WO2017072843A1 - 回転機械 - Google Patents
回転機械 Download PDFInfo
- Publication number
- WO2017072843A1 WO2017072843A1 PCT/JP2015/080168 JP2015080168W WO2017072843A1 WO 2017072843 A1 WO2017072843 A1 WO 2017072843A1 JP 2015080168 W JP2015080168 W JP 2015080168W WO 2017072843 A1 WO2017072843 A1 WO 2017072843A1
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- WIPO (PCT)
- Prior art keywords
- blade
- hub
- facing
- facing surface
- distance
- Prior art date
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D7/00—Rotors with blades adjustable in operation; Control thereof
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/025—Fixing blade carrying members on shafts
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
- F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/16—Sealings between pressure and suction sides
- F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
- F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/322—Blade mountings
- F04D29/323—Blade mountings adjustable
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/24—Three-dimensional ellipsoidal
- F05D2250/241—Three-dimensional ellipsoidal spherical
Definitions
- This disclosure relates to rotating machinery.
- At least one of the stationary blades and the moving blades is configured as a variable blade that can be rotated around a rotation axis along the radial direction of the hub in order to adjust the angle of attack to the flow. May be.
- variable blade In a rotating machine equipped with such a variable blade, when the variable blade is configured so that the hub-side end surface of the variable blade does not interfere with the blade-facing surface of the hub in the rotation range of the variable blade, the variable blade is closed
- the clearance between the hub-side end surface of the variable blade and the blade-facing surface of the hub is easily enlarged when the cord line is rotated in the direction in which the angle formed by the cord line and the axial direction of the hub increases.
- clearance loss loss due to leakage flow that passes through the clearance
- the variable blade has a spherical hub-side end surface that is concave outward in the radial direction of the hub so that the clearance does not increase even if the variable blade is rotated to the closed side, and the blade of the hub
- a rotating machine having a spherical spherical region in which the opposing surface is convex outward in the radial direction of the hub is disclosed.
- At least one embodiment of the present invention reduces clearance loss and reduces performance in a rotary machine including variable blades configured to be rotatable around a rotation axis along the radial direction of the hub. It aims at suppressing.
- a rotating machine is configured to cover a hub configured to rotate around a rotation center axis and to form a fluid flow path between the hub and the hub.
- a rotating machine including a casing and a variable wing disposed on the fluid flow path and configured to be rotatable about a rotation axis along a radial direction of the hub.
- a spherical hub-side end surface that is concave outward in the radial direction of the hub, and the hub faces the hub-side end surface of the variable wing and protrudes outward in the radial direction of the hub.
- a blade-facing hub portion including a first blade-facing surface having a region, and a first outer periphery provided upstream of the blade-facing hub portion in the axial direction of the hub and adjacent to the first blade-facing surface in the axial direction
- An upstream hub portion having a surface and the axial direction
- a downstream hub portion provided on the downstream side of the blade-facing hub portion and having a second outer peripheral surface adjacent to the first blade-facing surface in the axial direction, the following conditions (a) and ( A rotating machine that satisfies at least one of b).
- the downstream end of the first outer peripheral surface is positioned more outward in the radial direction of the hub than the upstream end of the first blade-facing surface.
- the upstream end of the second outer peripheral surface is located outside the downstream end of the first blade-facing surface in the radial direction of the hub.
- the variable blade is rotated to the close side.
- the clearance between the hub-side end surface of the variable blade and the blade-facing surface of the hub does not basically increase. For this reason, clearance loss can be reduced.
- a virtual extension surface in which the first outer peripheral surface is extended to the downstream side as compared with the case where the condition (a) is not satisfied. It is possible to form the first blade-facing surface so that the amount of protrusion of the hub toward the radially outer side is small.
- the first blade-facing surface can be formed so as not to protrude outward in the radial direction of the hub with respect to the virtual extension surface.
- production of a secondary flow is suppressed and the performance reduction of a rotary machine is reduced. It becomes easy to suppress.
- a virtual extension surface in which the second outer peripheral surface is extended upstream as compared with the case where the condition (a) is not satisfied.
- the first blade-facing surface so that the amount of protrusion of the hub toward the radially outer side is small.
- the first blade-facing surface can be formed so as not to protrude outward in the radial direction of the hub with respect to the virtual extension surface.
- the first blade-facing surface can be formed so as to suppress the peeling phenomenon behind the spherical region, so that it is easy to suppress the performance deterioration of the rotating machine. Therefore, according to the rotating machine described in the above (1), it is easy to suppress the performance deterioration of the rotating machine by satisfying at least one of the condition (a) and the condition (b).
