JP2007146695A - Supercharger - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a supercharger effectively preventing erosion caused by combustion residue included in exhaust gas and suppressing an increase of a production cost. <P>SOLUTION: A turbine impeller 15 is rotatably provided in a turbine housing 17, and nozzle blades 28 are fixedly provided at predetermined angle intervals around the turbine impeller. The nozzle blades form a nozzle blade ring 29 which directs exhaust gas flowing into the turbine housing, toward the center. The turbine housing has inside a tongue part for separating the flowing-in exhaust gas and exhaust gas swirling in the turbine housing after flowing therein. The tongue part is formed to locate one of the nozzle blades on the extension of the tongue part. <P>COPYRIGHT: (C)2007,JPO&INPIT

Description

  The present invention relates to a supercharger which is provided in an internal combustion engine for ships, automobiles and the like and is driven by using exhaust energy of the internal combustion engine to increase the supply pressure of the internal combustion engine and increase the output of the internal combustion engine.

  A supercharger is provided to increase the thermal efficiency and output of the internal combustion engine. The supercharger has a structure in which an exhaust turbine and an air supply compressor are coaxially connected, the exhaust turbine is driven by the energy of the exhaust gas of the internal combustion engine, and the air supply compressor is driven by the exhaust turbine, The air compressed by the air supply compressor is supplied to the internal combustion engine.

  An internal combustion engine, particularly a marine internal combustion engine, uses low-quality heavy oil as fuel, and the exhaust gas of the marine internal combustion engine contains combustion residues such as carbon. For this reason, the corrosion by the combustion residue in exhaust gas arises. Conventionally, in order to prevent erosion due to combustion residue, hard metal is sprayed on a portion where erosion is likely to occur, and coating with hard metal is performed.

  A conventional exhaust turbine will be described with reference to FIG.

  FIG. 3 is a cross-sectional view of the exhaust turbine 1 taken along a plane orthogonal to the rotational axis. In FIG. 3, 2 is a turbine housing, 3 is a turbine impeller, and the turbine impeller 3 is centered on the rotational axis 4. It is free to rotate.

  The turbine housing 2 has a circular outer shape, is provided with an exhaust gas inlet 5 that opens in a substantially tangential direction, and is an exhaust gas outlet (not shown) that is concentric with the rotary shaft 4 and perpendicular to the paper surface. Z).

  When high-pressure and high-temperature exhaust gas flows in from the exhaust gas inlet 5, the turbine impeller 3 rotates while rotating in the turbine housing 2 to rotate the turbine impeller 3, and is discharged from the exhaust gas outlet. At this time, since the exhaust gas flows along the inner surface of the turbine housing 2, groove-like erosion occurs on the inner surface of the turbine housing 2 due to combustion residues contained in the exhaust gas.

  Conventionally, in order to prevent erosion, a countermeasure has been taken in which hard metal is sprayed on the inner surface of the turbine housing 2 and coating is performed with the hard metal.

  However, it is difficult to uniformly coat a hard metal over a wide range of the inner surface of the turbine housing 2, which increases the manufacturing cost of the turbine housing 2, and consequently increases the manufacturing cost of the turbocharger. There was a problem.

  In addition, there exists a thing shown by patent document 1 as what sprayed the abrasion-resistant material on the inner wall of the turbine housing.

JP 2002-317641 A

  In view of such circumstances, the present invention provides a supercharger that effectively prevents erosion due to combustion residues contained in exhaust gas and suppresses an increase in manufacturing cost.

  In the present invention, a turbine impeller is rotatably provided in a turbine housing, nozzle blades are fixed around the turbine impeller at predetermined angular intervals, a nozzle blade ring is formed by the nozzle blade, The nozzle blade ring is directed toward the exhaust gas flowing into the turbine housing, and the turbine housing has a tongue portion for separating the exhaust gas flowing into the turbine housing and the exhaust gas swirling in the turbine housing after flowing in the turbine housing. And a supercharger in which the tongue is formed so that one of the nozzle blades is positioned on an extension of the tongue.

  Further, the present invention relates to a supercharger in which a hard film is coated on the nozzle blade so as to include a portion where erosion occurs due to combustion residue.

  According to the present invention, the inner peripheral surface of the tongue is configured by a curved surface continuous with the inner wall surface of the turbine housing, and exhaust gas along the inner peripheral surface is formed between the nozzle blades and the nozzle blades. The present invention relates to a supercharger that is guided to a flow path between nozzles.

  According to the present invention, a required gap is formed between the tip of the tongue and the outer end of the nozzle blade, and exhaust gas along the inner peripheral surface of the tongue extends from the gap to the outer peripheral side. The present invention relates to a supercharger having a shape that suppresses diversion.

