RU2750512C2 - System and method for reducing turbocharger compressor noise - Google Patents

Abstract

FIELD: compressors.

SUBSTANCE: methods and systems for the engine turbocharger compressor are presented. For example, a compressor may contain a passageway and a resonant chamber surrounding the passageway, with the passageway being fluidly connected to the resonant chamber via a recirculation channel, a discharge channel, and a plurality of openings located between the recirculation channel and the discharge channel.

EFFECT: due to the passage of the fluid from the resonant chamber through the holes in the passageway, the noise level of the compressor can be reduced.

20 cl, 26 dwg

Description

Cross-references to related claims

This application is a partial continuation of US patent application No. 14/841391, entitled "SYSTEM AND METHOD FOR REDUCING TURBOCHARGER COMPRESSOR NOISE", filed August 31, 2015. US patent application No. 14/841391 is a continuation of US patent application No. 13/528622, entitled " SYSTEM AND METHOD FOR TURBOCHARGER COMPRESSOR NOISE REDUCTION ", filed June 20, 2012, currently US Patent No. 9303561. The entire content of each of the above applications is hereby incorporated by reference in its entirety into this application in all respects.

Technology area

This application relates to methods and systems for engine intake systems equipped with compressors and using pressurization systems such as turbochargers and, in particular, turbocharger embodiments, methods and systems that reduce the noise generated by the turbocharger compressor.

Background and disclosure of the invention

Automotive engines may include turbochargers or mechanical superchargers configured to supply an increased amount of air to the engine intake manifold and combustion chamber by compressing the intake air with the turbocharger. In some cases, the compressor may be driven by a turbine configured to obtain energy from the exhaust gas stream of the engine. Transient and steady-state compressor operating conditions exhibit deficiencies known as noise, vibration, and NVH harshness, characterized by whistling or whistling noise. The whistling condition can cause unwanted or unacceptable levels of WSP, which can also lead to turbocharger or engine surging. In particular, turbochargers comprising a compressor with a ducted shroud housing can create problems in the form of noise generated by the BPF of the compressor impeller.

Attempts have been made to reduce noise from turbocharger compressors. One attempt involves the use of small channels to disrupt the boundary layer in the region of the incoming fluid flow to the turbocharger. Another attempt at noise reduction is disclosed by Dimer et al. In US Patent Publication 2010/0098532. According to Daimer et al., It is proposed to reduce the turbocharger noise resulting from stalling by means of indentations surrounding the leading edge of the compressor splitter vanes. The recess is located downstream of the leading edge of the main blades, which provides a path for fluid around the rotating stall area.

Other attempts to minimize compressor noise include various recirculation nozzles in which a portion of the stream is recirculated from downstream to upstream through a nozzle separated from the main flow nozzle. One example of such an approach is disclosed by Sirakov et al. In US Pat. No. 7,942,625. Sirakov proposes the use of a branch duct downstream of the leading edge of the blade, which allows a portion of the fluid passing through the compressor to re-circulate to the upstream region through the inner cavity and injection nozzle ...

However, the present inventors have found possible drawbacks in such systems. For example, these approaches do not investigate the compressor fluid flow path in the leading edge region of the main blade, and these approaches cannot effectively address the whistling noise problem as well. In addition, these approaches are not designed for wideband whistling noise with minimal impact on the fluid flow region, and in particular, these approaches do not address the problem of noise resulting from the frequency of passage of compressor impeller blades.

In one example, the above problems can be solved by using a compressor comprising: a housing; a passageway formed by the inner surface of the housing; a compressor wheel located in said housing downstream of the flow passage and having at least one main blade; a resonance chamber formed within the housing surrounding the passageway and in fluid communication with the passageway through the recirculation passage and the bypass passage; and an opening formed between the resonance chamber and the passageway and connected to the passageway between the recirculation passage and the bypass passage. According to one example, the compressor may further comprise a flow disturbance device formed by the bore and the opening may be one of a plurality of openings. The flow perturbation device may comprise a change in the cross-sectional region in the flow path, and this change, located at the leading edges of the main compressor blades, can reduce whistling. In addition, embodiments may comprise flow disturbance device components whose dimensions and proportions can be measured in accordance with some mathematical formula relating the components in this manner to one or more predetermined whistle noise frequencies. Thus, the combination of the flow disturbance device and the holes can disrupt the flow of air through the compressor, which can affect the wide frequency range corresponding to the whistle, and thus can reduce the noise generated by the compressor.

It should be understood that the above summary of the invention is only for acquaintance in a simple form with some concepts, which will be further disclosed in detail in the section "Implementation of the invention". This disclosure is not intended to denote key or essential features of the claimed subject matter, the scope of which is unambiguously defined by the claims following the "Implementation of the Invention" section. In addition, the claimed subject matter is not limited to embodiments that obviate any of the disadvantages recited above or in any other part of the present disclosure.

Brief Description of Drawings

FIG. 1 shows an example of a schematic diagram of a vehicle system containing a turbocharger.

FIG. 2 is a cross-sectional perspective view of a turbocharger including a compressor with a compressor inlet.

FIG. 3 is a cross-sectional view of an example of a compressor comprising a first embodiment of a flow disturbance device and a plurality of flow disturbance holes.

FIG. 4 is an enlarged view of a second embodiment of a flow disturbance device and a flow disturbance orifice.

FIG. 5 is an enlarged view of a third embodiment of a flow disturbance device and a flow disturbance orifice.

FIG. 6 is an enlarged view of a fourth embodiment of a flow disturbance device and a flow disturbance orifice.

FIG. 7 is an enlarged view of a fifth embodiment of a flow disturbance device and a flow disturbance orifice.

FIG. 8 is an enlarged view of a sixth embodiment of a flow disturbance device and a flow disturbance orifice.

FIG. 9 is a cross-sectional view of a compressor including a seventh embodiment of a flow disturbance device and a plurality of flow disturbance orifices.

FIG. 10 is an enlarged view of a seventh embodiment of the flow disturbance device and flow disturbance orifice.

FIG. 11 is an enlarged view of an eighth embodiment of a flow disturbance device and a flow disturbance orifice.

FIG. 12 is an enlarged view of a ninth embodiment of the flow disturbance device and flow disturbance orifice.

FIG. 13 is an enlarged view of a tenth embodiment of a flow disturbance device and a flow disturbance orifice.

FIG. 14 is an enlarged view of an eleventh embodiment of the flow disturbance device and flow disturbance orifice.

FIG. 15 is a cross-sectional view of a compressor comprising a twelfth embodiment of a flow disturbance device and a plurality of flow disturbance orifices.

FIG. 16 is a cross-sectional view of a compressor including a thirteenth embodiment of a flow disturbance device and a plurality of flow disturbance orifices.

FIG. 17 is a perspective view of a compressor inlet where the inlet includes a plurality of flow disturbance orifices.

FIG. 18-20 show various embodiments of compressors having a plurality of flow disturbance orifices.

FIG. 21-26 show various embodiments of compressors comprising a flow perturbation device.

FIG. 2-26 are to some extent, although other relative dimensions may be used.

Implementation of the invention

The following disclosure relates to systems and methods for a turbocharger compressor. An automobile system, such as the automobile system shown in FIG. 1 may include an engine, an engine intake system, an engine exhaust system, and a turbocharger connected between the intake system and the exhaust system. A turbocharger, such as the turbocharger shown in FIG. 2 comprises a turbine located inside the exhaust system and a compressor located inside the intake system, the turbine and the compressor being connected to each other by means of a shaft. The exhaust gases from the engine can pass through the turbocharger so that the turbine can rotate, the rotation of the turbine causing the compressor impeller to rotate. As the impeller rotates, air can be drawn into the compressor inlet and can flow through the central bore (which may be referred to herein as the “bore” or “inlet bore”) of the compressor, for example through the bore shown in FIG. 3.

The passageway may include a flow disturbance device (which may be referred to herein as a “annular flow disturbance device”) as shown in FIG. 3-16, and may further comprise at least one opening as shown in FIG. 2-26. For example, the diameter of the passageway in the flow disturbance device may be different from the diameter of the passageway in regions upstream of the flow disturbance device. A resonance chamber (which may be referred to herein as a "channel band", "annular chamber" or simply "chamber") surrounds the outer perimeter of the passageway and may contain one or more holes or openings formed between the inner perimeter of the passageway and the resonance camera. For example, each hole may be equidistant from each adjacent hole, as shown in FIG. 17. In another example, one or more openings may extend radially about the central axis of the passageway, as shown in FIG. 18. In another example, one or more holes may extend in an angular direction about a central axis as shown in FIG. 19. In another example, one or more openings may be located at a first distance from the branch duct and a second distance from the recirculation duct, where the first distance is different from the second distance, as shown in FIG. 20. In some embodiments, another flow disturbance device (such a device may be referred to herein as an “edge break”) may be located upstream of the openings, as shown in FIG. 21-24. In other embodiments, the flow disturbance device may be located downstream of the branch duct, as shown in FIG. 25 and upstream of the compressor wheel. In other embodiments, the flow disturbance device may be located upstream of the branch passage and downstream of the orifices, as shown in FIG. 26.

FIG. 1 shows a schematic diagram of a vehicle system 116. The vehicle system 116 comprises an engine system 118 coupled to an exhaust system 122 for reducing toxicity of the exhaust gases. Engine system 118 includes an engine 110 with multiple cylinders 130. Engine 110 includes an engine intake system 123 and an engine exhaust system 125. Engine intake system 123 includes a throttle 162 fluidly connected to intake manifold 144 via intake manifold 141. Engine exhaust system 125 includes exhaust manifold 148 fluidly connected to exhaust manifold 135 configured to direct exhaust gases to atmosphere. Throttle 162 may be located in inlet 141 downstream of the boost device, such as turbocharger 150 or a mechanical supercharger.