- the rotating machine satisfies at least the condition (a), and the first blade-facing surface is downstream of the first outer peripheral surface. It is formed so as not to protrude outward in the radial direction of the hub from the first virtual extension surface extended in the direction.
- the rotating machine satisfies at least the condition (b), and the first blade-facing surface is the second outer periphery. It is formed so as not to protrude outward in the radial direction of the hub from a second virtual extended surface whose surface is extended upstream.
- the spherical center of the first spherical region is the rotation axis of the variable blade and the rotation. Located at the intersection with the rotation center axis of the machine, the spherical radius of the first spherical region is R0, and the distance between the first virtual extension surface extending the first outer peripheral surface downstream and the spherical center is R1. Then, the first spherical region is formed so as to satisfy R0 ⁇ R1.
- the spherical center of the first spherical region is the rotation axis of the variable blade and the rotation. Located at the intersection with the rotation center axis of the machine, the spherical radius of the first spherical area is R0, and the distance between the second virtual extension surface extending the second outer peripheral surface upstream and the spherical center is R2. Then, the first spherical region is formed so as to satisfy R0 ⁇ R2.
- the rotating shaft of the variable blade is in front of the center of the code line of the variable blade.
- the distance Dh1 between the upstream end of the first blade-facing surface and the rotation center axis of the rotating machine is located on the edge side, and the distance Dh2 between the downstream end of the first blade-facing surface and the rotation center axis of the rotating machine is
- the distance L1 between the upstream end of the first blade-facing surface and the rotating shaft of the variable blade is smaller than the distance L2 between the downstream end of the first blade-facing surface and the rotating shaft of the variable blade.
- the upstream end of the first blade-facing surface including the first spherical region and the apex of the first spherical region (existing on the first spherical region and the hub diameter from the hub central axis). It is the point farthest in the direction, and the axial distance and the radial distance between the first spherical region and the intersection of the rotation axis) can be reduced. Therefore, the axial size of the rotary machine can be made compact, and the wasteful space on the blade leading edge side can be reduced to suppress the recirculation flow near the first blade facing surface.
- region vertex can be suppressed, and the influence which a 1st blade facing surface exerts on the smooth flow of the fluid along a 1st outer peripheral surface can be reduced effectively.
- the distance L3 in the axial direction of the hub between the downstream end of the first outer peripheral surface of the hub and the rotation shaft of the variable blade is The distance L4 in the axial direction of the hub between the upstream end of the second outer peripheral surface of the hub and the rotating shaft of the variable blade is smaller.
- the axial size of the rotating machine can be made compact, and the wasteful space on the blade leading edge side can be reduced to suppress the recirculation flow in the vicinity of the first blade facing surface. it can.
- variable blade in the rotating machine described in any one of (1) to (7) above, is a spherical tip side that protrudes radially outward of the hub.
- a blade-facing casing portion including a second blade-facing surface that includes an end surface, and wherein the casing has a spherical second spherical region that is concave on the radially outer side of the hub while facing the tip-side end surface of the variable blade.
- An upstream casing portion having a first inner peripheral surface that is provided upstream of the blade-facing casing portion in the axial direction of the hub and is adjacent to the second blade-facing surface in the axial direction;
- a downstream casing portion provided on the downstream side of the blade-facing casing portion and having a second inner peripheral surface adjacent to the second blade-facing surface in the axial direction, and the rotating shaft of the variable blade is Cordula of the variable wing
- the distance Dt1 between the upstream end of the second blade facing surface and the rotation center axis of the rotary machine is located on the leading edge side of the center of the second blade.
- the distance Dt1 between the downstream end of the second blade facing surface and the rotation center of the rotary machine The distance L5 between the upstream end of the second blade facing surface and the rotating shaft of the variable blade is greater than the distance Dt2 from the shaft, and the distance L5 between the downstream end of the second blade facing surface and the rotating shaft of the variable blade Is smaller than the distance L6.
- the upstream end of the second blade-facing surface including the second spherical region and the apex of the second spherical region (existing on the second spherical region and in the hub radial direction from the hub central axis) It is possible to reduce the axial distance and the radial distance between the second spherical region and the rotation axis). Therefore, the axial size of the rotary machine can be made compact, and the wasteful space on the blade leading edge side can be reduced to suppress the recirculation flow near the second blade facing surface.
- the distance L7 between the downstream end of the first inner peripheral surface of the casing and the rotation shaft of the variable blade is the first of the casing. 2
- the distance L8 in the axial direction of the hub between the upstream end of the inner peripheral surface and the rotation shaft of the variable blade is smaller.
