CENTRIFUGAL IMPELLER AND CENTRIFUGAL COMPRESSOR

Abstract

The impeller provides that when an angle made by a projection line 33 that is obtained by projecting a camber line 32 of the blade 22 onto a predetermined meridional cross section and the camber line 32 is defined as an inclination angle γθ and an inclination in a direction opposite to a rotating direction of the rotary shaft is defined to be positive, the blade 22 is formed in such a manner that the inclination angle γθ of a leading edge 22A is zero or positive on the hub 20 side and gradually increasing toward the shroud 21 and the inclination angle is gradually decreasing from the leading edge toward a trailing edge in a flow direction of the fluid.

Claims

1. A centrifugal impeller comprising: a hub; a shroud; and a plurality of blades disposed between the hub and the shroud, the centrifugal impeller blowing out fluid in a radial direction by rotation of a rotary shaft fixed to the hub, wherein when an angle made by a projection line that is obtained by projecting a camber line of the blade onto a predetermined meridional cross section and the camber line is defined as an inclination angle and an inclination in a direction opposite to a rotating direction of the rotary shaft is defined to be positive, the blade is formed in such a manner that the inclination angle of a leading edge is zero or positive on a hub side and gradually increasing toward the shroud and the inclination angle is gradually decreasing from the leading edge toward a trailing edge in a flow direction, and the inclination angle of the trailing edge in the blade is zero or positive on the hub side and gradually increasing toward the shroud.

2. (canceled)

3. The centrifugal impeller according to claim 1, wherein the inclination angle of the trailing edge in the blade is zero or positive over a region from the hub side to the shroud side.

4. The centrifugal impeller according to claim 1, wherein the leading edge of the blade, when projected onto the meridional cross section, has a linear shape from the hub side to the shroud side or a shape protruded toward an upstream side of the flow direction between the hub side and the shroud side.

5. A centrifugal compressor comprising the centrifugal impeller according to claim 1.

6. The centrifugal impeller according to claim 3, wherein the leading edge of the blade, when projected onto the meridional cross section, has a linear shape from the hub side to the shroud side or a shape protruded toward an upstream side of the flow direction between the hub side and the shroud side.

7. A centrifugal compressor comprising the centrifugal impeller according to claim 3.

8. A centrifugal compressor comprising the centrifugal impeller according to claim 4.

Description

BRIEF DESCRIPTION OF DRAWINGS

[0014] FIG. 1 is a longitudinal cross-sectional view of a centrifugal compressor according to the present embodiment.

[0015] FIG. 2 is a partial enlarged view illustrating an impeller.

[0016] FIG. 3 is a diagram for explaining an inclination angle of a blade shown on a meridional cross section.

[0017] FIG. 4 is a diagram illustrating the blade projected on the meridional cross section.

[0018] FIG. 5 is a diagram illustrating an intake port of the impeller as seen from an axial direction.

[0019] FIG. 6 is a schematic view illustrating the shape of a leading edge of the blade of the impeller.

[0020] FIG. 7 is a diagram illustrating a blowoff port of the impeller as seen from a radial direction.

[0021] FIG. 8 is a diagram illustrating the blowoff port of the impeller as seen from the axial direction.

[0022] FIG. 9 is a schematic view illustrating the shape of a trailing edge of the blade of the impeller.

[0023] FIG. 10 is an experimental measurement diagram showing changes in the development of boundary layers due to the shapes of blades in a conventional technique and the present embodiment.

[0024] FIG. 11 is a schematic view illustrating the shape of a leading edge of a blade in a conventional impeller.

[0025] FIG. 12 is a schematic view illustrating the shape of a trailing edge of the blade in the conventional impeller.

DESCRIPTION OF EMBODIMENTS

[0026] An embodiment of the present invention will be described below with reference to the drawings. Note that this invention is not limited by the following embodiment. Note also that elements in the following embodiment encompass those substitutable by and obvious to a person skilled in the art, or substantially the same elements.

