Rotary machine

Abstract

A rotary machine satisfies at least one of Dr1<Dh1Dr2 or Dc1Dt1>Dc2. Dr1, Dh1, Dr2, Dc1, Dt1, and Dc2 are distances from a rotational center axis of a hub to an upstream end of a first blade-facing surface facing a hub-side end surface of a variable blade, an upstream end of the hub-side end surface when the blade angle is maximum, a downstream end of a first outer peripheral surface adjacent to an upstream side of the blade-facing surface, an upstream end of a second blade-facing surface facing a tip-side end surface of the variable blade, an upstream end of the tip-side end surface when the blade angle is minimum, and a downstream end of a first inner peripheral surface adjacent to an upstream side of the second blade-facing surface, respectively.

Claims

1. A rotary machine comprising: a hub configured to be rotatable about a rotational center axis; a casing configured to cover the hub and forming a fluid flow passage between the casing and the hub; and a variable blade disposed in the fluid flow passage and configured to be revolvable about a pivot axis along a radial direction of the hub, wherein the hub includes: a blade-facing hub portion including a first blade-facing surface facing a hub-side end surface of the variable blade; and an upstream hub portion disposed upstream of the blade-facing hub portion in an axial direction of the hub and having a first outer peripheral surface being adjacent to the first blade-facing surface in the axial direction, wherein the casing includes: a blade-facing casing portion including a second blade-facing surface which faces a tip-side end surface of the variable blade; and an upstream casing portion disposed upstream of the blade-facing casing portion in the axial direction and having a first inner peripheral surface being adjacent to the second blade-facing surface in the axial direction, wherein at least one of following condition (a) or (b) is satisfied:
Dr1<Dh1Dr2(a)
Dc1Dt1>Dc2(b) where Dr1 is a distance between an upstream end of the first blade-facing surface and the rotational center axis of the hub, Dh1 is a distance between an upstream end of the hub-side end surface of the variable blade and the rotational center axis of the hub when an angle formed between the axial direction of the hub and a chord line of the variable blade is maximum, Dr2 is a distance between a downstream end of the first outer peripheral surface and the rotational center axis of the hub, Dc1 is a distance between an upstream end of the second blade-facing surface and the rotational center axis of the hub, Dt1 is a distance between an upstream end of the tip-side end surface of the variable blade and the rotational center axis of the hub when the angle formed between the axial direction of the hub and the chord line of the variable blade is minimum, and Dc2 is a distance between a downstream end of the first inner peripheral surface and the rotational center axis of the hub, and wherein when condition (a) is satisfied, a distance between Dh1 and Dr1 increases when the angle formed between the axial direction of the hub and the chord line of the variable blade is maximum; and when condition (b) is satisfied, a distance between Dt1 and Dc1 decreases when the angle formed between the axial direction of the hub and the chord line of the variable blade is maximum.

2. The rotary machine according to claim 1, wherein at least the above condition (a) is satisfied, and wherein the first blade-facing surface is inclined so as to be away from the rotational center axis of the hub toward downstream.

3. The rotary machine according to claim 1, wherein at least the above condition (b) is satisfied, and wherein the second blade-facing surface is inclined so as to be closer to the rotational center axis of the hub toward downstream.

4. The rotary machine according to claim 1, wherein the hub includes a downstream hub portion disposed downstream of the blade-facing hub portion in the axial direction of the hub, wherein the downstream hub portion includes a second outer peripheral surface adjacent to the first blade-facing surface in the axial direction, and wherein an expression Dh2Dr3 is satisfied, where Dh2 is a distance between a downstream end of the hub-side end surface of the variable blade and the rotational center axis of the hub when the angle formed between the axial direction of the hub and the chord line of the variable blade is minimum, and Dr3 is a distance between an upstream end of the second outer peripheral surface and the rotational center axis of the hub.

5. The rotary machine according to claim 2, wherein the hub includes a downstream hub portion disposed downstream of the blade-facing hub portion in the axial direction of the hub, wherein the downstream hub portion includes a second outer peripheral surface adjacent to the first blade-facing surface in the axial direction, and wherein an expression Dh3Dr3 is satisfied, where Dh3 is a distance between a downstream end of the hub-side end surface of the variable blade and the rotational center axis of the hub when the angle formed between the axial direction of the hub and the chord line of the variable blade is maximum, and Dr3 is a distance between an upstream end of the second outer peripheral surface and the rotational center axis of the hub.