- the axial size of the rotating machine can be reduced, or the useless space on the blade leading edge side can be reduced to suppress the recirculation flow near the second blade facing surface. it can.
- a rotating machine is configured to cover a hub configured to rotate around a rotation center axis, and to form a fluid flow path between the hub and the hub.
- a rotating machine including a casing and a variable wing disposed on the fluid flow path and configured to be rotatable about a rotation axis along a radial direction of the hub.
- a spherical tip-side end surface that protrudes radially outward of the hub; and the casing faces the tip-side end surface of the variable wing and is concave on the radially outer side of the hub.
- a blade-facing casing portion including a second blade-facing surface having a region; and a first inner portion provided upstream of the blade-facing casing portion in the axial direction of the hub and adjacent to the second blade-facing surface in the axial direction.
- Upstream side with circumferential surface A downstream casing portion having a second inner peripheral surface that is provided on the downstream side of the blade-facing casing portion in the axial direction and is adjacent to the second blade-facing surface in the axial direction,
- the rotation axis of the variable wing is located on the leading edge side of the center of the code line of the variable wing, and the distance Dt1 between the upstream end of the second blade facing surface and the rotation center axis of the rotary machine is the second
- the distance L5 between the downstream end of the blade-facing surface and the rotation center axis of the rotary machine is larger than the distance Dt2, and the distance L5 between the upstream end of the second blade-facing surface and the rotating shaft of the variable blade is It is smaller than the distance L6 between the
- the upstream end of the second blade facing surface including the second spherical region and the apex of the second spherical region (existing on the second spherical region and in the hub radial direction from the hub central axis) It is possible to reduce the axial distance and the radial distance between the second spherical region and the rotation axis). Therefore, the axial size of the rotary machine can be made compact, and the wasteful space on the blade leading edge side can be reduced to suppress the recirculation flow near the second blade facing surface.
- the distance L7 between the downstream end of the first inner peripheral surface of the casing and the rotation shaft of the variable blade is the first of the casing. 2
- the distance L8 in the axial direction of the hub between the upstream end of the inner peripheral surface and the rotation shaft of the variable blade is smaller.
- the axial size of the rotating machine can be made compact, and the wasteful space on the blade leading edge side can be reduced to suppress the recirculation flow near the second blade facing surface. it can.
- a rotary machine including variable blades configured to be rotatable around a rotation axis along a radial direction of a hub, clearance loss is reduced and performance degradation is suppressed. it can.
- FIG. 1 is a cross-sectional view showing a schematic configuration of an axial compressor 100 as a rotating machine according to some embodiments.
- An axial flow compressor 100 shown in FIG. 1 is configured to cover a hub 2 that is configured to rotate around a rotation center axis O ⁇ b> 1 and a casing that forms a fluid flow path 4 between the hub 2 and the hub 2. 6, a moving blade 8 fixed to the hub 2, and a stationary blade 10 fixed to the casing 6.
- the moving blade 8 is disposed on the fluid flow path 4 and is configured to be rotatable around a rotation axis O2 along the radial direction of the hub 2.
- a plurality of moving blades 8 arranged in the circumferential direction at one axial position of the rotation center axis O1 constitute one moving blade row, and the plurality of moving blade rows are in the axial direction of the rotation center axis O1 (hereinafter, referred to as “rotation center axis O1”). (It is described as the axial direction of the hub 2).
- the stationary blade 10 is disposed on the fluid flow path 4 and is configured to be rotatable around a rotation axis O ⁇ b> 3 along the radial direction of the hub 2.
- a plurality of stationary blades 10 arranged in the circumferential direction at one position in the axial direction of the hub 2 constitute one stationary blade row, and the moving blade rows and the stationary blade rows are alternately arranged in the axial direction of the hub 2. ing.
- FIG. 2 is a schematic meridional sectional view showing a part of the axial flow compressor 100 according to an embodiment.
- FIG. 3 is a schematic meridional sectional view showing a part of the axial flow compressor 100 according to the embodiment.
- FIG. 4 is a schematic meridional sectional view showing a part of the axial flow compressor 100 according to the embodiment.
- FIG. 5 is a schematic meridional sectional view showing a part of the axial flow compressor 100 according to the embodiment.
- FIG. 6 is a schematic meridional sectional view showing a part of the axial flow compressor 100 according to the embodiment.
- FIG. 7 is a schematic meridian cross-sectional view showing a part of the axial flow compressor 100 according to an embodiment.
- FIG. 8 is a schematic meridian cross-sectional view showing a part of the axial flow compressor 100 according to one embodiment.