[0027] FIG. 1 is a longitudinal cross-sectional view of a centrifugal compressor according to the present embodiment. A centrifugal compressor 1 includes: a casing 2 formed by a combination of a plurality of parts; a rotary shaft 5 supported so as to be rotatable about an axis line L via bearings (not shown) in the casing 2; and closed type impellers 6 fixed to the rotary shaft 5 so as to rotate integrally with the rotary shaft 5. In other words, the centrifugal compressor 1 of the present embodiment is a two-stage centrifugal compressor.

[0028] In the centrifugal compressor 1, the rotary shaft 5 is driven by a driving mechanism (not shown) to rotate the impellers 6. Consequently, fluid, such as gas or air, to be compressed is sucked into the centrifugal compressor 1 via a suction port 10 provided in the casing 2. An intake passage 11 is connected to the suction port 10 via a suction space 10A formed in the casing 2. The intake passage 11 bends along the direction of the axis line L of the rotary shaft 5 (axial direction) and has an opening facing an intake port 6A of the first-stage impeller 6.

[0029] Centrifugal force is imparted to the fluid sucked from the suction port 10 by the rotation of the first-stage impeller 6. The kinetic energy of such fluid is converted to pressure energy by a first-stage vaneless diffuser 12 provided at a blowoff port 6B of the impeller 6. This fluid is further guided to an intake port 6A of the second-stage impeller 6, which is the next compression stage, via a return bend 14 and a return vane 15.

[0030] Similarly, centrifugal force is imparted to such compressed fluid by the second-stage impeller 6. The kinetic energy of such fluid is converted to pressure energy by a second-stage vaneless diffuser 12 and discharged to a scroll 16 as compressed fluid with a higher pressure. Thereafter, the fluid is sent out from the scroll 16 to a discharge pipe (not shown) via a discharge port 17 provided in the casing 2. Note that the reference numeral 18 in FIG. 1 denotes a balance piston provided for adjusting thrust of the impeller 6. The impeller 6 will be described next.

[0031] FIG. 2 is a partial enlarged view illustrating the impeller. As shown in FIG. 2, the impeller 6 includes: a hub 20 fixed to the rotary shaft 5; a shroud 21 disposed with a space from the hub 20 in a radial direction and the axial direction; and a plurality of blades 22 disposed between the hub 20 and the shroud 21. The blades 22 are disposed radially with a space around the axis line L, although their graphic representation is omitted. A leading edge 22A of the blade 22 is positioned on the intake port 6A side of the impeller 6, and a trailing edge 22B extends to the blowoff port 6B of the impeller 6.

[0032] By the way, a boundary layer is generated on an inner wall surface 21A of the shroud 21, which constitutes a fluid passage together with the hub 20, on the intake port 6A side of the impeller 6. This boundary layer grows (develops) on the inner wall surface 21A of the shroud 21 when the fluid flows from the leading edge 22A of the blade 22 toward the trailing edge 22B. Consequently, a large energy deficit is generated at the blowoff port (blade outlet side) 6B. Thus, it is expected to deteriorate the performance of the impeller. In the present embodiment, the shape of the blade 22 has the following configuration in order to suppress the growth of the boundary layer.

[0033] An inclination angle required to define the shape of the blade 22 of the impeller 6 will be described first. FIG. 3 is a diagram for explaining the inclination angle of the blade shown on a meridional cross section. FIG. 4 is a diagram illustrating the blade projected on the meridional cross section. Since the blade 22 of the impeller 6 has a three-dimensional shape, the inclination angle is expressed with a cylindrical coordinate system shown in FIGS. 3 and 4.

[0034] In FIGS. 3 and 4, the Z-axis represents the axis line L of the rotary shaft 5. An r-Z plane formed by the Z-axis and a straight line r extending from an origin point O at an angle made by a predetermined angle θ from the X-axis represents a predetermined meridional cross section 30. When the blade 22 is projected on the meridional cross section 30, a broken line denoted by the reference numeral 31 is a line (streamline) dividing a meridional passage into equal areas in a blade span direction.