Turbocharger 150 includes a compressor 152 disposed between inlet 141 and inlet manifold 144. For example, compressor 152 may be a compressor having a bore with channels as shown in FIG. 3 and is disclosed in more detail below. Compressor 152 may be at least partially driven by an exhaust turbine 154 positioned between exhaust manifold 148 and outlet 135. Compressor 152 may be connected to exhaust turbine 154 via shaft 156. Compressor 152 may also at least partially driven by an electric motor 158. In the illustrated example, electric motor 158 is shown coupled to shaft 156. However, other suitable motor configurations are possible.

In one example, motor 158 may be powered by stored power from a system battery (not shown in the diagram) when the battery's electrical charge level is greater than a threshold charge level. Electric motor 158 is configured to drive turbocharger 150 (eg, during engine cranking) to provide electric boost (e-boost) to supply boost air. Thus, the electric motor 158 can work in conjunction with a supercharger (eg, turbocharger 150), providing increased performance of the supercharger (for example, to increase the amount of compressed air leaving the compressor 152). During engine 110 operation, exhaust gases generated by engine 110 may flow from the exhaust manifold to outlet 135 and drive exhaust turbine 154. However, if engine 110 has not been run for a sufficient amount of time (for example, if the period of time since starting the engine 110, less than the threshold time), then the flow of exhaust gases through the outlet nozzle 135 may not be high enough to spin the exhaust turbine 154 to normal operating speed (for example, up to the speed required for steady flow of compressed air from compressor 152). As a result, the electric motor 158 can be battery driven to spin the exhaust turbine 154 (and thus drive the compressor 152) until the exhaust mass flow rate has increased above the threshold flow rate. Therefore, when the exhaust gas mass flow rate increases, the amount of assistance provided by the electric motor 158 (eg, the amount and / or duration of power supply to the electric motor) can be reduced. Thus, during operation of the turbocharger, depending on the operation of the exhaust turbine, the degree of assistance received by the engine and provided by the electric motor 158 can be adjusted.

The exhaust system 125 of the engine may be connected to an exhaust system 122 located in the exhaust manifold 135. The exhaust system 122 may contain one or more exhaust gas control devices 170, which may be located in close proximity to each other. other at outlet 135. One or more exhaust gas control devices 170 may comprise a three way catalytic converter, a lean mixture nitrogen oxide (NOx) filter, a SCR catalyst, and so on. The catalysts can be configured to catalytically convert toxic combustion by-products generated in the exhaust gases, for example, various nitrogen oxides NOx, unburned hydrocarbons, carbon monoxide, etc., into less toxic substances before being released to the atmosphere. However, the catalytic efficiency of a catalyst can be greatly influenced by the temperature of the exhaust gases. For example, reducing the amount of nitrogen oxides NOx may require higher temperatures than the oxidation of carbon monoxide. At low temperatures, unwanted side reactions can also occur, such as the formation of ammonia and N2O species, which can negatively affect the emission control efficiency and reduce the quality of the exhaust gas emissions. Thus, the catalytic treatment of the exhaust gases can be delayed until the activation temperature of the catalyst (s) is reached. The exhaust system 122 may also include hydrocarbon recovery devices, particulate matter recovery devices, and other appropriate exhaust gas emission devices (not shown in the diagram). It will be appreciated that other components may be used in the engine system 118, such as various valves and sensors. For example, engine system 118 may further comprise a plurality of intake valves, exhaust valves, exhaust and / or intake bypass valves, temperature sensors, flow sensors, and the like.

The vehicle system 116 may further comprise a control system 114. It is shown that the control system 114 can receive information from a plurality of sensors 117 (various examples of which are disclosed herein) and send control signals to a plurality of actuators 181 (various examples of which are disclosed herein). For example, the sensors 117 may include an exhaust gas sensor 126 (located in the exhaust manifold 148), a temperature sensor 191, and a pressure sensor 193 (located downstream of the emission control devices 170). Other sensors such as pressure, temperature, air-fuel ratio, and composition sensors may be installed at various locations in the vehicle system 116. Actuators 181 may include, by way of example, fuel injectors (not shown in the diagram), a plurality of valves, a pump, and a throttle 162. Control system 114 may include controller 112. Controller 112 may receive signals from various sensors shown in FIG. 1 and use the various actuators shown in FIG. 1, to regulate the operation of the engine based on the received signals and instructions stored in the memory of the controller. For example, adjusting the amount of intake air to the engine 110 may include adjusting the throttle position 162 to increase or decrease the amount of intake air passing through the intake manifold 144 to the engine 110. In another example, adjusting the speed of the compressor 152 may comprise adjusting the compressor drive 152 (for example, adjusting the amount of electricity supplied to the electric motor 158) to increase or decrease the rotational speed of the compressor 152.

FIG. 2 shows an example of a turbocharger 202 similar to turbocharger 150 shown in FIG. 1, with a perspective view. For example, turbocharger 202 shown in FIG. 2, (as well as other turbochargers and compressors disclosed herein) may be included in an engine system such as engine system 118 shown in FIG. 1. Turbocharger 202 shown in FIG. 2 includes a compressor 200 similar to compressor 152 shown in FIG. 1, where compressor 200 is shown in cross section. Compressor 200 includes a housing 203, an inlet end 201, a port 204 (which may be referred to herein as a “center port”), and an impeller 206 disclosed below.

The passageway 204 of the compressor 200 is configured to direct air from the end 201 of the inlet of the compressor 200 to the end 213 of the outlet located downstream of the impeller 206. The passageway 204 may be connected to an inlet (not shown in FIG. 2), for example, with inlet 141 shown in FIG. 1 and disclosed above. The impeller 206 is coupled to the exhaust turbine 207 via a shaft 209. As the exhaust gases pass through the exhaust turbine 207, they can rotate the impeller 206, as discussed above with respect to turbocharger 150 in FIG. 1. Rotation of the impeller 206 allows air to be directed from the inlet and through the inlet end 201 of the compressor 200. The inlet air 211 can move through the passageway 204, through the impeller 206 and into the volute 215. The compressed inlet air can then exit the compressor 200 through the end 213 of the outlet.

In the example shown in FIG. 2, the housing 203 of the compressor 200 is a housing with a channeling band. In other words, the housing 203 includes a resonance chamber 208 surrounded by the outer perimeter of the passageway 204 and located (for example, formed) between the outer surface 241 of the passageway 204 and the inner surface 242 of the housing 203. The outer surface 241 of the passageway 204 and the inner surface 242 of the housing 203 are connected by a plurality of spacers 210 extending from the inner surface 242 to the outer surface 241 in a perpendicular direction to the central axis 205 of the flow passage 204. In the examples disclosed herein, the center axis of the flow passage is also the center axis of the casing and the compressor, and may thus be referred to as ...

During operation of compressor 200 (eg, while intake air may pass through inlet end 201 and through passageway 204), rotation of impeller 206 and intake air flow through compressor 200 may generate noise. Resonance chamber 208 can be used to reduce noise generated by compressor 200. For example, as intake air moves through passageway 204, acoustic resonance may develop within passageway 204. Due to the fact that the passageway 204 is surrounded by the resonance chamber 208, air can flow from the passageway 204 into the resonance chamber 208 through the passageway 214, thereby reducing resonance within the passageway 204. In other words, the passageway 214 provides a fluid connection. the environment of the passage channel 204 with a resonance chamber 208.

However, while resonance chamber 208 may reduce the amount of sounds produced by compressor 200, noise (eg, acoustic resonance) may also develop within resonance chamber 208. To reduce the amount of noise generated by the resonance chamber 208, openings 212 are connected to the passageway 204 upstream of the branch passage 214. Each opening 212 extends between the passageway 204 and the resonance chamber 208 in a radial direction about the central axis 205, and each opening 212 provides a fluid connection of the passageway 204 to the resonance chamber 208. For example, a portion of the air moving through the passageway 204 may enter through the outlet passage 214 into the resonance chamber 208. The air passing into the passageway 208 may then flow back into the passageway 204 through one or more holes 212. By directing air from the resonance chamber 208 to the passageway 204, it is possible to reduce the air pressure inside the resonance chamber 208 and the noise generated by the resonance chamber 208. By directing air from the passageway 204 to the resonance chamber 208 through the bypass passage 214 the first amount of noise can be eliminated by the compressor 200, while directing the air from the resonance chamber 208 back into the passageway 204 through one or more openings 212 can eliminate the second amount of noise generated by the compressor 200.

FIG. 2-17 show various embodiments of compressors or compressor parts, with each embodiment having a plurality of openings configured to provide a fluid connection between the resonance chamber surrounding the bore and the bore. In some examples, the compressor may also include a flow disturbance device located within the passageway. For example, a flow perturbation device may include a step, where the step is located at an angle relative to the central axis, in the range between 10 and 170 degrees. In other examples, the step may have other configurations and may be formed by multiple surfaces. Examples of steps, flow disturbance devices and openings are disclosed below. In alternative embodiments, the compressors shown in FIG. 2-17 may not include a flow disturbance device and may instead comprise a relatively straight passageway with openings located between the passageway and the resonance chamber.

FIG. 3 is a cross-sectional view of an example of a compressor 300 similar to compressor 152 shown in FIG. 1 or compressor 200 shown in FIG. 2 and disclosed above. Compressor 300 includes a housing 322 having an inlet end 301 and an outlet end 331. Passage 304 within housing 322 is configured to pass incoming intake air 332 from inlet end 301 to outlet end 331 and may have a substantially continuous interior surface 328 (which may be referred to herein as “interior surface”). Shown is the central axis 330 of the port 304, where the central axis 330 extends through the center of the port 304. A compressor wheel 306 is located within the housing 322 and contains at least one main blade 334. The compressor wheel 306 is connected to a shaft 336 and is rotatable within the housing 322 to compress the intake air. The housing 322 may include a flow disturbance device 316 configured to disrupt the inner surface 328. In the example shown in FIG. 3, the flow disturbance device 316 is located at the leading edge 326 of at least one main vane 334. In other words, the flow disturbance device 316 is axially aligned with the front edge 326 about the central axis 330.