- FIG. 9 is a schematic meridian cross-sectional view showing a part of the axial flow compressor 100 according to an embodiment
- the moving blade 8 includes a spherical hub side end surface 12 that is concave outward in the radial direction of the hub 2.
- the hub 2 includes a blade-facing hub portion 16 facing the hub-side end surface 12 of the moving blade 8, an upstream-side hub portion 20 provided upstream of the blade-facing hub portion 16 in the axial direction of the hub 2, and the hub 2.
- a downstream hub portion 32 provided on the downstream side of the blade-facing hub portion 16 in the axial direction.
- the blade-facing hub portion 16 includes a first blade-facing surface 14 that has a spherical first spherical region 15 that faces the hub-side end surface 12 of the moving blade 8 and is convex outward in the radial direction of the hub 2.
- the upstream hub portion 20 has a first outer peripheral surface 18 adjacent to the first blade opposing surface 14 in the axial direction of the hub 2, and the downstream hub portion 32 is the first blade opposing surface 14 in the axial direction of the hub 2.
- the spherical center O4 of the first spherical area 15 is located at the intersection of the rotational axis O2 of the moving blade 8 and the rotational center axis O1 of the rotating machine.
- wing opposing hub part 16, and the downstream side hub part 32 may be comprised integrally (it is one member), and each is comprised separately (it is another member). May be.
- at least one of the upstream hub portion 20, the blade-facing hub portion 16 and the downstream hub portion 32 may be constituted by a plurality of members. For example, as shown in FIG. It may be formed of these members.
- the hub-side end surface 12 of the moving blade 8 is formed into a spherical shape and the first blade-facing surface 14 has the first spherical region 15, so the moving blade Even if 8 is turned to the close side, the clearance between the hub-side end surface 12 of the moving blade 8 and the first blade-facing surface 14 of the hub 2 does not basically increase. For this reason, clearance loss can be reduced.
- downstream end 18 a of the first outer peripheral surface 18 is more of the hub 2 than the upstream end 14 a of the first blade facing surface 14. Located outside in the radial direction.
- the first blade-facing surface 14 can be formed.
- the spherical radius of the first spherical region 15 is R0 and the distance between the first virtual extension surface 180 and the spherical center O4 is R1, R0 ⁇ A first spherical region 15 is formed so as to satisfy R1. Further, as shown in FIG.
- the upstream end 34 a of the second outer circumferential surface 34 is more of the hub 2 than the downstream end 14 b of the first blade facing surface 14. Located outside in the radial direction.
- the second outer peripheral surface 34 is not protruded radially outward of the hub 2 with respect to the second virtual extension surface 340 extending upstream. It is possible to form the first blade-facing surface 14.
- the spherical radius of the first spherical region 15 is R0 and the distance between the second virtual extension surface 340 and the spherical center is R2, R0 ⁇ R2 is satisfied.
- a first spherical region 15 is formed so as to satisfy. As shown in FIG.
- the first outer peripheral surface 18 and the second outer periphery so that the first virtual extension surface 180 and the second virtual extension surface 340 coincide with each other.
- a surface 34 may be formed.
- the first virtual extension surface 180 and the second virtual extension surface 340 may be shifted. In the latter case, from the viewpoint of reducing the influence of the first blade-facing surface 14 on the mainstream smooth flow, both the first virtual extension surface 180 and the second virtual extension surface 340 are provided as shown in FIG.
- it is desirable to form the first blade facing surface 14 so as not to protrude outward in the radial direction of the hub 2.
- the first spherical region 15 is formed so as to satisfy both R0 ⁇ R1 and R0 ⁇ R2.
- the spherical radius R 0 of the first spherical area 15 is set with an emphasis on the second virtual extension plane 340 rather than the first virtual extension plane 180. It is desirable to do.
- the rotation axis O ⁇ b> 2 of the moving blade 8 is located closer to the leading edge 40 than the center O ⁇ b> 5 of the code line of the moving blade 8.
- the distance Dh1 between the upstream end 14a of the first blade facing surface 14 and the rotation center axis O1 of the axial flow compressor 100 is equal to the downstream end 14b of the first blade facing surface 14 and the axial flow compressor.
- the distance L1 between the upstream end 14a of the first blade-facing surface 14 and the rotational axis O2 of the blade 8 is equal to the distance Dh2 between the rotation center axis O1 of 100 and the downstream end 14b of the first blade-facing surface 14.
- the rotation axis O ⁇ b> 2 of the moving blade 8 is located on the leading edge 40 side with respect to the center O ⁇ b> 5 of the code line of the moving blade 8, and the upstream end of the first blade facing surface 14.