[0035] In FIG. 3, the reference numeral 32 denotes a camber line of the blade (for example, the leading edge) before being projected. When the camber line 32 is projected on the meridional cross section 30, a projection line (projection line of the camber line of the blade parallel to the meridional cross section 30) 33 is formed. An angle made by the projection line 33 and the camber line 32 is defined as the inclination angle of the blade 22 (inclination angle in a circumferential direction of the blade) γθ in the present embodiment. Note that the positive or negative sign of the inclination angle γθ is defined in accordance with the rotating direction of the rotary shaft 5. In the present embodiment, a direction opposite to the rotating direction (counter-rotating direction) is defined to be positive.

[0036] Note that the reference numeral 34 denotes a projection line of a camber line of the blade perpendicular to the meridional cross section 30. An angle γZ made by the above-described projection line 33 and the Z-axis (parallel line Z′ translated onto the meridional cross section 30) is defined as an axial tilt angle of the blade projected onto the meridional cross section 30.

[0037] The shape of the blade 22 will be described next. FIG. 5 is a diagram illustrating the intake port of the impeller as seen from the axial direction. FIG. 6 is a schematic view illustrating the shape of the leading edge of the blade of the impeller. As shown in FIG. 6, the leading edge 22A is formed in a curved manner so as to project more on the inner wall surface 21A side of the shroud 21 than on a inner wall surface 20A side of the hub 20. Specifically, the camber line 32 of the leading edge 22A curves in such a manner that the inclination angle γθ with respect to the projection line 33 formed on the above-described meridional cross section 30 (FIG. 3) is approximately zero or positive on the hub 20 side and gradually increasing toward the shroud 21. In such a configuration, the shroud 21 side of the leading edge 22A of the blade 22 inclines in the counter-rotating direction. Thus, a pressure surface P of the blade 22 is disposed so as to face the inner wall surface 21A of the shroud 21. Furthermore, since the inclination angle γθ gradually increases toward the shroud 21, the leading edge 22A inclines more on the shroud 21 side, thus facing the inner wall surface 21A of the shroud 21 in a larger degree. Consequently, gradually toward the shroud 21, force F generated by the pressure surface P of the blade 22 is headed to the inner wall surface 21A of the shroud 21. Note that the curve of the leading edge 22A may be a curve along a single arc or a curve made by a combination of arcs.

[0038] According to this configuration, the inclination angle γθ of the leading edge 22A in the blade 22 is zero or positive on the hub 20 side and gradually increasing toward the shroud 21. Thus, the pressure surface P of the blade 22 faces the inner wall surface 21A of the shroud 21 in a portion of the blade 22 from the leading edge 22A to the first half thereof in a flow direction. Consequently, a boundary layer 35 is pressed against the inner wall surface 21A of the shroud 21 by the force F of the pressure surface P of the blade 22, thereby suppressing the development of the boundary layer 35. On a suction surface S side of the blade 22, a boundary layer 35 generated on the suction surface S is pressed against the suction surface S by centrifugal force F1, thereby preventing its movement toward the shroud 21 and thus suppressing the development of the boundary layer 35.

[0039] The trailing edge 22B side of the blade 22 will be described next. FIG. 7 is a diagram illustrating the blowoff port of the impeller as seen from the radial direction. FIG. 8 is a diagram illustrating the blowoff port as seen from the axial direction. FIG. 9 is a schematic view illustrating the shape of the trailing edge of the blade of the impeller. Unlike the leading edge 22A side, the trailing edge 22B side of the blade 22 is formed in such a manner that the inclination angle γθ of the camber line 32 with respect to the projection line 33 is approximately zero or positive. Such a positive value is preferably closer to zero. A region between the leading edge 22A and the trailing edge 22B in the blade 22 is formed in such a manner that the inclination angle γθ gradually decreases (becomes closer to zero) along the flow direction of the fluid. In this configuration, the trailing edge 22B of the blade 22 erects generally perpendicular to the inner wall surface 20A of the hub 20 and the inner wall surface 21A of the shroud 21, thereby making its height (length) in the direction of the axis line L the shortest distance. Thus, an amount of wake flow due to the thickness of the trailing edge 22B of the blade 22 can be minimized.