Passage 304 may have a substantially circular cross-section, and flow disturbance device 316 may be a step 318 at the location where passage 304 is greatly reduced in diameter (eg, decreases from a first diameter 327 to a second diameter 329). In the example shown in FIG. 3, the step 318 is a portion of the inner surface 328 extending towards the central axis 330. In FIG. 4 shows an enlarged view of step 318 and is disclosed below. By forming the flow disturbance device 316 in the form of a step 318, the cross-sectional area of the flow passage 304 can be reduced. For example, when the flow passage 304 has a cylindrical shape (eg, circular cross section) as shown in FIG. 3, staging 318 allows the flow diameter in port 304 to be reduced, which can reduce axial inlet flow, and may also, or instead, increase compressor surge margin (e.g., reduce the chance of compressor surge during compressor 300 operation), and reduce whistling (for example, reduce the amount of noise generated by the compressor 300).

The housing 322 of the compressor 300 is a ducted shroud housing similar to the housing 203 shown in FIG. 2 and disclosed above. Compressor 300 includes a resonance chamber 308 formed by a housing 322 and surrounding the port 304. In other words, as disclosed above with reference to the resonance chamber 208 shown in FIG. 2, the resonance chamber 308 shown in FIG. 3 is formed between the outer surface 341 of the bore 304 and the inner surface 340 of the housing 322. Thus, the resonance chamber surrounds the outside of the bore 304 (eg, around its entire circumference). Spacer 342, similar to spacer 210 shown in FIG. 2, connects the outer surface 341 to the inner surface 340. The resonance chamber 308 is fluidly connected to the passageway 304 through the branch duct 314, the recirculation duct 302, and a plurality of openings 312. For example, the branch duct 314 and the recirculation duct 302 may be annular channels, formed by the inner surface 328 of the bore 304 and located between the bore 304 and the resonance chamber 308 (e.g., extending between the inner surface 328 and the outer surface 341 of the bore 304 in a radial direction relative to the central axis 330) to provide a fluid connection of the bore 304 with the resonance chamber 308. In other words, the bypass duct 314 and the recirculation duct 302 are formed by the inner surface 328 and extend along the inner perimeter of the passage duct 304. The duct 314 is located downstream of the recirculation duct 302 with respect to the air flow in the passage duct 304. For example, branch duct 314 is located downstream of leading edge 326 of at least one main blade 334, and recirculation duct 302 is located upstream of leading edge 326. Vent duct 314 is positioned such that a portion of the air leaving at least of one main blade 334, when the compressor wheel 306 rotates, can pass through the exhaust duct 314 and into the resonance chamber 308. Air can then pass through the resonance chamber 308 and can return to the passage duct 304 through the recirculation duct 302 and / or through the openings 312, and the amount of air exiting the resonance chamber 308 into the passageway 304 through the recirculation passage 302 is greater than the amount of air exiting the resonance chamber 308 into the passageway 304 through the openings 312 because the size of the openings 312 is smaller than the size of the return passage 302, as disclosed below.

Unlike the branch duct 314 and the recirculation duct 302, the openings 312 are not annular ducts. Instead, for example, each orifice 312 may extend between bore 304 and resonance chamber 308 radially about central axis 330 to provide fluid communication of bore 304 with resonance chamber 308. However, the apertures 312 do not form an annular opening around the inner perimeter passageway 304. Instead, each opening 312 may have an elliptical or circular cross-section, with each opening 312 spaced from the other opening 312 such that each opening 312 forms a cylindrical passageway between passageway 304 and resonance chamber 308. For example, each opening 312 may extend between bore 304 and resonance chamber 308 radially about central axis 330 (eg, as shown in FIG. 18). In another example, each aperture 312 may extend between bore 304 and resonance chamber 308 in an angular direction about a central axis 330 (eg, as shown in FIG. 19). For example, compressor 300 may include three different ports 312 in an embodiment similar to ports 212 shown in FIG. 2, with two openings 312 visible in the cross-section shown in FIG. 3. Each orifice 312 extends from the inner surface 328 of the bore 304 to the outer surface 341 of the bore 304. Thus, a fluid (e.g., air) can move between the bore 304 and the resonance chamber 308 through each of the apertures 312 such that passageway 304 is fluidly connected to resonance chamber 308 through openings 312. In addition, fluid can move between passageway 304 and resonance chamber 308 through both branch passage 314 and recirculation passage 302. However, although the passageway 304 is in fluid communication with the resonance chamber 308 through the recirculation passage 302, the amount of air that can move into the passageway 304 through the recirculation passage 302 is much less than the amount of air that can move into the passageway 304 through the end 301 of the inlet. In addition, although the passageway 304 further has a fluid connection to the resonance chamber 308 through the openings 312, the amount of air that can move into the passageway 304 through the openings 312 is less than the amount of air that can move into the passageway 304 through the passage 302 recirculation. Thus, the holes 312 can reduce the air pressure within the resonance chamber 308.

In an example of fluid movement through passage 304, air may pass through inlet end 301 of compressor 300 and travel through passage 304 towards compressor wheel 306. Since air can move towards the leading edge 326 of at least one main vane 334, a portion of the air can flow towards the flow disturbance device 316 (eg, towards the step 318) such that the air flow path through passage 304 is disrupted. air flow through passageway 304 through flow disturbance device 316 allows damping of the resonant frequency of passageway 304 countercurrent flow with respect to the incoming intake air stream 332. The flow disturbance device 316 can increase the expansion of the backflow air into the passageway 304 in order to mix the countercurrent air with the incoming intake air stream 332.

Since air can move past the leading edge 326 of at least one main vane 334 towards the outlet end 331, a portion of the air is allowed to flow through the exhaust duct 314 into the resonance chamber 308. Air entering the resonance chamber 308 through the exhaust duct 314 can be is redirected back to flow passage 304 through recirculation passage 302. By passing a portion of the air from the passageway 304 into the resonance chamber 308, the amount of noise caused by the frequency of passage of the blades of the compressor wheel 306 can be reduced. However, since air can move through the resonance chamber 308, the air pressure inside the resonance chamber can create unwanted noise. To reduce the air pressure within the resonance chamber 308 and disrupt the air flow path through the resonance chamber 308, holes 312 are used to provide an additional air flow path from the resonance chamber 308 to the passageway 304. Thus, the first portion of the air passing through the resonance chamber 308, can flow out of the resonance chamber 308 through the recirculation channel 302 and back into the passage channel 304, while the second part of the air (where the second part is smaller than the first part), can flow out of the resonance chamber 308 through one or more openings 312 and thus reduce the air pressure within the resonance chamber 308. By choosing the position and size of the holes 312, the amplitude of the noise generated by the resonance chamber 308 can be reduced.

FIG. 4 is an enlarged view of the flow disturbance device 316 shown in FIG. 3 with a second example of a step 405 of a flow disturbance device 316 as indicated by dashed lines. As discussed above using FIG. 3, the flow disturbance device 316 comprises a step 318, which may be substantially circular in the case of a substantially cylindrical body 322. The step 318 is formed by a first portion 416 of the inner surface 328 of the passageway 304 (shown in FIG. 3), a first step surface 414, and the second portion 418 of the inner surface 328. Both the first portion 416 and the second portion 418 of the inner surface 328 may extend in a parallel direction with respect to the central axis 330 of the passageway 304, and the first step surface 414 extends between the first portion 416 and the second portion 418 (and is connected to them) in the perpendicular direction relative to the central axis 330.

In this configuration, the inner corner 310 of the step 318 is defined as the joint between the first portion 416 and the first surface 414 of the step, and the outer corner 320 is defined as the joint between the first surface 414 of the step and the second portion 418. As a result, the inner corner 310 is located along the first diameter 327 (shown in Fig. 3), and the outer corner 320 is located along the second diameter 329 (shown in Fig. 3). An inner corner 310 may define or be contained in an upstream transition 402 of a step 318, and an outer corner 320 may define or be contained in a downstream transition 404 of a step 318. An example of a second step 405 is shown with a dashed line rotated with respect to the step. 318. Aperture 312 is shown to be located upstream of step 318 (and second step 405) along passage 304 with respect to incoming intake air stream 332 to at least one main blade 334 (shown in FIG. 3)

A first axis 408 and a second axis 410 are shown, where the first axis 408 is perpendicular to the step 318 and the second axis 410 is located perpendicular to the surface 406 of the second step (for example, to the surface of the second step 405, indicated by the dashed line). For some exemplary embodiments, an axis perpendicular to the step surface (eg, first axis 408, perpendicular to the first step surface 414) may be parallel to the center axis 330 of the body 322 (eg, the centerline of the body 322) or the general direction of the port 304. In another, exemplary embodiments, for example, with a second step 405, an axis perpendicular to the step surface (for example, a second axis 410 perpendicular to the second step surface 406) may be rotated at an angle 412 relative to the central axis 330 of the housing 322. Accordingly, in some cases (for example , in the example of the second rung 405), the rung can be angled to the incoming intake air stream 332. The angle 412 can have a value, for example, in the range between 0 and 80 degrees. In some cases, the angle 412 may be approximately 45 degrees or it may be negative. In various other examples, the flow disturbance device may include an upstream transition 402 and / or a downstream transition 404, which may be formed in various ways, as shown in FIG. 5-14 and disclosed below.

FIG. 5-9 show examples of alternative embodiments of flow disturbance devices similar to flow disturbance device 316 shown in FIG. 3-4 and disclosed above. For example, the alternative embodiments shown in FIG. 5-9 may be located within the compressor, for example, within the compressor 200 shown in FIG. 2, or within the compressor 300 shown in FIG. 3 instead of flow disturbance device 316.

