WO2008053635A1 - Profil aérodynamique transsonique et machine rotative à écoulement axial - Google Patents
Profil aérodynamique transsonique et machine rotative à écoulement axial Download PDFInfo
- Publication number
- WO2008053635A1 WO2008053635A1 PCT/JP2007/067645 JP2007067645W WO2008053635A1 WO 2008053635 A1 WO2008053635 A1 WO 2008053635A1 JP 2007067645 W JP2007067645 W JP 2007067645W WO 2008053635 A1 WO2008053635 A1 WO 2008053635A1
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- WIPO (PCT)
- Prior art keywords
- transonic
- blade
- cross
- sectional profile
- tip
- Prior art date
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Classifications
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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
- F04D29/324—Blades
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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
- F04D29/38—Blades
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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
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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
- F04D21/00—Pump involving supersonic speed of pumped fluids
-
- 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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
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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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
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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
- F05D2250/70—Shape
- F05D2250/71—Shape curved
- F05D2250/713—Shape curved inflexed
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the present invention relates to a transonic blade operating in a transonic or supersonic flow region, and an axial-flow rotating machine such as a turbine equipped with this transonic blade, and in particular, a transonic blade having a three-dimensional shape. And an axial-flow rotating machine including this transonic blade.
- the losses that occur in blade cascades can be broadly categorized, and the profile loss caused by the blade shape itself and the fluid flowing between the cascades.
- secondary loss due to As a blade that reduces secondary loss a moving blade that suppresses the secondary flow in the solid wall boundary layer on the blade surface by placing the high position of the leading edge in the axial direction from the low position is proposed.
- the axial direction represents the axial direction of the rotor around which the blades are installed
- the radial direction represents the radial direction of the rotor.
- the loss of profile loss is reduced by configuring a three-dimensional wing.
- some moving blades are provided with transonic blades that operate by the inflow of a transonic or supersonic differential fluid.
- a shock wave is generated due to the compressibility of the differential fluid, resulting in the above-mentioned profile loss and secondary loss.
- Various losses occur. That is, the loss due to the shock wave itself, the loss due to the interference between the shock wave and the solid wall boundary layer, and the shock wave and tip talance leakage flow (leakage flow ejected from the gap between the blade tip and the casing due to the pressure difference between the blade back and the wing) Loss due to interference.
- each loss due to these shock waves is shown in FIG. 16 because a strong shock wave is generated on the tip (blade tip) 101 side of blade 100 as shown in the blade surface static pressure distribution in FIG. As shown in the efficiency distribution in the circumferential direction (blade height direction), the efficiency on the tip side becomes low. Furthermore, as shown in FIG. 17, the flow force decelerated by the separation shock wave 110, which is a kind of shock wave. For the leading edge 102 of the wing 100, the incidence (the difference between the inlet angle and the angle of the leading edge of the wing) increases. When this incident increases, the pressure loss increases, and the efficiency of the axial-flow rotating machine decreases accordingly.
- the moving blades in Patent Document 1 are particularly effective in suppressing the radial shock waves of the blades and the solid walls in order to suppress loss due to interference between the shock waves and the solid wall boundary layer.
- the position of the interference point with the boundary layer is designed so that the higher the radial height, the more upstream the axial direction. That is, as a whole, the shape is inclined forward to the upstream side so that the position of the leading edge force radial direction in the moving blade cross section is higher in the axial direction. This suppresses the secondary flow of the solid wall boundary layer, avoids the enlargement of the boundary layer before the interference with the shock wave, prevents peeling, and reduces the loss.
- Patent Document 1 JP-A-7-224794
- the moving blade of Patent Document 1 is configured to have a forward leaning posture on the upstream side, and thus, as described above, the interference between the secondary flow and the shock wave due to the tip leakage flow occurs. Mitigated and reduced loss on the chip side is observed. This forces the flow to the tip side, and the force that can improve the efficiency on the tip side. Conversely, the boundary layer on the hub (root) side becomes thick and the flow becomes unstable. The efficiency on the side will deteriorate.