- the distance Dh1 between 14a and the rotation center axis O1 of the axial flow compressor 100 is larger than the distance Dh2 between the downstream end 14b of the first blade facing surface 14 and the rotation center axis O1 of the axial flow compressor 100, and the first blade
- the distance L1 between the upstream end 14a of the facing surface 14 and the rotation axis O2 of the moving blade 8 is smaller than the distance L2 between the downstream end 14b of the first blade facing surface 14 and the rotation axis O2 of the moving blade 8.
- the upstream end 14a of the first blade facing surface 14 including the first spherical region 15 and the apex 15a of the first spherical region 15 (existing on the first spherical region 15 from the rotation center axis O1 to the hub 2). It is the point farthest away in the radial direction, and the axial distance and the radial distance between the first spherical region 15 and the intersection of the rotation axis O2) can be reduced. Accordingly, the axial size of the axial flow compressor 100 is reduced, or the useless space U1 on the leading edge 40 side of the moving blade 8 is reduced to reduce the recirculation flow in the vicinity of the first blade facing surface 14 (see FIG. 8). Can be suppressed.
- the amount of protrusion of the first spherical surface vertex 15a in the radial direction of the hub 2 from the first outer peripheral surface 18 is suppressed, and the first blade-facing surface 14 is in a smooth flow F of fluid along the first outer peripheral surface 18.
- the influence exerted can be reduced effectively.
- the distance L3 in the axial direction of the hub 2 between the downstream end 18a of the first outer peripheral surface 18 of the hub 2 and the rotational axis O2 of the moving blade 8 is The distance L4 in the axial direction of the hub 2 between the upstream end 34a of the second outer peripheral surface 34 and the rotational axis O2 of the rotor blade 8 is smaller than the distance L4.
- the axial size of the axial flow compressor 100 is reduced, or the useless space U1 on the front edge 40 side of the moving blade 8 is reduced to reduce the recirculation flow in the vicinity of the first blade facing surface 14 (see FIG. 8) can be suppressed. Further, the fluid flowing through the fluid flow path 4 is less likely to flow into the clearance between the hub-side end surface 12 of the moving blade 8 and the first blade-facing surface 14 of the hub 2 through the space U1. Thereby, the efficiency fall of the axial flow compressor 100 can be suppressed.
- the moving blade 8 includes a spherical tip-side end surface 22 that is convex outward in the radial direction of the hub 2.
- the casing 6 includes a blade-facing casing portion 26 facing the tip-side end surface 22 of the rotor blade 8, an upstream casing portion 30 provided upstream of the blade-facing casing portion 26 in the axial direction of the hub 2, and the hub 2. And a downstream casing portion 36 provided on the downstream side of the blade-facing casing portion 26 in the axial direction.
- the blade-facing casing portion 26 includes a second blade-facing surface 24 that has a spherical second spherical region 25 that is opposed to the tip-side end surface 22 of the moving blade 8 and that is recessed radially outward of the hub 2.
- the upstream casing portion 30 has a first inner peripheral surface 28 adjacent to the second blade facing surface 24 in the axial direction of the hub 2, and the downstream casing portion 36 is a second blade facing surface in the axial direction of the hub 2.
- 24 has a second inner peripheral surface 38 adjacent to the second inner peripheral surface 38.
- the upstream casing part 30, the blade-facing casing part 26, and the downstream casing part 36 may be configured integrally (with one member), or may be configured separately (with different members). May be.
- at least one of the upstream casing part 30, the blade facing casing part 26, and the downstream casing part 36 may be constituted by a plurality of members. For example, as shown in FIG. It may be formed of these members.
- the tip side end surface 22 of the moving blade 8 is formed in a spherical shape and the second blade facing surface 24 has the second spherical region 25.
- the tip side end face 22 of the moving blade 8 and the second blade facing surface 24 of the casing 6 even if the blade 8 is rotated to the open side (the direction in which the angle formed by the cord line of the moving blade 8 and the axial direction of the hub 2 decreases). And the clearance with does not basically expand. For this reason, clearance loss can be reduced.
- the rotation axis O ⁇ b> 2 of the moving blade 8 is located on the leading edge 40 side with respect to the center O ⁇ b> 5 of the code line of the moving blade 8, and the second blade facing surface 24.
- the distance Dt1 between the upstream end 24a of the axial flow compressor 100 and the rotation center axis O1 of the axial flow compressor 100 is equal to the distance Dt2 between the downstream end 24b of the second blade-facing surface 24 and the rotation center axis O1 of the axial flow compressor 100.