Each of the embodiments shown in FIG. 5-9 contains openings 312, with openings 312 shown in approximately the same position in each example. In other examples, the holes 312 may be positioned differently and / or a different number of holes 312 may be used. For example, in some embodiments, the holes 312 may be located more or less from a corresponding step (eg, from step 318) of the perturbation device. flow (e.g., flow perturbation device 316) in a direction parallel to central axis 330, each opening 312 in fluid communication with a resonance chamber (e.g., resonance chamber 208 surrounding passageway 204, as shown in FIG. 2, or resonance chamber 308 surrounding the passageway 304, as shown in Fig. 3). In other embodiments, a different number of holes 312 may be used, such as two, four, five, etc. In other embodiments, the flow disturbance device may have no holes 312. While FIG. 4-8, figs. 10-14 and FIG. 17 does not show a resonance chamber, a corresponding resonance chamber for each embodiment may be located within each structure, similar to the arrangement of the resonance chamber 208 around the passageway 204 (shown in FIG. 2) or the arrangement of the resonance chamber 308 around the passageway 304 (shown in FIG. 3), etc.

FIG. 5 is an enlarged view (eg, similar to that shown in FIG. 4) of another example of a flow perturbation device, wherein the flow perturbation device 500 is located within a compressor, for example, within the compressor 200 shown in FIG. 2, or within the compressor 300 shown in FIG. 3. The flow disturbance device 500 shown in FIG. 5 includes a step 506 perpendicular to the incoming intake air stream 332, similar to step 318 shown in FIG. 3-4 and disclosed above. However, although the flow disturbance device 500 shown in FIG. 5 is similar to the flow disturbance device 316 shown in FIG. 3-4, the upstream transition 502 and the downstream transition 504 in the flow disturbance device 500 have smoothed (e.g., rounded) corners, in contrast to the outer corner 320 and the inner corner 310, which are shown in FIG. 3-4 and disclosed above.

FIG. 6 shows another example of a flow disturbance device 600 similar to the flow disturbance device 316 shown in FIG. 3-4, and the flow disturbance device 500 shown in FIG. 5. Unlike flow disturbance device 316 and flow disturbance device 500, flow disturbance device 600 includes a step 604 located at an angle 608 with respect to the incoming intake air stream 332. For example, the angle 608 can range between zero and ninety degrees, such so that the step 604 is not perpendicular to the incoming intake air stream 332 and the step 604 is not further parallel to the incoming intake air stream 332. In the example shown in FIG. 6, a step 604 is located in the flow disturbance device 600 at an angle between an upstream transition 602 and a downstream transition 606. In this example, the upstream and downstream transitions comprise curved surfaces to which a step 604 is attached. The step 604, an upstream transition 602, and a downstream transition 606 may together form continuous curved surface. Thus, the step 604 can be angled with respect to the direction of movement of the incoming intake air stream 332.

In some embodiments of the flow disturbance device, such as the embodiments shown in FIGS. 7-8, the upstream transition and the downstream transition in the flow perturbation device may include reverse directional parts. In other words, portions of the flow perturbation device may begin to travel downstream (eg, relative to the incoming intake air flow) and then travel upstream at least a short distance. Such examples are disclosed below using FIGS. 7-8.

FIG. 7 shows another example of a flow disturbance device located within a compressor, for example, within compressor 200 or compressor 300 shown in FIG. 2 and FIG. 3-4 respectively. The flow disturbance device 700 shown in FIG. 7 includes a projecting member 702 and a recessed member 704. For example, the projecting member 702 extends in the opposite direction to the direction of movement of the incoming intake air stream 332, while the recessed member 704 extends in the same direction as the incoming intake air stream 332 The protruding element 702 contains outer corners 706 and the recessed element contains inner corners 708. In some cases, one or more outer corners 706 and inner corners 708 may form a square section (eg, may be right angles) as shown in FIG. 7. In other examples (eg, as shown in FIG. 8 and disclosed below), one or more of the outer corners 706 and inner corners 708 may be smoothed (eg, rounded).

FIG. 8 shows another example of a flow disturbance device. In this example, flow disturbance device 800 includes a projecting element 802 and a recessed element 804. In additional examples, flow disturbance device 800 may include a plurality of projecting elements 802 and / or recessed elements 804. Similar to the example shown in FIG. 7 and disclosed above, the protruding member 802 extends in a direction opposite to the direction of movement of the incoming intake air stream 332, and the recessed member 804 extends in the same direction as the incoming intake air stream 332. However, in the example of the flow disturbance device 800 shown in FIG. ... 8, the surfaces of the protruding element 802 and the recessed element 804 smoothly mate (eg, form continuously curved surfaces) with adjacent surfaces. For example, unlike the outer corners 706 of the protruding member 702 and the inner corners 708 of the recessed member 704 shown in FIG. 7, the projecting element 802 and the recessed element 804 shown in FIG. 8 include rounded outer corners 806 and rounded inner corners 808. In some examples, the protruding element and the recessed element may be substantially cylindrical elements and can be toroidal.

FIG. 9 is a cross-sectional view of another example of a compressor similar to compressor 200 shown in FIG. 2 and compressor 300 shown in FIG. 3-4. Compressor 900 includes a compressor wheel 921 disposed in a housing 902. A compressor wheel 921 is rotatable within a housing 902 to compress the incoming intake air stream 332. Passage 304 is located within the housing 902, is configured to pass intake air, and comprises substantially continuous inner surface 328. Compressor 900 may also have a flow disturbance device 912 located at the leading edge 920 of the main blades 928 and configured to disrupt the inner surface 328.

The compressor wheel 921 may also have dividing vanes 922 and / or other features. Each dividing vane 922 may have a leading edge 926 that may be located downstream of the leading edge 920 of the main vanes 928. In various embodiments (eg, in the example shown in FIG. 9), the flow disturbance device 912 may include a step 909, located perpendicular to the central axis 330 of the compressor 900. The flow disturbance device 912 is fluidly connected to the resonance chamber 906, and the opening 908 of the resonance chamber 906 is formed between the step 909 of the flow disturbance device 912 and the inner surface 328. The size and shape of the resonance chamber 906 can be selected so as to reduce the whistling noise generated by the compressor wheel 921, and this resonance chamber may be additionally fluidly coupled to passageway 304 through openings 312. For example, similar to the embodiments shown in FIGS. 2-4, three openings 312 are located along the inner surface 328 and about a central axis 330 (eg, along the inner perimeter of the port 304). Alternative embodiments may include a different number and / or arrangement of openings 312. Openings 312 can further reduce the amount of noise generated by compressor 900 by further disturbing the air flow through passage 304 and resonance chamber 906.

The wording "at the leading edge of the main blades" can refer to a preselected maximum distance at which the flow disturbance device can be located relative to the leading edge of the main blade or main blades. The preselected maximum distance may be measured in absolute units or may be measured relative to a reference distance between other turbocharger points for the embodiment disclosed herein. For example, the reference distance can be the longitudinal distance from the leading edge to the trailing edge of the main blade.

In some examples, the step 909 of the flow disturbance device 912 may be located substantially in line with the leading edge 920 of at least one main vane 928 with respect to the direction of flow. In other words, in some examples, air may flow out of at least one main blade and enter the opening 908 formed by the flow disturbance device 912. In some examples, most of the flow disturbance devices 912 may be located upstream of the leading edge 920 of the main blades 928. The step 909 of the flow disturbance device 912 may be located some distance from the leading edge 920 of the main blades 928 in a parallel direction with respect to the central axis 330 and on some distance from the main blades 928. In some cases, at least a portion of the flow disturbance device 912 may be located upstream of the leading edge of the main blades 928. In some examples, the step 909 of the flow disturbance device 912 is substantially in line with the leading edge 920 the main blades 928 of the compressor, radially relative to the central axis 330.

The opening 908 formed by the flow disturbance device 912 on the inner surface 328 of the passageway is an annular opening along the inner perimeter of the passageway 304, the opening 908 being fluidly connected to the resonance chamber 906. In this example, the resonance chamber 906 is open into the passageway 304 only through the opening 908 and openings 312. The phrase "the resonance chamber is open into the passage channel only through the opening and openings" can mean that the resonance chamber has boundaries (for example, closed) everywhere, except for the locations of the opening 908 and openings 312, where it is open into the through channel.

In some examples, the opening 908 and the resonance chamber 906 may be formed as a single piece, and may be formed (for example) as a molded part. In other examples, the opening 908 and the chamber may be formed by two or more body parts 902. In other examples, the opening 908 may be cut into the interior of the port 304 and formed, for example, as a tube or conduit or the like, and the resonance chamber 906 may represent an additional volume (for example, an additional closed part) connected to the outer part of the passageway 304, providing a fluid connection between the passageway 304 and the resonance chamber 906 through the opening 908 and openings 312.

FIG. 10-14 illustrate various examples of embodiments of flow disturbance devices that may be located within a compressor, for example, within compressor 200, compressor 300, or compressor 900 disclosed above. Each of the embodiments shown in FIG. 10-14 further comprises openings 312 as disclosed above and shown using FIGS. 2-9. The openings 312 can provide an additional flow path for air moving through the passageway (eg, through passageway 304 shown in FIGS. 3-4).

The flow disturbance device 1100 shown in FIG. 10 includes a leading edge surface 1104 that is radially tapered in the opposite direction from the compressor centerline 330. The flow disturbance device 1100 may also include a trailing edge step end 1102 that can greatly reduce the cross-section of the passageway. The leading edge surface 1104 may be adjacent to the step end 1102 of the flow disturbance device 1100. In some cases, the leading edge surface 1104 may form an acute angle upstream of the step end 1102, or may transition into this portion.

The flow disturbance device 1200 shown in FIG. 11 includes a leading edge surface 1204 tapered radially inward toward the compressor centerline 330. The flow disturbance device 1200 may also include a trailing edge step end 1202 that can greatly reduce the cross-section of the passageway. The leading edge surface 1204 may be adjacent to the step end 1202 of the flow disturbance device 1200. In some cases, the leading edge surface 1204 may form an obtuse angle upstream of the step end 1202, or may transition into that portion.