  The present invention also relates to a turbocharger in which an extension of the inner peripheral surface of the tongue or a tangent line at the tip of the inner peripheral surface is in contact with the inner surface of the nozzle blade.

  Furthermore, the present invention relates to a supercharger in which the tip of the tongue and the outer end of the nozzle blade are in contact with each other.

  According to the present invention, a turbine impeller is rotatably provided in the turbine housing, nozzle vanes are fixed around the turbine impeller at predetermined angular intervals, and a nozzle vane ring is formed by the nozzle vanes. The nozzle blade ring is directed toward the exhaust gas flowing into the turbine housing, and the turbine housing has a tongue for separating the exhaust gas flowing into the turbine housing and the exhaust gas swirling in the turbine housing after flowing in the turbine housing. Since the tongue portion is formed so that one of the nozzle blades is positioned on the extension of the tongue portion, the exhaust gas along the outer peripheral surface and inner peripheral surface of the tongue portion is effectively It is guided to the flow path between the nozzles, and the separation of the inflowing flow of the exhaust gas by the tongue and the swirling flow in the turbine housing is effectively performed, and a part of the swirling flow may be divided and merged with the inflowing flow. Prevented, Erosion of the turbine housing by shrink residue is prevented.

  Further, according to the present invention, since the nozzle blade is coated with the hard film so as to include a portion where erosion occurs due to the combustion residue, the parts to be coated are small parts and the coating range is small. Less cost is required.

  Further, according to the present invention, the inner peripheral surface of the tongue portion is constituted by a curved surface continuous with the inner wall surface of the turbine housing, and exhaust gas along the inner peripheral surface is formed between the nozzle blade and the nozzle blade. Therefore, a part of the swirl flow is prevented from being diverted and joined to the inflow flow, and erosion of the turbine housing due to the combustion residue is prevented.

  According to the present invention, a required gap is formed between the tip of the tongue and the outer end of the nozzle blade, and the exhaust gas along the inner peripheral surface of the tongue has an outer periphery from the gap. Since the shape that suppresses the diversion to the side is suppressed, the swirling flow of the exhaust gas flowing in the turbine housing can be reduced, and erosion of the turbine housing due to the combustion residue is prevented.

  Further, according to the present invention, the extension of the inner peripheral surface of the tongue or the tangent at the tip of the inner peripheral surface is in contact with the inner surface of the nozzle blade, so that the flow along the inner peripheral surface of the tongue is Smoothly guided to the nozzle flow path.

  Furthermore, according to the present invention, the tip of the tongue and the outer end of the nozzle blade are in contact with each other, so that a part of the swirling flow is prevented from being diverted and joined to the inflowing flow, and the turbine caused by the combustion residue Excellent effect of preventing erosion of housing.

  The best mode for carrying out the present invention will be described below with reference to the drawings.

  In FIG. 1, an outline of a supercharger 10 in which the present invention is implemented will be described.

  In FIG. 1, 11 is an exhaust turbine, 12 is an air supply compressor, and 13 is a shaft support.

  A turbine impeller 15 is provided at one end of a rotating shaft 14 rotatably supported by the shaft support portion 13, and a compressor impeller 16 is provided at the other end of the rotating shaft 14, and the turbine impeller 15, The compressor wheel 16 is rotated integrally with the rotary shaft 14.

  The turbine impeller 15 is housed in a turbine housing 17 provided at one end of the shaft support portion 13, and the compressor wheel 16 is housed in a compressor housing 18 provided at the other end of the shaft support portion 13. Has been.

  The turbine housing 17 is formed in an annular passage 19 formed around the turbine impeller 15, an exhaust gas inlet 21 communicating with the annular passage 19 from a tangential direction, and a central portion of the turbine housing 17. And an exhaust gas outlet 22 that opens in the axial direction of the turbine impeller 15. The compressor housing 18 includes an annular passage 23 formed around the compressor wheel 16, a compressed air discharge port (not shown) communicating with the annular passage 23, and a central portion of the compressor housing 18. And a suction port 24 that opens in the axial direction of the compressor wheel 16.

  The turbine turbine wheel 15 and the turbine housing 17 constitute the exhaust turbine 11, and the compressor wheel 16 and the compressor housing 18 constitute the air supply compressor 12.

  The exhaust gas 25 flows in from the exhaust gas inlet 21, swirls while expanding in the annular channel 19, and further flows out of the exhaust gas outlet 22, so that the energy of the exhaust gas 25 The turbine impeller 15 is rotated. Due to the rotation of the turbine wheel 15, the compressor wheel 16 is rotated through the rotating shaft 14, the air 26 is sucked from the suction port 24, and further compressed in the process of flowing through the annular passage 23. Compressed air is discharged from a compressed air discharge port (not shown) and supplied to a combustion chamber (not shown) of the internal combustion engine.