6. The rotary machine according to claim 1, wherein the casing includes a downstream casing portion disposed downstream of the blade-facing casing portion in the axial direction of the hub, wherein the downstream casing portion includes a second inner peripheral surface adjacent to the second blade-facing surface in the axial direction, and wherein an expression Dt2Dc3 is satisfied, where Dt2 is a distance between a downstream end of the tip-side end surface of the variable blade and the rotational center axis of the hub when an angle formed between the axial direction of the hub and the chord line of the variable blade is maximum, and Dc3 is a distance between an upstream end of the second inner peripheral surface and the rotational center axis of the hub.

7. The rotary machine according to claim 3, wherein the casing includes a downstream casing portion disposed downstream of the blade-facing casing portion in the axial direction of the hub, wherein the downstream casing portion includes a second inner peripheral surface adjacent to the second blade-facing surface in the axial direction, and wherein an expression Dt3Dc3 is satisfied, where Dt3 is a distance between a downstream end of the tip-side end surface of the variable blade and the rotational center axis of the hub when the angle formed between the axial direction of the hub and the chord line of the variable blade is minimum, and Dc3 is a distance between an upstream end of the second inner peripheral surface and the rotational center axis of the hub.

8. The rotary machine according to claim 1, wherein a groove generated by gap between the tip-side end surface of the variable blade and the second blade-facing surface is deepened and a groove generated by second gap between the hub-side end surface and the first blade-facing surface is flattened as the angle formed between the axial direction of the hub and the chord line of the variable blade decreases, and the groove generated by the gap between the tip-side end surface and the second-blade facing surface is flattened and the groove generated by second gap between the hub-side end surface and the first blade-facing surface is deepened as the angle formed between the axial direction of the hub and the chord line of the variable blade increases.

Description

BRIEF DESCRIPTION OF DRAWINGS

(1) FIG. 1 is a cross-sectional view of a schematic configuration of an axial-flow compressor according to some embodiments.

(2) FIG. 2 is a schematic diagram for describing the blade angle 1 of rotor blade and the blade angle 2 of stationary vane, showing a rotor blade or a stationary vane and a part of a hub seen from outside in the radial direction of the hub.

(3) FIGS. 3A and 3B are each a schematic meridional cross-sectional view showing a part of an axial-flow compressor according to an embodiment. FIG. 3A is a meridional cross-sectional shape of and around a rotor blade when the blade angle of the rotor blade is at its minimum. FIG. 3B is a meridional cross-sectional shape of and around a rotor blade when the blade angle of the rotor blade is at its maximum.

(4) FIGS. 4A and 4B are each a schematic meridional cross-sectional view showing a part of an axial-flow compressor according to an embodiment. FIG. 4A is a meridional cross-sectional shape of and around a rotor blade when the blade angle of the rotor blade is at its minimum. FIG. 4B is a meridional cross-sectional shape of and around a rotor blade when the blade angle of the rotor blade is at its maximum.

(5) FIGS. 5A and 5B are each a schematic meridional cross-sectional view showing a part of an axial-flow compressor according to an embodiment. FIG. 5A is a meridional cross-sectional shape of and around a rotor blade when the blade angle of the rotor blade is at its minimum. FIG. 5B is a meridional cross-sectional shape of and around a rotor blade when the blade angle of the rotor blade is at its maximum.

(6) FIG. 6 is a schematic meridional cross-sectional view of a part of an axial-flow compressor according to an embodiment.

(7) FIG. 7 is a schematic diagram showing the shape (solid line) of the rotor blade as seen from the upstream side along the axial direction of the hub when the blade angle is at its minimum, and the shape (two dotted chain line) of the rotor blade as seen from the upstream side along the axial direction of the hub when the blade angle is at its maximum.

(8) FIG. 8 is a schematic meridional cross-sectional shape for describing a recirculation flow that occurs due to a step between the first outer peripheral surface and the first blade-facing surface or a step between the first inner peripheral surface and the second blade-facing surface.