The flow disturbance device 1300 shown in FIG. 12 includes a leading edge surface 1304 extending radially inwardly toward the compressor centerline 330. The flow disturbance device 1300 may also include a trailing edge step end 1302 that can greatly reduce the cross-section of the passageway. The leading edge surface 1304 may be located separate from the step end 1302 of the flow disturbance device 1300. In some cases, the leading edge surface 1304 may or may form a right angle upstream of the step end 1302.

The flow disturbance device 1400 shown in FIG. 13 includes a leading edge surface 1404 that is separate from the step end 1402. The leading edge surface 1404 may form the upstream side of the annular channel 1406, and the step end 1402 may form the downstream edge of the annular channel 1406.

The flow disturbance device 1500 shown in FIG. 14 includes a leading edge surface 1508 that is separate from the step end 1502. The leading edge surface 1508 may form the upstream side of the annular channel 1510, and the step end 1502 may form the downstream edge of the annular channel 1510. In some cases, the leading edge surface 1508 may form a negative angle upstream of the step edge 1502, or may go to this part.

FIG. 15 is a cross-sectional view of another example of a compressor similar to the compressors shown in FIG. 2-3 and FIG. 9. Compressor 1600 shown in FIG. 15 includes a body 1618, an inlet end 1602, and a port 1606. For example, body 1618, an inlet end 1602, and a port 1606 may be the same as body 203, an inlet end 201, and a port 204 shown in FIG. 2 and disclosed above. Compressor 1600 further comprises a compressor wheel 1616 coupled to a shaft 1610 and rotatable within a housing 1618, the compressor wheel 1616 comprising at least one main blade 1608 with a leading edge 1614.

The passageway 1606 is in fluid communication with the resonance chamber 1612 through a branch passage 314, openings 312, and a recirculation passage 302, which are similar to the examples shown in FIGS. 2-3 and disclosed above. As discussed above with respect to the embodiment shown in FIG. 3, branch duct 314 is located downstream of leading edge 1614 of at least one main vane 1608 relative to incoming intake air stream 332, and recirculation duct 302 is located upstream of leading edge 1614, with openings 312 located between branch duct 314 and duct 302 recirculation (eg, downstream of the recirculation passage 302 and upstream of the branch passage 314). As the compressor wheel 1616 rotates, air may be directed by at least one main vane 1608 into the resonance chamber 1612 through the exhaust duct 314. The first portion of the air may pass through the resonance chamber 1612 and back to the passage duct 1606 through the recirculation duct 302, while the second portion of the air can pass through the resonance chamber 1612 and back to the passageway 1606 through the openings 312, the first portion being larger than the second portion.

The passageway 1606 includes a flow disturbance device 1604 located downstream of the openings 312 and downstream of the leading edge 1614 of the main blade 1608. In other words, the flow disturbance device 1604 is located downstream (relative to the incoming intake air stream 332) of the axis 1626 and axis 1626 is located along front edge 1614 and extends radially about centerline 330. In alternative embodiments, flow disturbance device 1604 may be located at least partially in line with axis 1626 such that axis 1626 intersects flow disturbance device 1604. In other embodiments, the flow disturbance device 1604 may be located upstream of the axis 1626 (eg, upstream of the leading edge 1614). However, in each example of the above disclosed embodiments, the branch duct 314 is located downstream of the holes 312, with the holes 312 located downstream of the recirculation duct 302, and the flow disturbance device is located between the branch duct 314 and the holes 312. Thus, the air flow, flowing out of the resonance chamber 1612 through openings 312 can be further disturbed by a flow disturbance device 1604 located downstream of openings 312, thereby reducing the amount of noise generated by the air passing through the compressor.

The flow disturbance device includes a first surface 1620, a second surface 1622, and a third surface 1624, with the first surface 1620 and third surface 1624 located approximately parallel to the central axis 330. In the example shown in FIG. 15, passageway 1606 has a cylindrical shape and third surface 1624 is offset from first surface 1620 towards central axis 330. As a result, the diameter of passageway 1606 defined by third surface 1624 is less than diameter of passageway 1606 defined by first surface 1620. Second surface 1622 is angled with respect to first surface 1620 and third surface 1624 and connects first surface 1620 and third surface 1624. For example, second surface 1622 may extend between first surface 1620 and third surface 1624 without curvature (e.g., may extend directly from edge of first surface 1620 to the edge of the third surface 1624 without bends). In another example, second surface 1622 may be smoothly curved and extend continuously between first surface 1620 and third surface 1624 such that first surface 1620, second surface 1622, and third surface 1624 together form a smooth surface without sharp and / or sharp edges or corners. and the diameter of the passageway 1606 at the location of the first surface 1620 is greater than the diameter of the passageway 1606 at the location of the third surface 1624.

FIG. 16 shows another example of a compressor 1700 similar to compressor 1600 shown in FIG. 15. Similar components contained in both compressor 1700 and compressor 1600 are labeled the same and may not be referred to again during the disclosure of compressor 1700 below.

Compressor 1700 includes a housing 1718, an inlet 1702, and a passageway 1706. The passageway 1706 includes a flow disturbance device 1704. In the example shown in FIG. 16, the flow disturbance device 1704 is formed by a first surface 1709, a second surface 1710, a third surface 1711, and a fourth surface 1712, with the first surface 1709 and the fourth surface 1712 located approximately parallel to the central axis 330, and the second surface 1710 and third surface 1711 at an angle with respect to the first surface 1709 and the fourth surface 1712. The second surface 1710 is attached to the third surface 1711 at a location located at some greater distance from the central axis 330, compared to the same distance for the first surface 1709 and for the fourth surface 1712. The second surface 1710 is further attached to the first surface 1709, and the third surface 1711 is additionally connected to the fourth surface 1712. In this configuration, the diameter of the passageway 1706 at the point where the second surface 1710 is connected to the third surface 1711 is greater than the diameter of the passageway 1706 in the location of the first surface 1709 or the location of the fourth surface 1712.

In one example, the second surface 1710 can extend in the direction and join the third surface 1711 without curvature, and the third surface 1711 can extend in the direction and join the fourth surface 1712 without curvature. In other words, well-defined edges may be formed at the mating points of the first surface 1709 and the second surface 1710, the second surface 1710 and the third surface 1711, and the third surface 1711 and the fourth surface 1712. In another example, the mating points of the first surface 1709 and the second surfaces 1710, second surface 1710 and third surface 1711, and third surface 1711 and fourth surface 1712 may be bent such that first surface 1709, second surface 1710, third surface 1711, and fourth surface 1712 together form a smooth region of passageway 1706 (for example, an area with no pronounced corners). Within the smooth region, as disclosed above, the diameter of the passageway 1706 between the second surface 1710 and the third surface 1711 is greater than the diameter of the passageway 1706 at the location of the first surface 1709 or at the location of the fourth surface 1712. In other examples, only the second surface 1710 and the third surface 1711 may be curved (for example, may form a smooth junction, as discussed above), or only the first surface 1709 and the second surface 1710 may be curved, etc.

In the embodiment shown in FIG. 16, the flow disturbance device 1704 is located downstream of the openings 312 and downstream of the leading edge 1614 of the main blade 1608. In other words, the flow disturbance device 1704 is located downstream (relative to the incoming intake air stream 332) from the axis 1626 (as disclosed above using Fig. 15). In alternative embodiments, the flow disturbance device 1704 may be located at least partially in line with the axis 1626 such that the axis 1626 intersects the flow disturbance device 1704. In other embodiments, the flow disturbance device 1704 may be located upstream of the axis 1626 (eg, upstream of the leading edge 1614). However, in each example of the above disclosed embodiments, the branch duct 314 is located downstream of the openings 312, with the holes 312 located downstream of the recirculation duct 302, and the flow disturbance device 1704 is located between the branch duct 314 and the holes 312. Thus, the air flow flowing out of resonance chamber 1612 through openings 312 can be further disturbed by a flow disturbance device 1704 located downstream of openings 312, thereby reducing the amount of noise generated by the air passing through the compressor. Although the compressor 1600 shown in FIG. 15 and compressor 1700 shown in FIG. 16 include a flow disturbance device (flow disturbance device 1604 and flow disturbance device 1704, respectively), in further embodiments, a flow disturbance device may be omitted. In other words, in some examples, embodiments of a compressor comprising a plurality of openings (eg, openings 312) as disclosed above using FIGS. 2-16 and below using FIG. 17 may include a flow disturbance device (e.g., embodiments such as those disclosed above using FIGS. 2-16), and in other examples, the compressor may not have a flow disturbance device, and instead may include a smooth and relatively straight (e.g. continuous, relatively uniform diameter) passageway as indicated by dashed line 1750 in FIG. 16. For example, dashed line 1750 may indicate the shape of flow passage 1706 in an alternative embodiment of compressor 1700 that does not include flow disturbance device 1704. Such embodiments, however, include a branch duct, openings, a resonance chamber, and a recirculation duct as disclosed above, but do not include a flow disturbance device.

FIG. 17 shows an example of an inlet 1803 of a compressor, such as the compressors shown in FIG. 2-3, FIG. 9 and FIG. 15-16. The passageway 1801 is formed by an inlet 1803, which passageway is similar to the passageways disclosed above in relation to the compressors disclosed above. Center axis 330 is shown to illustrate the relative positioning of a plurality of holes formed by inlet 1803, these holes being similar to holes 312 shown in FIG. 2-9 and in FIG. 10-16 and disclosed above. For example, inlet 1803 may include three openings, including the first opening 1810 shown in FIG. 17, and the positions of the second hole and the third hole are designated 1812 and 1814, respectively. The first axis 1802 passes through the center of the first hole 1810 and is parallel to the direction in which the first hole 1810 extends relative to the central axis 330. The second axis 1804 passes through the center of the second hole 1812 and is parallel to the direction in which the second hole 1812 extends relative to the central axis 330. The third axis 1806 extends through the center of the third hole 1814 and is parallel to the direction in which the third hole 1814 extends about the center axis 330.