  Next, the exhaust turbine 11 according to the embodiment of the present invention will be described with reference to FIG.

  The inner periphery of the annular passage 19 communicates with the space in which the turbine impeller 15 is accommodated, and the nozzle vanes 28 are fixed around the turbine impeller 15 at the required angular intervals on the same circumference. The nozzle blade ring 29 is formed by the arrangement of the nozzle blades 28. The nozzle blade 28 has a blade shape in cross section, is inclined at a required angle with respect to the swirling flow of exhaust gas, and directs the flowing exhaust gas toward the center of the nozzle blade ring 29.

  A hard film is formed by coating a hard material on the surface of the nozzle blade 28, particularly on the surface (surface toward the center) facing the exhaust gas flow. The coating is performed by spraying a hard metal such as chrome carbide (Cr3 C2) or ceramic. Further, the thickness of the hard film is about 100 μm to 500 μm, and the thickness of the hard film is uniform at 200 μm to 350 μm at the portion where the adjacent nozzle blades 28 do not overlap on the surface facing the center of the nozzle blade 28. It is preferable. It should be noted that the coating range may be carried out by specifying a portion where erosion occurs by experiment or the like and limiting to the specified portion.

  Further, a tongue 31 forming a part of the exhaust gas inlet 21 is formed inside the turbine housing 17, and the tongue 31 passes through the exhaust gas 25 flowing in and the turbine housing 17 after flowing in. It separates the exhaust gas that has swirled, and further prevents a part of the exhaust gas 25 that has swirled in the annular channel 19 from joining the exhaust gas 25 that has flowed in.

  The tongue 31 is extended, and the tip of the tongue 31 is curved toward the center. Further, one of the nozzle blades 28 is disposed so as to be located on the extension of the tongue portion 31, and an outer end (end on the outer peripheral side) of the nozzle blade 28 and a tip end of the tongue portion 31 are in a predetermined range. A gap 32 is formed.

  The inner peripheral surface of the tongue portion 31 is an extension of the inner wall surface of the turbine housing 17, that is, the inner wall surface of the annular passage 19, and the inner peripheral surface of the tongue portion 31 and the inner wall surface of the turbine housing 17, The inner wall surface of the annular channel 19 is a continuous curved surface, the inner peripheral surface of the tongue 31 has a gradually increasing curvature, and the extension of the inner peripheral surface of the tongue 31 is smooth on the inner surface of the nozzle blade 28. It has become to continue.

  Here, in a smoothly continuous state, when the tangent of the tip of the inner peripheral surface of the tongue 31 is in contact with the inner surface of the nozzle blade 28, or the extension of the curved surface of the inner peripheral surface of the tongue 31 is the nozzle blade 28. The case where it touches the inner surface of the case is considered. The inner peripheral surface of the tongue 31 is a curved surface in which the exhaust gas 25 flowing along the inner wall of the annular channel 19 does not peel off on the inner peripheral surface of the tongue 31 or a curved surface approximated to such a curved surface. It is preferable that

  Also, the outer peripheral surface of the tongue portion 31 is smoothly continuous with the outer surface of the nozzle blade 28. For example, the tangent line at the tip of the outer peripheral surface of the tongue portion 31 contacts the outer surface of the nozzle blade 28, or The extension of the curved surface of the outer peripheral surface of the tongue 31 is in contact with the outer surface of the nozzle blade 28.

  By extending the tongue portion 31 and disposing the nozzle blade 28 on the extension of the tongue portion 31, the exhaust gas 25 flowing along the inner peripheral surface of the tongue portion 31 is allowed to flow into the nozzle blade 28. The flow of exhaust gas along the outer peripheral surface of the tongue 31 is guided to the nozzle passage between the nozzle blades 28b adjacent to the nozzle blades 28a. It is guided to the intermediate flow path 33.

  The operation will be described below.

  The exhaust gas 25 flowing in from the exhaust gas inlet 21 expands while swirling along the annular channel 19, is guided by the nozzle blades 28, and travels toward the turbine impeller 15. By flowing out of the exhaust gas outlet 22 through the turbine impeller 15, the energy of the exhaust gas is transmitted to the turbine impeller 15, and the turbine impeller 15 is rotated.

  In the course of the flow of the exhaust gas 25, the exhaust gas 25 is directed toward the center by the nozzle blades 28, and the exhaust gas 25 that has flowed into the nozzle blade ring 29 further flows into the nozzles by the nozzle blades 28. Outflow to the outside of the wing ring 29 is suppressed. The exhaust gas 25 flowing along the inner peripheral surface of the tongue portion 31 is guided to the inter-nozzle flow path 33 between the nozzle blades 28a adjacent to the nozzle blades 28, and the The flow of exhaust gas along the outer peripheral surface is guided to the inter-nozzle flow path 33 between the nozzle blades 28b adjacent to the nozzle blades 28b.