(9) FIG. 9 is a diagram showing a static-pressure distribution with respect to the chord directional position, for the pressure surface and the suction surface of a rotor blade. Herein, the chord directional position is a dimensionless blade-chord length, where 0% represents the leading edge of the rotor blade and 100% represents the trailing edge.

DETAILED DESCRIPTION

(10) Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. It is intended, however, that unless particularly specified, dimensions, materials, shapes, relative positions and the like of components described in the embodiments shall be interpreted as illustrative only and not intended to limit the scope of the present invention.

(11) For instance, an expression of relative or absolute arrangement such as in a direction, along a direction, parallel, orthogonal, centered, concentric and coaxial shall not be construed as indicating only the arrangement in a strict literal sense, but also includes a state where the arrangement is relatively displaced by a tolerance, or by an angle or a distance whereby it is possible to achieve the same function.

(12) On the other hand, an expression such as comprise, include, have, contain and constitute are not intended to be exclusive of other components.

(13) FIG. 1 is a cross-sectional view of a schematic configuration of an axial-flow compressor 100 serving as a rotary machine according to some embodiments.

(14) The axial-flow compressor 100 shown in FIG. 1 includes a hub 2 configured to rotate about the rotational center axis O1, a casing 6 configured to cover the hub 2 and forming a fluid flow passage 4 with the hub 2, rotor blades 8 fixed to the hub 2, and stationary vanes 10 fixed to the casing 6.

(15) The rotor blades 8 are disposed in the fluid flow passage 4, and configured to be revolvable about the pivot axis O2 along the radial direction of the hub 2, thereby being capable of changing the angle 1 (see FIG. 2; hereinafter, the angle 1 is referred to as the blade angle of rotor blade) formed between the axial direction of the hub 2 and the chord line of the rotor blade 8. A plurality of rotor blades 8 are arranged in the circumferential direction at an axial-directional position on the rotational center axis O1, forming one rotor-blade row. A plurality of rotor-blade rows are arranged along the axial direction of the rotational center axis O1 (hereinafter, referred to as the axial direction of the hub 2).

(16) The stationary vanes 10 are disposed in the fluid flow passage 4, and configured to be revolvable about the pivot axis O3 along the radial direction of the hub 2, thereby being capable of changing the angle 2 (see FIG. 2; hereinafter, the angle 2 is referred to as the blade angle of stationary vane) formed between the axial direction of the hub 2 and the chord line of the stationary vane 10. A plurality of stationary vanes 10 are arranged in the circumferential direction at a position in the axial direction of the hub 2, forming one stationary-vane row. The rotor-blade rows and the stationary-vane rows are arranged alternately in the axial direction of the hub.

(17) When the hub 2 and the rotor blades 8 fixed to the hub 2 rotate about the rotational center axis O1, a fluid that flows from an inlet 7 of the casing 6 becomes compressed, and the compressed fluid flows out from an outlet 9 of the casing 6.

(18) Next, with regard to the axial-flow compressor 100 shown in FIG. 1, a rotor blade 8 and the meridional cross-sectional shape around the rotor blade 8 according to some embodiments will be described with reference to FIGS. 3 to 5.

(19) FIGS. 3A and 3B are each a schematic meridional cross-sectional view showing a part of the axial-flow compressor 100 according to an embodiment. FIG. 3A is a meridional cross-sectional shape of and around the rotor blade 8 when the blade angle of the rotor blade 8 is at its minimum. FIG. 3B is a meridional cross-sectional shape of and around the rotor blade 8 when the blade angle of the rotor blade 8 is at its maximum. FIGS. 4A and 4B are each a schematic meridional cross-sectional view showing a part of the axial-flow compressor 100 according to an embodiment. FIG. 4A is a meridional cross-sectional shape of and around the rotor blade 8 when the blade angle of the rotor blade 8 is at its minimum. FIG. 4B is a meridional cross-sectional shape of and around the rotor blade 8 when the blade angle of the rotor blade 8 is at its maximum. FIGS. 5A and 5B are each a schematic meridional cross-sectional view showing a part of the axial-flow compressor 100 according to an embodiment. FIG. 5A is a meridional cross-sectional shape of and around the rotor blade 8 when the blade angle of the rotor blade 8 is at its minimum. FIG. 5B is a meridional cross-sectional shape of and around the rotor blade 8 when the blade angle of the rotor blade 8 is at its maximum.