In the example shown in FIG. 17, the first hole 1810, the second hole 1812, and the third hole 1814 are rotated relative to each other and are located about the central axis 330. In other words, the first axis 1802 and the second axis 1804 intersect the central axis 330 (for example, they are located radially relative to the central axis 330), and rotated relative to each other through the first angle 1808. In addition, the first axis 1802 and the third axis 1806 intersect the central axis 330 and are rotated relative to each other by the second angle 1816, and the second axis 1804 and the third axis 1806 are rotated relative to each other by the third angle ( not shown in the diagram). In the example shown in FIG. 17, the first angle, the second angle, and the third angle have the same value (for example, the first hole 1810, the second hole 1812, and the third hole 1814 are rotated relative to each adjacent hole by the same angle and are located at the same distance from each adjacent hole). In alternative embodiments, the implementation of one or more holes may be rotated relative to adjacent holes at different angles, and / or there may be a different number of holes, for example, four, five, etc. For example, in some embodiments, the distance between the first hole and the second hole may be greater than the distance between the second hole and the third hole. Alternative embodiments may include additional hole spacing configurations. In addition, in some examples, the holes may be located closer to or further from the leading edge of at least one main compressor blade (for example, from the leading edge 1614 shown in FIGS. 15-16), with each hole, however, located between a branch duct and a recirculation duct (eg, between branch duct 314 and recirculation duct 302, as shown in FIGS. 15-16). In other examples, each hole may be positioned differently from the other hole toward the front edge or away from the front edge of the at least one main blade (eg, toward the center axis 330).

In some examples, the holes may have a different size (eg, opening diameter) and / or a different shape than the examples shown in FIGS. 2-17. For example, in one embodiment, each hole may have a diameter of four millimeters. In an alternative embodiment, each hole may have a diameter of six millimeters. In another embodiment, one or more holes may be four millimeters in diameter and the remaining holes may be six millimeters in diameter. In other embodiments, additional dimensions (eg, diameters) may be used, and all holes may be the same size, or one or more holes may have a different size than other holes. In other examples, one or more holes may be different in shape, such as elliptical, rectangular, etc., and all holes may be the same shape, or one or more holes may be different from the other holes.

FIG. 18-26 show individual embodiments of compressors comprising a plurality of ports and / or a flow disturbance device. For example, in FIG. 18-20 are partial cross-sectional views of embodiments of compressors having multiple openings but no flow disturbance device, while FIG. 21-26 are partial cross-sectional views of embodiments of compressors comprising both a plurality of openings and a flow disturbance device. It should be noted that the embodiments shown in FIG. 21-26 may include any of the aperture embodiments shown in FIGS. 18-20 and disclosed below.

FIG. 18 shows an example of a compressor comprising a resonance chamber 1850 (similar to resonance chamber 308 shown in FIG. 3, resonance chamber 1612 shown in FIGS. 16-17, etc.), a bypass duct 1856 (similar to a bypass duct 314 shown in Fig. 3 and Fig. 16-17), a recirculation channel 1858 (similar to the recirculation channel 302 shown in Fig. 3 and Fig. 16-17), which are located upstream of the branch channel 1856, and a plurality of openings 1860 (similar to openings 312 shown in FIGS. 3-16) located between the recirculation duct 1858 and the branch duct 1856.

Passage 1853 (similar to passageway 304 shown in FIGS. 3-14, passageway 1606 shown in FIG. 15, and passageway 1706 shown in FIG. 16) includes a first surface 1859 located downstream of the branch passage 1856, the second surface 1862 located between the branch duct 1856 and the holes 1860 in the direction of the central axis 330, and the third surface 1866 located upstream of the recirculation duct 1858. First surface 1859, second surface 1862, and third surface 1866 are annular surfaces defining the shape of passageway 1853, similar to the examples shown in FIGS. 2 and FIG. 15-16. In the example shown in FIG. 18, the first surface 1859, the second surface 1862, and the third surface 1866 are annular surfaces equally spaced about the central axis 330. In other words, in the cross-sectional view of FIG. 18, first surface 1859, second surface 1862, and third surface 1866 are shown parallel to each other and aligned with a common axis 1851, with a common axis 1851 parallel to center axis 330 and spaced away from center axis 330.

In the example shown in FIG. 18, openings 1860 extend from passageway 1853 to resonance chamber 1850 radially about central axis 330. In other words, each opening 1860 extends in a direction parallel to radial axis 1852. Openings 1860 are formed by second surface 1862 about central axis 330 and are equidistant from the branch duct 1856 and the recirculation duct 1858. As discussed above with respect to the openings shown in FIG. 17, the holes 1860 are not annular channels. Instead, each hole 1860 is circular or elliptical when viewed from the central axis 330, and each hole 1860 is not aligned with the other hole 1860.

FIG. 19 shows an alternative embodiment of the holes. In the example shown in FIG. 19, the holes 1902 extend from the passageway 1853 to the resonance chamber 1850 in a direction defined by an angle relative to the central axis 330. In other words, the axis 1904 intersects the central axis 330 at an angle 1900 relative to the central axis 330, and each hole 1902 extends along the axis 1904 between passageway 1853 and resonance chamber 1850. While axis 1904 is shown to be approximately forty-five degrees relative to central axis 330, in alternative embodiments, axis 1904 may be located relative to central axis 330 at a different angle, for example, twenty-five degrees, seventy five degrees, etc. In each of the embodiments, the holes 1902 extend along the axis 1904 such that each hole 1902 is rotated relative to the central axis 330 by the same angle that the axis 1904 is rotated relative to the central axis 330. In addition, although the holes 1902 are rotated relative to the central axis 330 each opening 1902 is equally spaced between the branch duct 1856 and the recirculation duct 1858, as discussed above with respect to the apertures 1860 shown in FIG. 18. In some embodiments, for example, as shown in FIG. 20 and disclosed below, one or more openings spaced at a different distance between the branch duct 1856 and the recirculation duct 1858 may be used.

FIG. 20 shows openings 2002 similar to openings 1860 shown in FIG. 18 and open above, but located closer to the branch duct 1856 than to the recirculation duct 1858. In other words, one or more openings 2002 may be located at a first distance 2003 from the branch duct 1856 and may be located at a second distance 2005 from the recirculation duct 1858, the second distance 2005 being greater than the first distance 2003. In alternative embodiments, the first distance 2003 and the second the distance 2005 may differ from the distances shown in FIG. 20. For example, in one embodiment, the first distance 2003 may be greater than the second distance 2005 such that one or more openings 2002 are located closer to the recirculation channel 1858 than to the branch channel 1856. In addition, although the openings 2002, shown in FIG. 20 are similar to holes 1860 shown in FIG. 18 (eg, holes 2002 extend radially with respect to central axis 330), other embodiments may include holes that extend at an angle relative to central axis 330, such as holes 1902 shown in FIG. 19 and disclosed above. In other words, alternative embodiments may comprise various combinations of hole shapes, positions, sizes, etc., as shown in FIG. 18-20 and disclosed above.

FIG. 21-26 show examples of a second flow disturbance device (which may be referred to herein as an "edge break" or "constriction region" and / or an "expansion region" of the passageway), the second flow disturbance device being isolated and separated from the flow disturbance devices, disclosed above and shown in FIG. 3-16. FIG. 21-26 show an embodiment of openings similar to the embodiment of FIGS. 18. It will be appreciated that the embodiments shown in FIG. 21-26 may include alternative aperture embodiments (eg, having a different shape, size, position, etc.) similar to the embodiments shown in FIGS. 19, figs. 20 or disclosed above.

FIG. 21 shows a first example of an edge break 2101 upstream of branch duct 1856 and opening 1860. Edge break 2101 comprises a first depressed surface 2102 extending at an angle relative to the central axis 330 by a first value, a second depressed surface 2104 extending in the direction rotated about the central axis 330 by a second value, and a parallel surface 2106 extending in a parallel direction with respect to the central axis 330. A second depressed surface 2104 is attached to the first depressed surface 2102, and the first depressed surface 2102 and the second depressed surface 2104 are formed by the second surface 1862. The first depressed surface 2102 is positioned such that the distance from the center axis 330 to points along the first depressed surface 2102 is less than the distance from the center axis 330 to points along the second depressed surface 2104. In other words, the first depressed surface 2 012 and the second depressed surface 2104 form tapers away from the center axis 330 in a direction opposite to the direction of movement of the incoming intake air stream 332, with the second depressed surface 2104 forming a taper spaced from the center axis 330 at a greater distance than the first depressed surface 2102 The parallel surface 2106 is positioned such that the diameter of the passageway 1853 in regions along the parallel surface 2106 is greater than the diameter of the passageway 1853 in the regions along the first depressed surface 2102 and the second depressed surface 2104.

FIG. 22 shows a second example of edge rupture upstream of branch duct 1856 and opening 1860. Edge rupture 2201 shown in FIG. 22 includes a first depressed surface 2102 and a second depressed surface 2104, as discussed above using FIG. 21, but does not include the parallel surface 2106 shown in FIG. 21. Instead, the edge break 2201 comprises a third depressed surface 2204 and a fourth depressed surface 2206, the third depressed surface 2204 extending in a direction at an angle relative to the central axis 330 by a first value, and the fourth depressed surface 2206 extending in a direction rotated relative to the central axis 330 to the second value. The third depressed surface 2204 and the fourth depressed surface 2206 are located together and upstream of the recirculation duct 1858, similar to the parallel surface 2106 shown in FIG. 21 and disclosed above, with the third depressed surface 2204 connected to the fourth depressed surface 2206. In this embodiment, the diameter of the passageway in regions along the third depressed surface 2204 is less than the diameter of the passageway in regions along the fourth depressed surface 2206. In other words, the third depressed surface 2204 and the fourth depressed surface 2206 defines constrictions at various distances from the center axis 330 in a direction opposite to the direction of movement of the incoming intake air stream 332.

