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An apparatus and a method for controlling operation of a linear motor compressor, by which a linear motor compressor can operate always in an optimum condition by coping with the load variation due to changes in a refrigerator and the circumstances. In more detail, a current peak value at TDC=0 is d

An apparatus and a method for controlling operation of a linear motor compressor, by which a linear motor compressor can operate always in an optimum condition by coping with the load variation due to changes in a refrigerator and the circumstances. In more detail, a current peak value at TDC=0 is detected by comparing a current applied to the linear motor compressor with a formerly detected current, and accordingly the linear motor compressor is operated by a switching control signal generated according to a duty-ratio corresponding to the current peak value.

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An apparatus and a method for controlling operation of a linear motor compressor, by which a linear motor compressor can operate always in an optimum condition by coping with the load variation due to changes in a refrigerator and the circumstances. In more detail, a current peak value at TDC=0 is d

An apparatus and a method for controlling operation of a linear motor compressor, by which a linear motor compressor can operate always in an optimum condition by coping with the load variation due to changes in a refrigerator and the circumstances. In more detail, a current peak value at TDC=0 is detected by comparing a current applied to the linear motor compressor with a formerly detected current, and accordingly the linear motor compressor is operated by a switching control signal generated according to a duty-ratio corresponding to the current peak value. hydrophobic coating is a single layer having a gradient of hardness over the depth of the single layer. 6. The low-pressure turbine according to claim 5, wherein: a depth range near the top of the gradient layer is softer than a remaining depth of the gradient layer, and the depth range near the top of the gradient layer has a hardness between 500 and 1500 Vickers. 7. The low-pressure turbine according to claim 6, wherein: the depth range near the top of the gradient layer has a thickness between 0.1 and 2 micrometers. 8. The low-pressure turbine according to claim 6, wherein: the remaining depth of the gradient layer has a hardness between 1500 and 3000 Vickers and a thickness between 0.1 and 6 micrometers. 9. The low-pressure turbine according to claim 2, wherein: the hydrophobic coating includes a sequence of discrete layers including at least one relatively harder layer with amorphous carbon and at least one relatively softer layer with amorphous carbon or a plasma polymer; at least one relatively harder layer and at least one relatively softer layer are applied alternately to the surfaces of the blades, and the lowest layer of the sequence of layers is a relatively harder layer with amorphous carbon or a plasma polymer, and the uppermost layer of the sequence of layers is a relatively softer layer with amorphous carbon or a plasma polymer, and at least the uppermost, relatively softer layer has a hydrophobic property. 10. The low-pressure turbine according to claim 9, wherein: the at least one relatively harder layer with amorphous carbon or a plasma polymer each has a hardness between 1500 and 3000 Vickers, and the at least one relatively softer layer with amorphous carbon or a plasma polymer has a hardness between 500 and 1500 Vickers. 11. The low-pressure turbine according to claim 9, wherein: the at least one relatively harder and at least one relatively softer layers of the sequence of discrete layers each have a thickness between 0.1 and 2 micrometers. 12. The low-pressure turbine according to claim 9, wherein: the thicknesses of the relatively harder and relatively softer layers are inversely proportional to their hardness. 13. The low-pressure turbine according to claim 1, wherein: an adhesion layer is applied between the surface of the blades and the coating. 14. The low-pressure turbine according to claim 1, wherein: the coating is applied to the surfaces of the stationary and the rotating blades of the low-pressure turbine. the channel, and having a second surface coupled to the first surface, and substantially parallel to a wall of the channel and extending axially along the channel, such that flow into and out of the annular channel of the inner portion of the inlet is partially obstructed; wherein the central channel and the annular channel of the inner portion of the inlet are each in communication with the compressor wheel. 2. A turbocharger as defined in claim 1 further comprising: a noise suppressor attached to the housing at the outer portion of the inlet, the noise suppressor having an outer diameter greater than the outer diameter of the annular channel of the inner portion of the inlet, and having an inner diameter less than the inner diameter of the annular channel of the inner portion of the inlet. 3. A turbocharger as defined in claim 2 further comprising: a channel in the inner radial wall that is in air-flow communication with the vanes of the compressor wheel and the annular channel. 4. A turbocharger as defined in claim 3 further comprising: a plurality of apertures in the inner radial wall that provide communication between the vanes of the compressor wheel and the annular channel. 5. A turbocharger as defined in claim 1 wherein: the inner deflector has a substantially "J" shaped cross section. 6. A turbocharger as defined in claim 1 wherein: the inner deflector has a substantially "L" shaped cross section. 7. A turbocharger as defined in claim 1 wherein: the first and second surfaces of the inner deflector are configured to prevent "line of sight" emission of sound waves from the annular channel. 8. A turbocharger as defined in claim 1 wherein: the inner deflector further comprises a third surface substantially parallel to and coupled with the annular channel. 9. A turbocharger as defined in claim 7 wherein: the first and second surfaces of the inner deflector are configured to dampen sound waves. 10. A turbocharger as defined in claim 7 wherein: the first and second surfaces of the inner deflector are configured to cancel sound waves. 11. A turbocharger as defined in claim 7 further comprising: sound insulating material in the annular channel. 12. A turbocharger as defined in claim 11 further comprising: sound insulating material in the inlet and outlet. 13. An inner deflector ring for use in a bypass port compressor having an axial inlet defining a central channel and an annular channel disposed concentrically therearound, a compressor wheel disposed within the compressor, and an aperture providing communication between compressor wheel and the annular channel, the inner deflector ring comprising: a first substantially radially extending surface, for obstructing flow along the annular channel, and a second substantially axially extending surface. 14. An inner deflector ring as defined in claim 13 further comprising: a third axially extending surface extending along the annular channel and separated from the first axially extending surface by the second radially extending surface, which is disposed therebetween. 15. A turbocharger system having a noise reduction device comprising: a bypass port compressor having a housing, a concentric inner radial wall and outer radial wall collectively defining the compressor inlet, the inner radial wall circumscribing a central channel, and an annular channel interposed between the outer radial wall and the inner radial wall, the annular channel being disposed concentrically around the central channel, a compressor outlet, a compressor wheel having a plurality of vanes, the wheel located between the inlet and outlet and in communication with both the central and annular channels; and an inner deflector disposed within the annular channel, having a first surface extending radially across the annular channel, and a second surface extending axially along the annular channel, to partially obstruct flow into and out of the