(20) In some embodiments, as shown in FIGS. 3A to 5B for instance, the hub 2 includes a blade-facing hub portion 16 including the first blade-facing surface 14 facing the hub-side end surface 12 of the rotor blade 8, and an upstream hub portion 20 disposed upstream of the blade-facing hub portion 16 in the axial direction of the hub 2 and including the first outer peripheral surface 18 being adjacent to the first blade-facing surface 14 in the axial direction of the hub 2. Furthermore, as shown in FIGS. 3A to 5B for instance, the casing 6 includes a blade-facing casing portion 26 including the second blade-facing surface 24 facing the tip-side end surface 22 of the rotor blade 8, and an upstream casing portion 30 disposed upstream of the blade-facing casing portion 26 in the axial direction of the hub 2 and including the first inner peripheral surface 28 being adjacent to the second blade-facing surface 24 in the axial direction of the hub 2.

(21) Furthermore, the upstream hub portion 20, the blade-facing hub portion 16, and the downstream hub portion 32 may be formed integrally (of one piece), or may be formed separately (of separate members). Alternatively, at least one of the upstream hub portion 20, the blade-facing hub portion 16, or the downstream hub portion 32 may be formed of a plurality of members. For instance, as shown in FIG. 6, the blade-facing hub portion 16 may be formed of a plurality of members.

(22) Furthermore, the upstream casing portion 30, the blade-facing casing portion 26, and the downstream casing portion 36 may be formed integrally (of one piece), or may be formed separately (of separate members). Alternatively, at least one of the upstream casing portion 30, the blade-facing casing portion 26, or the downstream casing portion 36 may be formed of a plurality of members. For instance, as shown in FIG. 6, the blade-facing casing portion 26 may be formed of a plurality of members.

(23) In some embodiments, as shown in FIGS. 3A to 5B for instance, the axial-flow compressor 100 is configured so as to satisfy at least one of the following condition (a) or (b).
Dr1<Dh1Dr2(a)
Dc1Dt1>Dc2(b)

(24) Herein, as shown in FIGS. 3B, 4B, and 5B, Drl is the distance between the upstream end 14a of the first blade-facing surface 14 and the rotational center axis O1 of the hub 2, Dh1 is the distance between the upstream end 12a on the hub-side end surface 12 of the rotor blade 8 and the rotational center axis O1 of the hub 2 when the blade angle of the rotor blade 8 is at its maximum, and Dr2 is the distance between the downstream end 18a of the first outer peripheral surface 18 and the rotational center axis O1 of the hub 2. Furthermore, as shown in FIGS. 3A, 4A, and 5A, Dc1 is the distance between the upstream end 24a of the second blade-facing surface 24 and the rotational center axis O1 of the hub 2, Dt1 is the distance between the upstream end 22a of the tip-side end surface 22 of the rotor blade 8 and the rotational center axis O1 of the hub 2 when the blade angle of the rotor blade 8 is at its minimum, and Dc2 is the distance between the downstream end 28a of the first inner peripheral surface 28 and the rotational center axis O1 of the hub 2.

(25) Next, the technical advantage of satisfying at least one of the condition (a) or (b) will be described with reference to FIG. 7.

(26) FIG. 7 is a schematic diagram showing the shape 8a (solid line) of the rotor blade 8 as seen in the axial direction of the hub 2 when the blade angle is at its minimum, and the shape 8b (two dotted chain line) of the rotor blade 8 as seen in the axial direction of the hub 2 when the blade angle is at its maximum.

(27) FIG. 7 shows that the clearance between the hub-side end surface 12 of the rotor blade 8 and the first blade-facing surface 14 of the hub 2 (hereinafter, referred to as merely hub-side clearance) is greater by the region Ch when the blade angle of the rotor blade 8 is at its maximum than when the blade angle of the rotor blade 8 is at its minimum. In a case where the hub-side end surface 12 of the rotor blade 8 and the first blade-facing surface 14 of the hub 2 are configured not to interfere with each other in the rotation range of the rotor blade 8, the hub-side clearance increases as the blade 8 is revolved to the close side (direction A in FIG. 7, that is a direction that the blade angle increases). Thus, the hub-side clearance is the maximum when the blade angle of the rotor blade 8 is at its maximum.