- a distance L5 between the upstream end 24a of the two blade facing surface 24 and the rotation axis O2 of the moving blade 8 is equal to a distance L6 between the downstream end 24b of the second blade facing surface 24 and the rotation axis O2 of the moving blade 8.
- the rotation axis O ⁇ b> 2 of the moving blade 8 is located on the leading edge 40 side with respect to the center O ⁇ b> 5 of the code line of the moving blade 8, and the upstream end of the second blade facing surface 24.
- the distance Dt1 between 24a and the rotation center axis O1 of the axial flow compressor 100 is larger than the distance Dt2 between the downstream end 24b of the second blade facing surface 24 and the rotation center axis O1 of the axial flow compressor 100, and the second blade A distance L5 between the upstream end 24a of the facing surface 24 and the rotation axis O2 of the moving blade 8 is smaller than a distance L6 between the downstream end 24b of the second blade facing surface 24 and the rotation axis O2 of the moving blade 8.
- the upstream end 24a of the second blade facing surface 24 including the second spherical region 25 and the apex 25a of the second spherical region 25 (existing on the second spherical region 25 from the rotation center axis O1 to the hub 2 It is the point farthest in the radial direction, and the axial distance and the radial distance between the second spherical region 25 and the intersection of the rotation axis O2) can be reduced. Accordingly, the axial size of the axial flow compressor 100 is reduced, or the useless space U2 on the leading edge 40 side of the moving blade 8 is reduced to reduce the recirculation flow in the vicinity of the second blade facing surface 24 (see FIG. 8). Can be suppressed.
- the distance L7 between the downstream end 28a of the first inner peripheral surface 28 of the casing 6 and the rotational axis O2 of the rotor blade 8 is the second inner peripheral surface of the casing.
- the distance L8 in the axial direction of the hub 2 between the upstream end 38a of the blade 38 and the rotational axis O2 of the rotor blade 8 is smaller than the distance L8.
- the axial size of the axial flow compressor 100 is reduced, or the useless space U2 on the front edge 40 side of the moving blade 8 is reduced to reduce the recirculation flow in the vicinity of the second blade facing surface 24 (see FIG. 8) can be suppressed. Further, since the fluid entering the space U2 from the main flow portion of the fluid flow path 4 is reduced, the leakage flow at the clearance between the tip end surface 22 of the moving blade 8 and the second blade facing surface 24 of the casing 6 can be suppressed. . Thereby, the efficiency fall of the axial flow compressor 100 can be suppressed.
