering portion that extends generally axially from a radially inner end of the outer portion, the centering portion having a non-axisymmetric configuration characterized by a plurality of relatively smaller-radius portions alternating in a circumferential direction with a plurality of relatively larger-radius portions.
8. The heat shield of claim 7, further comprising an inner portion joined with the centering portion and extending radially inwardly therefrom.