(28) FIG. 7 shows that the clearance between the tip-side end surface 22 of the rotor blade 8 and the second blade-facing surface 24 of the casing 6 (hereinafter, referred to as tip-side clearance) is greater by the region Ct when the blade angle of the rotor blade 8 is at its minimum than when the angle of the rotor blade 8 is at its maximum. In a case where the tip-side end surface 22 of the rotor blade 8 and the second blade-facing surface 24 of the casing 6 are configured not to interfere with each other in the rotation range of the rotor blade 8, the tip-side clearance increases as the rotor blade 8 is revolved to the open side (direction B of FIG. 7, that is a direction that the blade angle decreases). Thus, the hub-side clearance is the maximum when the blade angle of the rotor blade 8 is at its minimum.

(29) Accordingly, with the axial-flow compressor 100 shown in FIG. 3A to FIG. 5B, if at least one of the above condition (a) or (b) is satisfied, at least one of the hub-side clearance Ch or the tip-side clearance Ct is retracted from the mainstream of the fluid flow passage 4 at the upstream end of the rotor blade 8 at any blade angle. Thus, it is possible to reduce clearance loss due to a leakage flow that passes through at least one of the hub-side clearance Ch or the tip-side clearance Ct.

(30) Furthermore, with the axial-flow compressor 100 shown in FIGS. 3A to 5B, if at least one of Dr1<Dr2 (part of condition (a)) or Dc1>Dc2 (part of condition (b)) is satisfied, a step g is formed in at least one of the gap between the first outer peripheral surface 18 and the first blade-facing surface 14 or the gap between the first inner peripheral surface 28 and the second blade-facing surface 24. This step g, as shown in FIG. 8, generates a recirculation flow in at least one of the vicinity of the first blade-facing surface 14 of the hub 2 or the vicinity of the second blade-facing surface 24 of the casing 6. This recirculation flow increases the virtual flow rate, and thus it is possible to suppress separation on the hub 2 or the casing 6.

(31) In some embodiments, shown in FIGS. 5A and 5B for instance, the axial-flow compressor 100 satisfies at least the above condition (a), and the first blade-facing surface 14 is inclined so as to be away from the rotational center axis O1 of the hub toward downstream.

(32) Herein, whether separation occurs tends to depend on the flow rate in the vicinity of the leading edge of the rotor blade 8. If the flow rate in the vicinity of the leading edge of the rotor blade 8 is set to be high, separation can be suppressed easily even if the flow rate is somewhat small in the vicinity of the trailing edge of the rotor blade 8. Further, as shown in FIG. 9, the pressure difference between the pressure surface and the suction surface of the blade tends to be greater at the leading-edge side of the blade (upstream of the center of the chord line of the blade). A leakage flow passing through the hub-side clearance Ch is created by the pressure difference between the pressure surface and the suction surface of the rotor blade 8. Thus, if the clearance on the leading-edge side of the rotor blade 8 with the maximum pressure difference is off the mainstream, it is possible to reduce the clearance loss effectively.

(33) As described above, the need for the effect to reduce clearance loss and suppress separation is greater at the leading-edge side of the rotor blade 8 and relatively smaller at the trailing-edge side. Thus, on the trailing-edge side, the disadvantage from a decrease in the efficiency accompanying generation of a recirculation flow may outweigh the advantage of the effect to reduce clearance loss and suppress separation.

(34) In this regard, with the axial-flow compressor 100 shown in FIG. 5A and FIG. 5B, if the above condition (a) is satisfied, the upstream end of the hub-side clearance Ch is retracted from the mainstream of the fluid flow passage 4 at any blade angle. Thus, at the leading-edge side of the rotor blade 8, it is possible to reduce clearance loss due at a leakage flow that passes through the hub-side clearance Ch and suppress a decrease in separation by forming a recirculation flow. Furthermore, with the axial-flow compressor 100 shown in FIGS. 5A and 5B, the first blade-facing surface 14 is inclined so as to be away from the rotational center axis O1 of the hub 2 toward downstream, and thereby it is possible to suppress the disadvantage caused by the recirculation flow at the trailing-edge side of the rotor blade 8.