- the present invention is not limited to the above-described embodiments, and includes forms obtained by modifying the above-described embodiments and forms obtained by appropriately combining these forms.
- the relationship between the shape of the fluid flow path 4 formed by the hub 2 and the casing 6 and the shape of the moving blade 8 has been described. This can also be applied to the relationship between the shape of and the shape of the stationary blade 10.
- the present invention can be applied to rotating machines such as a boiler axial flow fan, a blast furnace axial flow blower, a gas turbine compressor, and various turbines.
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Abstract
Description
また、上記(1)に記載の回転機械において上記条件(a)を満たす場合には、上記条件(a)を満たさない場合と比較して、第1外周面を下流側に延長した仮想延長面に対するハブの径方向外側への突出量が小さくなるように第1翼対向面を形成することが可能となる。あるいは、該仮想延長面に対してハブの径方向外側に突出しないように第1翼対向面を形成することも可能となる。このように、第1外周面に沿った流体のスムーズな流れを妨げないよう第1翼対向面を形成することが可能となるため、二次流れの発生を抑制し、回転機械の性能低下を抑制することが容易となる。
一方、上記(1)に記載の回転機械において上記条件(b)を満たす場合には、上記条件(a)を満たさない場合と比較して、第2外周面を上流側に延長した仮想延長面に対するハブの径方向外側への突出量が小さくなるように第1翼対向面を形成することが可能となる。あるいは、該仮想延長面に対してハブの径方向外側に突出しないように第1翼対向面を形成することも可能となる。このように、球面領域の後方での剥離現象を抑制するよう第1翼対向面を形成することが可能となるため、回転機械の性能低下を抑制することが容易となる。
したがって、上記(1)に記載の回転機械によれば、上記条件(a)と上記条件(b)の少なくとも一方を満たすことにより、回転機械の性能低下を抑制することが容易となる。
例えば、「ある方向に」、「ある方向に沿って」、「平行」、「直交」、「中心」、「同心」或いは「同軸」「一致」等の相対的な配置関係を表す表現は、厳密にそのような相対的配置関係を表すのみならず、公差、若しくは、同じ機能が得られる程度の角度や距離をもって相対的に変位している状態も表すものとする。
また、一の構成要素を「備える」、「具える」、「具備する」、「含む」、又は、「有する」という表現は、他の構成要素の存在を除外する排他的な表現ではない。
例えば、上述した幾つかの実施形態では、ハブ2及びケーシング6によって形成される流体流路4の形状と動翼8の形状の関係について説明したが、これらの関係については、該流体流路4の形状と静翼10の形状との関係にも適用することができる。
また、本発明は、例えばボイラ用軸流ファン、高炉用軸流ブロワ、ガスタービン圧縮機及び各種タービン等の回転機械に適用することができる。
4 流体流路
6 ケーシング
7 入口
8 動翼
9 出口
10 静翼
12 ハブ側端面
14 第1翼対向面
14a 第1翼対向面の上流端
15 第1球面領域
16 翼対向ハブ部
18 第1外周面
18a 第1外周面の下流端
20 上流側ハブ部
22 チップ側端面
24 第2翼対向面
24a 第2翼対向面の上流端
25 第2球面領域
26 翼対向ケーシング部
28 第1内周面
28a 第1内周面の下流端
30 上流側ケーシング部
32 下流側ハブ部
34 第2外周面
34a 第2外周面の上流端
36 下流側ケーシング部
38 第2内周面
38a 第2内周面の上流端
40 前縁
100 軸流圧縮機
180 第1仮想延長面
340 第2仮想延長面
Claims (11)
- 回転中心軸周りに回転するように構成されたハブと、
前記ハブを覆うよう構成され、前記ハブとの間に流体流路を形成するケーシングと、
前記流体流路上に配置され、前記ハブの径方向に沿った回動軸周りに回動可能に構成された可変翼と、を備える回転機械であって、
前記可変翼は、前記ハブの径方向外側に凹である球面状のハブ側端面を含み、
前記ハブは、
前記可変翼の前記ハブ側端面に対向するとともに前記ハブの径方向外側に凸である球面状の第1球面領域を有する第1翼対向面を含む翼対向ハブ部と、
前記ハブの軸方向において前記翼対向ハブ部の上流側に設けられ、前記軸方向において前記第1翼対向面に隣接する第1外周面を有する上流側ハブ部と、
前記軸方向において前記翼対向ハブ部の下流側に設けられ、前記軸方向において前記第1翼対向面に隣接する第2外周面を有する下流側ハブ部と、
を含み、
以下の条件(a)と条件(b)の少なくとも一方を満たす回転機械。
(a)前記第1外周面の下流端は、前記第1翼対向面の上流端よりも前記ハブの径方向において外側に位置する。
(b)前記第2外周面の上流端は、前記第1翼対向面の下流端よりも前記ハブの径方向において外側に位置する。 - 前記回転機械は少なくとも前記条件(a)を満たし、
前記第1翼対向面は、前記第1外周面を下流側に延長した第1仮想延長面よりも前記ハブの径方向において外側に突出しないよう形成されている請求項1に記載の回転機械。 - 前記回転機械は少なくとも前記条件(b)を満たし、
前記第1翼対向面は、前記第2外周面を上流側に延長した第2仮想延長面よりも前記ハブの径方向において外側に突出しないよう形成されている請求項1又は2に記載の回転機械。 - 前記第1球面領域の球面中心は、前記可変翼の回動軸と前記回転機械の回転中心軸との交点に位置し、