FIG. 23 shows an embodiment having an edge break 2301 that does not include the first depressed surface 2102 and the second depressed surface 2104, and further comprises a tapered surface 2300. In other words, the second surface 1862 does not form a taper directed away from the central axis 330 in the regions above downstream of the holes 1860.

The tapered surface 2300, located upstream of the recirculation channel 1858, forms a constriction directed away from the central axis 330, in a direction opposite to the direction of movement of the incoming intake air stream 332. Unlike the example of the third depressed surface 2204 and the fourth depressed surface 2206, which are shown in FIG. 22 and disclosed above, the tapered surface 2300 forms a continuous tapered portion of the port 1853. In other words, the tapered surface 2300 forms a constriction extending from the recirculation port 1858 in a direction opposite to the direction of movement of the incoming intake air stream 332 (for example, towards the compressor inlet ), and having a smooth surface without bending or changing the angle of inclination about the central axis 330.

FIG. 24 shows another embodiment comprising an edge break 2401. The edge break 2401 comprises a continuous curved surface 2400, in contrast to the tapered surface 2300 shown in FIG. 23 and disclosed above. The continuous curved surface 2400 is curved away from the central axis 330 and from the recirculation channel 1858 in the opposite direction to the direction of the incoming intake air stream 332. In other words, the diameters of the passage channel 1853 in regions along the continuous curved surface 2400 increase with increasing distance from the recirculation channel 1858 (for example, the diameter at the first location upstream of the recirculation duct is less than the diameter in the second location upstream of the recirculation duct if the second location is further upstream than the first location relative to the direction of the incoming intake air flow).

FIG. 25 illustrates an embodiment having an edge break 2501 located downstream of branch duct 1856. Edge break 2501 comprises a rectilinear surface 2500 and a corner surface 2502, with the rectilinear surface 2500 extending in a parallel direction with respect to the central axis 330 (e.g., parallel to the second surface 1862 and third surface 1866), and the corner surface 2502 extends in a direction at an angle relative to the central axis 330. The straight surface 2500 is connected to the corner surface 2502. The diameter of the passageway 1853 at the place where the corner surface 2502 connects to the rectilinear surface 2500 is less than the diameter of the passageway channel 1853 at the location where the corner surface 2502 abuts the branch channel 1856. In other words, the corner surface 2502 extends away from the center axis and rectilinear surface 2500, in a direction opposite to the direction of the incoming intake air stream 332.

FIG. 26 illustrates an embodiment having an edge break 2601 located upstream of branch duct 1856 and downstream of openings 1860. Edge break 2601 comprises a corner surface 2600 formed by a second surface 1862. Corner surface 2600 extends away from central axis 330 and to branch channel 1856. In other words, the diameter of the passageway 1853 at the point where the corner surface 2600 meets the second surface 1862 is less than the diameter of the passageway 1853 at the point where the corner surface 2600 abuts the branch channel 1856.

Although the examples shown in FIG. 2-26 are depicted as separate embodiments, alternative embodiments may comprise combinations of the above disclosed flow disturbance devices and orifices. For example, in one embodiment, the compressor may include a plurality of holes located between the branch duct and the recirculation duct, where a first flow disturbance device is located downstream of the holes and a second flow disturbance device (e.g., an edge break) is located upstream of the holes, and downstream of the compressor inlet, the holes extending radially with respect to the central axis of the compressor. In another example, the compressor may include a first flow disturbance device, a second flow disturbance device and openings as disclosed above, the openings extending in an angular direction relative to the central axis of the compressor. In another example, the compressor may include multiple openings and only one flow disturbance device located either upstream or downstream of the openings. In addition, other embodiments may comprise various combinations of flow disturbance devices and / or orifices.

FIG. 2-26 show examples of embodiments with the relative position of various components. If these components are shown to be in direct contact with each other or directly connected, then such elements may be referred to as being in direct contact or directly connected, at least by way of example. Likewise, items shown adjacent or adjacent may be adjacent or adjacent, at least by way of example. For example, components that are in surface contact with each other may be referred to as having surface contact. In another example, elements that are spaced apart from each other and without any other components may be referred to as such, by way of example only. In another example, elements shown above / below each other, on opposite sides with respect to each other, or to the right / left of each other, may be referred to as such, relative to each other. In addition, as shown in the illustrations, the topmost element or the topmost point of the element may be referred to as the “top” of the specified component, and the lowest element or the lowest point of the element may be referred to as the “bottom” of the specified component, at least by way of example. Used in this document, the terms top / bottom, top / bottom, above / below can be indicated relative to the vertical axis in the drawings and be used to indicate the position of elements relative to each other in the drawings. For example, items shown above other items are vertically higher than other items. In another example, the shapes of the elements shown in the drawings may be indicated as such (eg, elements that are round, straight, flat, curved, rounded, beveled, angular, etc.). In addition, elements shown in intersection with each other may be indicated as intersecting elements or intersecting with each other, in at least one example. In addition, an item shown within another item or shown outside of another item may be referred to as such, by way of example only.

By surrounding the bore of the compressor with the resonance chamber and providing a fluid connection between the bore and the resonance chamber through the bleed and recirculation duct, air can flow into the resonance chamber through the bleed while the compressor wheel rotates. The first amount of air passing through the resonance chamber can leave the resonance chamber through the recirculation channel and enter the passage channel again. Thus, by passing air through the resonance chamber and the passageway, the amount of noise generated by the air flow can be reduced. In addition, by positioning the holes between the branch duct and the recirculation duct, as disclosed above, a second amount of air can escape from the resonance chamber into the passage duct, the second amount being less than the first amount. In this way, it is possible to reduce the pressure inside the resonance chamber and thus further reduce the amount of sound generated by the air flow. In some embodiments, the flow disturbance device may be located within the bore if the flow disturbance device is configured to disrupt (eg, change) the flow of air moving through the bore. By disrupting the flow of air moving through the passageway and through the flow disturbance device, it is possible to further reduce the number of sounds generated by the air flow. By working together the resonance chamber, the holes and the flow perturbation device, the amount of noise generated by the air flow passing through the compressor can be reduced to a greater extent than the amount of noise that is reduced by using the resonance chamber alone.

In one embodiment, the compressor comprises: a housing; a passageway formed by the inner surface of the housing; a compressor wheel located in said housing downstream of the flow passage and having at least one main blade; a resonance chamber formed within the housing surrounding the passageway and in fluid communication with the passageway through the recirculation passage and the bypass passage; and an opening formed between the resonance chamber and the passageway and connected to the passageway between the recirculation passage and the bypass passage. In a first example of a compressor, the compressor comprises a flow perturbation device formed by the inner surface of the bore and located between the branch duct and an opening within the bore and extending towards the central axis of the compressor. The second compressor example optionally comprises the first example, and is further characterized in that the flow disturbance device is an annular flow disturbance device extending along the inner perimeter of the bore and around the central axis of the compressor. The third example of a compressor optionally contains one or more examples, from the first to the second, and is characterized in that the flow disturbance device comprises a front edge surface that is tapered radially outward in the direction from the central axis, and a rear edge surface located near the front edge of at least one the main blade and located perpendicular to the central axis. The fourth example of the compressor optionally contains one or more examples, from the first to the third, and is characterized in that the leading edge of at least one main blade is located upstream of the flow disturbance device. The fifth example of a compressor optionally contains one or more examples, from the first to the fourth, and is characterized in that the flow disturbance device comprises a first surface defining the first diameter of the passage channel, a second surface defining the second diameter of the passage channel, and a third surface located at an angle with respect to the first surface and the second surface and connecting the first surface to the second surface. The sixth example of a compressor optionally contains one or more examples, from the first to the fifth, and is characterized in that the flow disturbance device comprises a first surface and a second surface extending in a parallel direction with respect to the central axis, a third surface and a fourth surface located at an angle relative to the first surface and second surfaces and located between the first surface and the second surface, and wherein the diameter of the passage along the first surface and the second surface is less than the diameter of the passage along the third surface and the fourth surface. The seventh example of the compressor optionally contains one or more examples, from the first to the sixth, and is characterized in that the opening is located between the recirculation channel and the bypass channel along the passage channel in the direction of the central axis of the compressor, and wherein the opening is one of a plurality of holes located between the channel recirculation and branch duct. The eighth example of the compressor optionally contains one or more examples, from the first to the seventh, and is characterized in that each hole of the plurality of holes is located radially about a central axis. The ninth example of the compressor optionally contains one or more examples, from the first to the eighth, and is characterized in that each hole of the plurality of holes is formed as a cylindrical opening extending between the resonance chamber and the passage channel. The tenth example of the compressor optionally contains one or more examples, from the first to the ninth, and further comprises a flow disturbance device formed by the passage channel and located upstream of the plurality of holes with respect to the direction of movement of the intake air flow through the passage channel, and the diameter of the passage channel along the device flow disturbance is less than the diameter in the area of the inlet opening of the passage channel.

In another embodiment, the compressor comprises: a housing having a central axis; a compressor wheel located in said housing having a main blade rotatable inside the housing around a central axis; a passageway located within the housing and at least partially upstream of the compressor wheel; a chamber located inside the housing and surrounding the outer perimeter of the passageway, said chamber in fluid communication with the passageway through a branch passage and a recirculation passage; and an annular flow disturbance device located downstream of the opening and upstream of the branch channel, the annular flow disturbance device comprising a front edge surface, a rear edge surface and an angular surface connecting the front edge surface with the rear edge surface, and the trailing edge surface is located near the leading edge of the main scapula. In a first example of a compressor, the compressor comprises an opening fluidly connecting said chamber to a passageway, the opening being located between the branch passage and the recirculation passage along the passageway in the direction of the central axis. The second compressor example optionally comprises the first example and is characterized in that the hole is one of a plurality of holes located between the branch duct and the recirculation duct, the plurality of holes are located radially with respect to the central axis of the compressor, and each hole of the plurality of holes is formed as a cylindrical hole between indicated by the camera and the through passage. The third example of the compressor optionally contains one or more examples, from the first to the second, and is characterized in that the first axis, located radially relative to the central axis and passing through the center of the first hole of the plurality of holes, is inclined at a first angle with respect to the second axis located radially relative to the central axis and passing through the center of the second hole of the plurality of holes, and the first hole is located adjacent to the second hole, and the angle between each pair of adjacent holes of the plurality of holes in the direction around the central axis is equal to the first angle. The fourth example of the compressor optionally contains one or more examples, from the first to the third, and is characterized in that each hole of the plurality of holes is isolated and separated from each other hole, and wherein none of the plurality of holes is formed by a branch or recirculation channel. The fifth example of the compressor optionally contains one or more examples, from the first to the fourth, and differs in that the discharge channel is located downstream of the leading edge of the main blade, and the recirculation channel is located upstream of the leading edge of the main blade, relative to the direction of the central axis.