(35) In some embodiments, as shown in FIGS. 5A and 5B for instance, the axial-flow compressor 100 satisfies at least the above condition (b), and the second blade-facing surface 24 is inclined so as to be closer to the rotational center axis O1 of the hub 2 toward downstream.

(36) As described above, the need for the effect to reduce clearance loss and suppress separation is greater at the leading-edge side of the rotor blade 8 and relatively smaller at the trailing-edge side. Thus, on the trailing-edge side, the disadvantage from a decrease in the efficiency accompanying generation of a recirculation flow may outweigh the advantage of the effect to reduce clearance loss and suppress separation.

(37) In this regard, with the axial-flow compressor 100 shown in FIG. 5A and FIG. 5B, if the above condition (b) is satisfied, the upstream end of the tip-side clearance Ct is retracted from the mainstream of the fluid flow passage 4 at any blade angle. Thus, at the leading-edge side of the rotor blade 8, it is possible to reduce clearance loss caused by a leakage flow that passes through the tip-side clearance Ct and suppress a decrease in separation by forming a recirculation flow. Furthermore, with the axial-flow compressor 100 shown in FIGS. 5A and 5B, the second blade-facing surface 24 is inclined so as to be closer to the rotational center axis O1 of the hub 2 toward downstream, and thereby it is possible to suppress the disadvantage caused by the recirculation flow at the trailing-edge side.

(38) In some embodiments, as shown in FIGS. 3A, 4A, and 5A for instance, the hub 2 includes a downstream hub portion 32 disposed downstream of the blade-facing hub portion 16 in the axial direction of the hub 2. The downstream hub portion 32 has the second outer peripheral surface 34 adjacent to the first blade-facing surface 14 in the axial direction. The axial-flow compressor 100 is configured to satisfy Dh2Dr3.

(39) Herein, Dh2 is the distance between the downstream end 12b of the hub-side end surface 12 of the rotor blade 8 and the rotational center axis O1 of the hub 2 when the blade angle of the rotor blade 8 is at its minimum, and Dr3 is the distance between the upstream end 34a of the second outer peripheral surface 34 and the rotational center axis O1 of the hub 2.

(40) With this configuration, Dh2Dr3 is satisfied, and thereby the hub-side clearance Ch is retracted from the mainstream of the fluid flow passage 4 from the leading-edge side to the trailing-edge side when the blade angle is at its minimum.

(41) As described above, the need for the effect to reduce clearance loss is greater at the leading-edge side of the rotor blade 8 (upstream of the center of the chord line of the rotor blade 8) and relatively smaller at the trailing-edge side of the rotor blade 8. Thus, as with the axial-flow compressor 100 shown in FIGS. 3A to 5B, at the trailing-edge side of the rotor blade 8, if the hub-side clearance Ch is retracted from the mainstream of the fluid flow passage 4 when the blade angle is minimum, it is possible to satisfy the need for the effect to reduce clearance loss to some extent.

(42) In some embodiments, as shown in FIGS. 3B and 5B for instance, the axial-flow compressor 100 satisfies Dh3Dr3.

(43) Herein, Dh3 is the distance between the downstream end 12b of the hub-side end surface 12 of the rotor blade 8 and the rotational center axis O1 of the hub 2 when the blade angle is at its maximum, and Dr3 is the distance between the upstream end 34a of the second outer peripheral surface 34 and the rotational center axis O1 of the hub 2.

(44) With this configuration, the entire region of the hub-side clearance Ch is retracted from the mainstream of the fluid flow passage 4 at any blade angle. Thus, it is possible to enjoy the effect to reduce clearance loss caused by a leakage flow that passes through the hub-side clearance Ch at any blade angle.

(45) In some embodiments, as shown in FIGS. 3B, 4B, and 5B for instance, the casing 6 includes a downstream casing portion 36 disposed downstream of the blade-facing casing portion 26 in the axial direction of the hub 2. The downstream casing portion 36 has the second inner peripheral surface 38 adjacent to the second blade-facing surface 24 in the axial direction. The axial-flow compressor 100 is configured to satisfy Dt2Dc3.