  The exhaust gas flowing on the outer peripheral surface of the tongue 31 flows along the inner peripheral surface of the tongue 31 by moving toward the inter-nozzle flow path 33 between the nozzle blade 28 and the nozzle blade 28b. The gas 25 is prevented from diverting from the gap 32 to the outer peripheral side.

  Thus, the exhaust gas flowing on the inner peripheral surface of the tongue portion 31 does not flow out of the nozzle blade ring 29 and join the exhaust gas 25 flowing in from the exhaust gas inlet 21. The flow rate of the exhaust gas 25 swirling in the annular channel 19 is significantly reduced, and erosion of the turbine housing 17 due to combustion residues can be suppressed. Therefore, even if a hard film is not formed on the inner surface of the turbine housing 17, erosion due to combustion residues of the turbine housing 17 can be suppressed.

  Further, since the nozzle blade 28 is coated with a hard film, it is possible to prevent the nozzle blade 28 from being eroded by combustion residues. Further, the nozzle blade 28 is a small part compared to the turbine housing 17 and has a small coating range, so that the cost required for coating the nozzle blade 28 is greatly reduced.

  The tongue 31 may be further extended so that the tip of the tongue 31 and the outer end of the nozzle blade 28 are brought into contact with each other. By bringing the tip of the tongue portion 31 and the outer end of the nozzle blade 28 into contact with each other, the gap 32 is eliminated, and a part of the exhaust gas 25 swirling through the annular channel 19 flows into the inflowing exhaust gas 25. It can be completely deterred from joining.

  Further, the curved surface of the inner peripheral surface of the tongue portion 31 so that the exhaust gas 25 flowing along the inner peripheral surface of the tongue portion 31 is directed to the flow path 33 between the nozzle blades 28 and the nozzle blades 28a. What is necessary is just to set a shape. Alternatively, if the shape of the inner peripheral surface of the tongue 31 is prevented from diverting the exhaust gas along the inner peripheral surface from the gap 32 to the outer peripheral side, it is practical even if the gap 32 is provided. By providing the gap 32 without any hindrance, the nozzle blade 28 and the turbine housing 17 can be easily manufactured, and the manufacturing cost can be reduced.

  Further, the positional relationship between the nozzle blade 28 and the tongue portion 31 is at least outside of the nozzle blade 28 with respect to the tangent of the inner peripheral surface tip of the tongue portion 31 or the extension of the curved surface of the inner peripheral surface of the tongue portion 31. It is sufficient that the end does not protrude to the center side.

  The supercharger described above is preferably implemented in an internal combustion engine with a small output fluctuation, such as a marine internal combustion engine.

It is sectional drawing which shows the supercharger which concerns on embodiment of this invention. It is an AA arrow line view of FIG. It is sectional drawing of the turbine housing part which shows the conventional supercharger.

Explanation of symbols

DESCRIPTION OF SYMBOLS 11 Exhaust turbine 12 Air supply compressor 13 Shaft support part 15 Turbine wheel 17 Turbine housing 19 Ring tunnel 21 Exhaust gas inlet 22 Exhaust gas outlet 28 Nozzle blade 29 Nozzle blade ring 31 Tongue part 33 Nozzle flow path

Claims (6)

  A turbine impeller is rotatably provided in the turbine housing, nozzle vanes are fixed around the turbine impeller at predetermined angular intervals, a nozzle vane ring is formed by the nozzle vanes, and the nozzle vane ring is , The exhaust gas flowing into the turbine housing is directed to the center, and the turbine housing has a tongue portion that separates the exhaust gas flowing in and the exhaust gas swirling in the turbine housing after flowing in, The supercharger according to claim 1, wherein the tongue is formed so that one of the nozzle blades is positioned on an extension of the tongue.   The supercharger according to claim 1, wherein the nozzle blade is coated with a hard film so as to include a portion where erosion occurs due to combustion residue.   An inner peripheral surface of the tongue portion is configured by a curved surface continuous with the inner wall surface of the turbine housing, and an exhaust gas along the inner peripheral surface is formed in an inter-nozzle flow path formed between the nozzle blades and the nozzle blades. The turbocharger according to claim 1, wherein the turbocharger is guided.   A required gap is formed between the tip of the tongue and the outer end of the nozzle blade, and the exhaust gas along the inner circumferential surface of the tongue is prevented from being diverted from the gap to the outer circumferential side. The supercharger according to claim 1, wherein the supercharger has a shape to be formed.   The supercharger according to claim 1, wherein an extension of the inner peripheral surface of the tongue portion or a tangent line at the tip of the inner peripheral surface is in contact with the inner surface of the nozzle blade.   The supercharger according to claim 1, wherein a tip of the tongue portion and an outer end of the nozzle blade contact each other.

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