In another embodiment, the compressor comprises: an inlet passage located within the compressor housing; a compressor wheel located in said housing, downstream of the inlet passageway, and having a main blade rotatable about the central axis of the inlet passageway; a first annular passage located upstream of the leading edge of the main blade and connecting the inlet passageway and an annular chamber surrounding the inlet passageway; a second annular passage located downstream of the leading edge of the main blade and connecting the inlet passageway and the annular chamber; a plurality of holes located between the first annular passage and the second annular passage in the direction of the central axis and connecting the inlet passageway with the annular chamber; and a flow disturbance device disposed along an inner surface of the inlet passageway between the second annular channel and the plurality of holes, the flow disturbance device comprising a leading edge surface, a rear edge surface, and at least one angular surface joined between the front edge surface and a rear edge surface. In a first compressor example, the leading edge surface and the trailing edge surface are located approximately parallel to the central axis, the leading edge surface being located at a greater distance from the central axis than the trailing edge surface, in a radial direction relative to the central axis, and wherein the at least one corner surface comprises exactly one corner surface connecting the leading edge surface and the trailing edge surface. The second compressor example optionally comprises the first example and is characterized in that the front edge surface and the rear edge surface are located approximately parallel to the central axis and wherein at least one corner surface comprises a first corner surface and a second corner surface, the first corner surface being connected to the second corner surface at a place located at a distance from the central axis, the surface of the front edge and the surface of the rear edge, in a radial direction relative to the central axis.

It should be noted that the examples of control programs and evaluation programs included in this application can be used with a variety of configurations of engine and / or vehicle systems. The control methods and algorithms disclosed in this application can be stored as executable instructions in non-volatile memory and executed by a control system consisting of a controller in combination with various sensors, drives, and other engine means. Specific algorithms disclosed herein may represent one or more processing strategies such as event-driven, interrupt-driven, multitasking, multithreading, and the like. In addition, the illustrated various acts, operations and / or functions may be performed in the specified sequence, in parallel, or in some cases may be omitted. Likewise, this order of processing is not required to achieve the features and benefits of the embodiments disclosed herein, but is for convenience of illustration and description. One or more of the illustrated acts, operations and / or functions may be repeated depending on the particular strategy employed. In addition, the disclosed actions, operations, and / or functions may graphically represent code to be programmed into the non-volatile memory of a computer-readable storage medium in an engine control system, where the disclosed actions are performed by executing instructions in a system containing various engine hardware components. together with an electronic controller.

It should be understood that the configurations and algorithms disclosed in this application are illustrative, and that these specific embodiments of the invention should not be construed as limiting, as numerous modifications are possible. For example, the above technology can be applied to engines with cylinder configurations V-6, I-4, I-6, V-12, with 4 boxer cylinders and other types of engines. The subject matter of the present invention includes all new and non-obvious combinations and sub-combinations of various systems and configurations, as well as other features, functions and / or properties disclosed in this application.

In the following claims, in particular, certain combinations and sub-combinations are indicated, which are considered novel and non-obvious. In such claims, reference may be made to “some” element or “first” element or the equivalent of such an element. It should be understood that such claims may include one or more of the recited elements without requiring or excluding two or more of such elements. Other combinations and sub-combinations of the disclosed features, functions, elements and / or properties may be included in the claims by modifying existing claims or by introducing new claims in the present or related application. Such claims, whether broader, narrower, equivalent, or different in terms of the scope of the original claims, are also deemed to be included in the subject matter of the present invention.

Claims (36)

1. Compressor containing body; a passageway formed by the inner surface of the housing; a compressor wheel located in said housing downstream of the flow passage and having at least one main blade; a resonance chamber formed within the housing surrounding the passageway and in fluid communication with the passageway through the recirculation passage and the bypass passage; and an opening formed between the resonance chamber and the passageway and connected to the passageway between the recirculation passage and the bypass passage. 2. A compressor according to claim 1, further comprising a flow perturbation device formed by the inner surface of the bore and located between the branch duct and an opening inside the bore and extending in the direction of the central axis of the compressor. 3. A compressor according to claim. 2, characterized in that the flow disturbance device is an annular flow disturbance device extending along the inner perimeter of the flow channel and around the central axis of the compressor. 4. Compressor according to claim. 3, characterized in that the flow disturbance device comprises a front edge surface beveled radially outward from the central axis, and a rear edge surface located near the front edge of at least one main blade and located perpendicular to the central axis ... 5. A compressor according to claim. 4, characterized in that the leading edge of at least one main blade is located upstream of the flow disturbance device. 6. A compressor according to claim 3, characterized in that the flow disturbance device comprises a first surface defining the first diameter of the passage channel, a second surface defining the second diameter of the passage channel, and a third surface located at an angle relative to the first surface and the second surface and connecting the first surface with a second surface. 7. A compressor according to claim 3, characterized in that the flow disturbance device comprises a first surface and a second surface extending in a parallel direction relative to the central axis, a third surface and a fourth surface located at an angle relative to the first surface and the second surface and located between the first surface and the second surface, and wherein the diameter of the passageway along the first surface and the second surface is less than the diameter of the passageway along the third surface and the fourth surface. 8. Compressor according to claim. 1, characterized in that the opening is located between the recirculation channel and the branch channel along the passage channel in the direction of the central axis of the compressor, and wherein the opening is one of a plurality of holes located between the recirculation channel and the branch channel. 9. The compressor of claim. 8, characterized in that each hole of the plurality of holes is located radially about a central axis. 10. The compressor of claim 8, wherein each of the plurality of holes is formed as a cylindrical opening extending between the resonance chamber and the passageway. 11. A compressor according to claim 8, further comprising a flow disturbance device formed by a bore and located upstream of the plurality of holes with respect to the direction of flow of the intake air through the bore, and wherein the diameter of the flow channel along the flow disturbance device is less than the diameter in the area of the inlet passage channel. 12. Compressor containing a housing having a central axis; a compressor wheel located in said housing having a main blade rotatable inside the housing around a central axis; a passageway located within the housing and at least partially upstream of the compressor wheel; a chamber located inside the housing and surrounding the outer perimeter of the passageway, said chamber in fluid communication with the passageway through a branch passage and a recirculation passage; and an annular flow disturbance device on the passage channel located downstream of the opening and upstream of the outlet channel, and the annular flow disturbance device comprises a front edge surface, a rear edge surface and an angular surface connecting the front edge surface with the rear edge surface, and the surface the posterior edge is located near the anterior edge of the main scapula. 13. The compressor of claim 12, further comprising an opening fluidly connecting said chamber to the bore, the bore being located between the branch passage and the recirculation passage along the bore in the direction of the central axis. 14. Compressor according to claim 13, characterized in that the hole is one of a plurality of holes located between the branch channel and the recirculation channel, the plurality of holes are located radially with respect to the central axis of the compressor, and each hole of the plurality of holes is formed as a cylindrical opening between the specified camera and the through passage. 15. A compressor according to claim 14, characterized in that the first axis located radially relative to the central axis and passing through the center of the first hole of the plurality of holes is inclined at a first angle relative to the second axis located radially relative to the central axis and passing through the center of the second hole from a plurality of holes, the first hole being adjacent to the second hole, and wherein the angle between each pair of adjacent holes of the plurality of holes in the direction around the central axis is equal to the first angle. 16. The compressor of claim. 14, characterized in that each hole of the plurality of holes is isolated and separated from each other hole, and wherein none of the plurality of holes is formed by a branch duct or a recirculation duct. 17. Compressor according to claim 16, characterized in that the discharge channel is located downstream of the leading edge of the main blade and the recirculation channel is located upstream of the leading edge of the main blade relative to the direction of the central axis. 18. Compressor containing an inlet passage located inside the compressor housing; a compressor wheel located in said housing downstream of the inlet passage and having a main blade rotatable about the central axis of the inlet passage; a first annular passage located upstream of the leading edge of the main blade and connecting the inlet passageway and an annular chamber surrounding the inlet passageway; a second annular passage located downstream of the leading edge of the main blade and connecting the inlet passageway and the annular chamber; a plurality of holes located between the first annular passage and the second annular passage in the direction of the central axis and connecting the inlet passageway with the annular chamber; and a flow disturbance device located along the inner surface of the inlet passageway between the second annular channel and the plurality of holes, the flow disturbance device comprising a front edge surface, a rear edge surface, and at least one angular surface joined between the front edge surface and a rear edge surface. 19. A compressor according to claim 18, wherein the front edge surface and the rear edge surface are approximately parallel to the central axis, the front edge surface located at a greater distance from the central axis than the rear edge surface, radially relative to the central axis, and wherein at least one corner surface comprises exactly one corner surface connecting the front edge surface and the rear edge surface. 20. A compressor according to claim 18, wherein the front edge surface and the rear edge surface are located approximately parallel to the central axis, and wherein at least one corner surface comprises a first corner surface and a second corner surface, the first corner surface being connected to the second corner surface surface at a location located at a distance from the central axis of the front edge surface and the rear edge surface, in a radial direction relative to the central axis.

Images