前記第1球面領域の球面半径をR0とし、前記第1外周面を下流側に延長した第1仮想延長面と前記球面中心との距離をR1とすると、
前記第1球面領域は、R0≦R1を満たすよう形成されている請求項1乃至3の何れか1項に記載の回転機械。 - 前記第1球面領域の球面中心は、前記可変翼の回動軸と前記回転機械の回転中心軸との交点に位置し、
前記第1球面領域の球面半径をR0とし、前記第2外周面を上流側に延長した第2仮想延長面と前記球面中心との距離をR2とすると、
前記第1球面領域は、R0≦R2を満たすよう形成されている請求項1乃至4の何れか1項に記載の回転機械。 - 前記可変翼の回動軸は、前記可変翼のコードラインの中心よりも前縁側に位置し、
前記第1翼対向面の上流端と前記回転機械の回転中心軸との距離Dh1は、前記第1翼対向面の下流端と前記回転機械の回転中心軸との距離Dh2よりも大きく、
前記第1翼対向面の上流端と前記可変翼の回動軸との距離L1は、前記第1翼対向面の下流端と前記可変翼の回動軸との距離L2よりも小さい請求項1乃至5の何れか1項に記載の回転機械。 - 前記ハブの第1外周面の下流端と前記可変翼の回動軸との前記ハブの軸方向における距離L3は、前記ハブの第2外周面の上流端と前記可変翼の回動軸との前記ハブの軸方向における距離L4よりも小さい請求項6に記載の回転機械。
- 前記可変翼は、前記ハブの径方向外側に凸である球面状のチップ側端面を含み、
前記ケーシングは、
前記可変翼の前記チップ側端面に対向するとともに前記ハブの径方向外側に凹である球面状の第2球面領域を有する第2翼対向面を含む翼対向ケーシング部と、
前記ハブの軸方向において前記翼対向ケーシング部の上流側に設けられ、前記軸方向において前記第2翼対向面に隣接する第1内周面を有する上流側ケーシング部と、
前記軸方向において前記翼対向ケーシング部の下流側に設けられ、前記軸方向において前記第2翼対向面に隣接する第2内周面を有する下流側ケーシング部と、
を含み、
前記可変翼の回動軸は、前記可変翼のコードラインの中心よりも前縁側に位置し、
前記第2翼対向面の上流端と前記回転機械の回転中心軸との距離Dt1は、前記第2翼対向面の下流端と前記回転機械の回転中心軸との距離Dt2よりも大きく、
前記第2翼対向面の上流端と前記可変翼の回動軸との距離L5は、前記第2翼対向面の下流端と前記可変翼の回動軸との距離L6よりも小さい請求項1乃至7の何れか1項に記載の回転機械。 - 前記ケーシングの第1内周面の下流端と前記可変翼の回動軸との距離L7は、前記ケーシングの第2内周面の上流端と前記可変翼の回動軸との前記ハブの軸方向における距離L8よりも小さい請求項8に記載の回転機械。
- 回転中心軸周りに回転するように構成されたハブと、
前記ハブを覆うよう構成され、前記ハブとの間に流体流路を形成するケーシングと、
前記流体流路上に配置され、前記ハブの径方向に沿った回動軸周りに回動可能に構成された可変翼と、を備える回転機械であって、
前記可変翼は、前記ハブの径方向外側に凸である球面状のチップ側端面を含み、
前記ケーシングは、
前記可変翼の前記チップ側端面に対向するとともに前記ハブの径方向外側に凹である球面状の第2球面領域を有する第2翼対向面を含む翼対向ケーシング部と、
前記ハブの軸方向において前記翼対向ケーシング部の上流側に設けられ、前記軸方向において前記第2翼対向面に隣接する第1内周面を有する上流側ケーシング部と、
前記軸方向において前記翼対向ケーシング部の下流側に設けられ、前記軸方向において前記第2翼対向面に隣接する第2内周面を有する下流側ケーシング部と、
を含み、
前記可変翼の回動軸は、前記可変翼のコードラインの中心よりも前縁側に位置し、
前記第2翼対向面の上流端と前記回転機械の回転中心軸との距離Dt1は、前記第2翼対向面の下流端と前記回転機械の回転中心軸との距離Dt2よりも大きく、
前記第2翼対向面の上流端と前記可変翼の回動軸との距離L5は、前記第2翼対向面の下流端と前記可変翼の回動軸との距離L6よりも小さい回転機械。 - 前記ケーシングの第1内周面の下流端と前記可変翼の回動軸との距離L7は、前記ケーシングの第2内周面の上流端と前記可変翼の回動軸との前記ハブの軸方向における距離L8よりも小さい請求項10に記載の回転機械。
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JPH0726904A (ja) * | 1993-07-12 | 1995-01-27 | Ishikawajima Harima Heavy Ind Co Ltd | 回転機械装置の翼端部構造 |
JP2000356198A (ja) * | 1999-06-11 | 2000-12-26 | Mitsubishi Heavy Ind Ltd | 軸流送風機用動翼 |
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DE202010017911U1 (de) * | 2010-10-30 | 2013-02-11 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Axialturbomaschine |
JP2012211527A (ja) * | 2011-03-30 | 2012-11-01 | Mitsubishi Heavy Ind Ltd | ガスタービン |
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JPS53162407U (ja) * | 1977-05-27 | 1978-12-19 | ||
JPS5973600U (ja) * | 1982-11-10 | 1984-05-18 | 株式会社日立製作所 | 可変静翼の駆動機構 |
JPH0726904A (ja) * | 1993-07-12 | 1995-01-27 | Ishikawajima Harima Heavy Ind Co Ltd | 回転機械装置の翼端部構造 |
JP2000356198A (ja) * | 1999-06-11 | 2000-12-26 | Mitsubishi Heavy Ind Ltd | 軸流送風機用動翼 |
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