[0040] Effects of the present embodiment will be described next. FIG. 10 is an experimental measurement diagram showing changes in the development of the boundary layers due to the shapes of the blades in the conventional technique and the present embodiment. In FIG. 10, A to C show changes in the boundary layer in the configuration using the conventional blade 100 (FIGS. 11 and 12). D to F show changes in the boundary layer in the configuration using the blade 22 of the present embodiment. Specifically, A and D each illustrate an amount of the boundary layer at a position before the outflow port of the impeller. Moreover, B and E each illustrate an amount of the boundary layer in midstream to the outflow port of the impeller. Furthermore, C and F each illustrate an amount of the boundary layer in a middle portion of the length of the blade in the flow direction.

[0041] In the conventional configuration, an amount of the boundary layer 109 (a portion with a particularly large pressure loss in an accumulated development portion of the boundary layer) increases along the flow direction of the fluid (C.fwdarw.B.fwdarw.A). In the present embodiment, on the other hand, while an amount of the boundary layer 35 (a portion with a particularly large pressure loss in an accumulated development portion of the boundary layer) slightly increases along the flow direction of the fluid (F.fwdarw.E.fwdarw.D), the amount of the boundary layer is reduced significantly as compared to the conventional configuration. Thus, it can be understood that the growth of the boundary layer (the portion with a particularly large pressure loss in the accumulated development portion of the boundary layer) can be suppressed.

[0042] As described above, the impeller 6 according to the present embodiment is configured to include the hub 20, the shroud 21, and the plurality of blades 22 disposed between the hub 20 and the shroud 21 and blow out the fluid in the radial direction by the rotation of the rotary shaft 5 fixed to the hub 20. When the angle made by the projection line 33 that is obtained by projecting the camber line 32 of the blade 22 onto the predetermined meridional cross section 30 and the camber line 32 is defined as the inclination angle γθ and an inclination in the direction opposite to the rotating direction of the rotary shaft 5 is defined to be positive, the inclination angle γθ of the leading edge 22A in the blade 22 is zero or positive on the hub 20 side and gradually increasing toward the shroud 21. Thus, the pressure surface P of the blade 22 faces the inner wall surface 21A of the shroud 21 in the portion of the blade 22 from the leading edge 22A to the first half thereof. Consequently, the boundary layer 35 is pressed against the inner wall surface 21A of the shroud 21 by the force F of the pressure surface P of the blade 22, thereby suppressing the development of the boundary layer 35. On the suction surface S of the blade 22, the boundary layer 35 is pressed against the suction surface S by the centrifugal force F1, thereby preventing its movement toward the shroud 21 and thus suppressing the development of the boundary layer 35.

[0043] Furthermore, in the flow direction of the fluid, the blade 22 is formed in such a manner that the inclination angle γθ is gradually decreasing from the leading edge 22A toward the trailing edge 22B. Consequently, the surface area of the blade 22 in the latter half of the blade 22 is reduced, and thus the amount of the boundary layer developed over the blade surface in the latter half of the blade 22 can be reduced. This can suppress the generation of the energy deficit portion on the blade outlet side, thereby allowing the performance of the impeller 6 to be fulfilled sufficiently.