(46) Herein, Dt2 is the distance between the downstream end 22b on the tip-side end surface 22 of the rotor blade 8 and the rotational center axis O1 of the hub 2 when the blade angle is at its maximum, and Dc3 is the distance between the upstream end 38a of the second inner peripheral surface 38 and the rotational center axis O1 of the hub 2.

(47) With this configuration, Dt2Dc3 is satisfied, and thereby the tip-side clearance Ct is retracted from the mainstream of the fluid flow passage 4 when the blade angle is at its maximum.

(48) As described above, the need for the effect to reduce clearance loss is greater at the leading-edge side of the rotor blade 8 and relatively smaller at the trailing-edge side of the rotor blade 8. Thus, as with the axial-flow compressor 100 shown in FIGS. 3B, 4B and 5B, at the trailing-edge side of the rotor blade 8, if the tip-side clearance Ct is retracted from the mainstream of the fluid flow passage 4 when the blade angle is maximum, it is possible to satisfy the need for the effect to reduce clearance loss to some extent.

(49) In some embodiments, as shown in FIGS. 3A and 5A for instance, the axial-flow compressor 100 satisfies Dt3Dc3.

(50) Herein, Dt3 is the distance between the downstream end 22b of the tip-side end surface 22 of the rotor blade 8 and the rotational center axis O1 of the hub 2 when the blade angle is at its minimum, and Dc3 is the distance between the upstream end 38a of the second inner peripheral surface 38 and the rotational center axis O1 of the hub 2.

(51) With this configuration, the entire region of the tip-side clearance Ct is retracted from the mainstream of the fluid flow passage 4 at any blade angle. Thus, it is possible to enjoy the effect to reduce clearance loss caused by a leakage flow that passes through the tip-side clearance Ch at any blade angle.

(52) In some embodiments, the axial-flow compressor 100 may satisfy Dt3<Dc3 as shown in FIG. 4A for instance, or may satisfy Dh3>Dr3 as shown in FIG. 4B for instance. As described above, the need for the effect to reduce clearance loss is relatively small at the trailing-edge side of the rotor blade 8, and thus even with this configuration, satisfying at least one of the above condition (a) or (b) makes it possible to enjoy the effect to reduce clearance loss caused by a leakage flow that passes through the tip-side clearance Ct.

(53) Embodiments of the present invention were described in detail above, but the present invention is not limited thereto, and various amendments and modifications may be implemented.

(54) For instance, while the relationship between the shape of the rotor blade 8 and the shape of the hub 2 or the casing 6 is described in the above embodiments, this relationship can be applied to the relationship between the shape of the stationary vane 10 and the shape of the hub 2 or the casing 6.

(55) Furthermore, to suppress an increase in the hub-side clearance or the tip-side clearance when changing the blade angle, spherical machining as described in Patent Document 1 may be applied to the hub-side end surface 12, the first blade-facing surface 14, the tip-side end surface 22, and the second blade-facing surface 24 if needed.

(56) Furthermore, the present invention can be applied to a rotary machine such as a boiler axial-flow fan, a blast-furnace axial-flow blower, a gas turbine compressor, and various turbines.

DESCRIPTION OF REFERENCE NUMERALS

(57) 2 Hub 4 Fluid flow passage 6 Casing 7 Inlet 8 Rotor blade 9 Outlet 10 Stationary vane 12 Hub-side end surface 12a Upstream end of hub-side end surface 12b Downstream end of hug-side end surface 14 First blade-facing surface 14a Upstream end of first blade-facing surface 16 Blade-facing hub portion 18 First outer peripheral surface 18a Downstream end of first outer peripheral surface 20 Upstream hub portion 22 Tip-side end surface 22a Upstream end of tip-side end surface 22b Downstream end of tip-side end surface 24 Second blade-facing surface 24a Upstream end of second blade facing surface 26 Blade-facing casing portion 28 first inner peripheral surface 28a Downstream end of inner peripheral surface 30 Upstream casing portion 32 Downstream hub portion 34 Second outer peripheral surface 34a Upstream end of second outer peripheral surface 36 Downstream casing portion 38 Second inner peripheral surface 38a Upstream end of second inner peripheral surface 100 Axial-flow compressor