[0044] Moreover, the inclination angle γθ of the trailing edge 22B in the blade 22 is zero or positive over the region from the hub 20 side to the shroud 21 side according to the present embodiment. Thus, the height (length) of the trailing edge 22B of the blade 22 in the direction of the axis line L can be made the shortest distance. Consequently, the amount of the wake flow due to the thickness of the trailing edge 22B of the blade 22 can be minimized. Furthermore, the reduced surface area of the blade 22 in the latter half of the blade 22 can significantly reduce the amount of the boundary layer developed over the blade surface in the latter half of the blade 22 as compared to the conventional technique.

[0045] Moreover, the provision of the above-described impeller 6 in the centrifugal compressor 1 of the present embodiment can suppress the generation of the energy deficit portion on the outlet side of the blade 22, thus improving the compression efficiency of the centrifugal compressor 1.

[0046] While the embodiment of the present invention has been described above, the present invention is not limited by the above details. For example, the above-described embodiment has described the configuration in which the inclination angle γθ of the trailing edge 22B in the blade 22 is zero or positive over a region from the hub 20 side to the shroud 21 side. However, the inclination angle γθ of the trailing edge in the blade 22 may be zero or positive on the hub 20 side and may be gradually increasing toward the shroud 21. According to such a configuration, the pressure surface P of the blade 22 faces the inner wall surface 21A of the shroud 21 also in the latter half of the blade 22. Consequently, the boundary layer 35 is pressed against the shroud 21 by the force of the pressure surface P of the blade 22, thereby suppressing the development of the boundary layer 35 more effectively.

[0047] Moreover, the leading edge 22A of the blade 22, when projected onto the meridional cross section, has the shape in which the hub 20 and the shroud 21 are generally straight lines in the above-described embodiment. However, the present invention is not limited thereto. The leading edge 22A may have a protruding shape protruded toward the upstream side in the flow direction of the fluid between the hub 20 and the shroud 21. According to such a configuration, the area of a portion of the leading edge 22A of the blade 22 facing the shroud 21 can be increased, thereby more effectively suppressing the development of the boundary layer 35 accordingly.

[0048] Moreover, while the leading edge of the blade 22 in the present embodiment is configured such that the inclination angle γθ curves with a gradually larger degree from the hub 20 side toward the shroud 21, the present invention is not limited thereto. The inclination may be configured to increase (bend) sharply so as to turn outwardly (configuration provided with a discontinuous portion somewhere in the span direction). In this case, not a single but a plurality of bent portions (discontinuous portions) may be provided.

[0049] Moreover, while the impeller 6 in the present embodiment is provided in the two-stage centrifugal compressor 1, the impeller 6 can be applied to a single-stage centrifugal compressor or a multistage centrifugal compressor including three or more stages as long as the compressor includes an impeller.

REFERENCE SIGNS LIST

[0050] 1 centrifugal compressor [0051] 2 casing [0052] 5 rotary shaft [0053] 6 impeller (rotary impeller) [0054] 6A intake port [0055] 6B blowoff port [0056] 10 suction port [0057] 10A suction space [0058] 11 intake passage [0059] 12 vaneless diffuser [0060] 14 return bend [0061] 15 return vane [0062] 16 scroll [0063] 17 discharge port [0064] 18 balance piston [0065] 20 hub [0066] 20A inner wall surface [0067] 21 shroud [0068] 21A inner wall surface [0069] 22 blade [0070] 22A leading edge [0071] 22B trailing edge [0072] 30 meridional cross section [0073] 32 camber line [0074] 33 projection line [0075] 35 boundary layer (a portion with a particularly large pressure loss in an accumulated development portion of the boundary layer) [0076] 100 blade [0077] 101 intake port [0078] 102 leading edge [0079] 103 camber line [0080] 104 straight line [0081] 105 wall surface [0082] 106 wall surface [0083] 107 blowoff port [0084] 108 trailing edge [0085] 109 boundary layer (a portion with a particularly large pressure loss in an accumulated development portion of the boundary layer) [0086] L axis line [0087] O origin point [0088] P pressure surface [0089] S suction surface [0090] Z′ parallel line [0091] r straight line [0092] γθ inclination angle