- the present invention suppresses a decrease in efficiency due to a shock wave on the tip side, and avoids enlargement of the boundary layer on the hub side and prevents the transonic blade and shaft to prevent separation.
- An object is to provide a flow rotating machine.
- the transonic blade of the present invention is a transonic blade that operates in a flow region with a working fluid of transonic speed or higher, the hub on the connection position side with the rotating shaft,
- the mean which is the center position in the height direction that is the radial direction of the rotating shaft, the tip that is the tip of the position farthest from the rotating shaft in the height direction, and the upstream of the working fluid that flows in An edge and a trailing edge located downstream of the working fluid, and each cross-sectional profile in the height direction of the blade is connected in parallel to a first direction connecting the leading edge and the trailing edge.
- the cross-sectional profile on the tip side and the cross-sectional profile between the mean and the hub are protruded upstream in the first direction to form an s-shape, and the tip side
- the transition amount in the first direction of the cross-sectional profile is larger than the transition amount in the first direction of the cross-sectional profile between the mean and the hub.
- the tip side in the first direction, the tip side is inclined to the upstream side, and the forward sweep shape in which the tip side is inclined to the upstream side, and the portion between the mean and the hub in the first direction is on the upstream side.
- the S-shape is combined with the protruding backward sweep shape, and the tip side protrudes to the most upstream side.
- each cross-sectional profile in the height direction of the blade may be continuously shifted also in the second direction perpendicular to the first direction. That is, in the second direction
- the tip side is inclined to the upstream side, and / or a forward lean shape may be combined, and the backward lean in which the portion between the mean and the hub protrudes upstream in the second direction. It does not matter even if the shape is a combination of shapes
- the cross-sectional angle between the first direction and the axial direction of the rotary shaft in each cross-sectional profile in the height direction of the blade may be a three-dimensional blade shape that continuously changes.
- An axial-flow rotating machine of the present invention includes a rotating shaft that is positioned at the center and rotates, and a plurality of motions that are installed on the outer circumferential surface of the rotating shaft at equal intervals in the outer circumferential direction and the axial direction of the rotating shaft.
- a shaft provided with a blade, a casing covering the rotating shaft and the moving blade, and a plurality of stationary blades alternately disposed on the inner peripheral surface of the casing in the axial direction of the moving blade and the rotating shaft
- a rotary rotator comprising any one of the above-mentioned transonic blades as a part of the plurality of moving blades.
- the boundary side on the hub side is thinned by forming an S shape in which the tip side and the portion between the hub and the mean protrude to the upstream side, so that the separation resistance on the hub side is reduced.
- the chip side boundary layer can be thickened to reduce chip leakage loss.
- shock waves can be weakened and various losses due to shock waves can be suppressed. By reducing these losses, the blade rotation Energy can be efficiently transmitted to the fluid.
- FIG. 1 is a schematic configuration diagram of a gas turbine.
- FIG. 2 is a diagram showing a cross-sectional profile of a transonic blade.
- FIG. 3 is a cross-sectional view in the span direction showing the configuration of the transonic blade.
- FIG. 4A is a diagram for explaining the sweep direction, which is the transition direction of the center of gravity of the cross-sectional profile of the transonic blade.
- FIG. 4B is a diagram for explaining the lean direction, which is the transition direction of the center of gravity of the cross-sectional profile of the transonic blade.
- FIG. 5A is a diagram for explaining a basic configuration of the transonic wing of the present invention.
- FIG. 5B is a diagram for explaining the basic configuration of the transonic wing of the present invention.
- FIG. 5C is a diagram for explaining the basic configuration of the transonic wing of the present invention.
- FIG. 6 is a diagram showing the axial flow velocity distribution in the span direction for each of the transonic blades of FIGS. 5A to 5C.
- FIG. 7 is a diagram showing the efficiency distribution in the span direction for each of the transonic blades of FIG. 5A to FIG. 5C.
- FIG. 8 is a diagram showing a state of shock waves with respect to the transonic blade shown in FIG. 5B arranged in the circumferential direction of the rotor.
- FIG. 9 is a schematic perspective view showing the configuration of the transonic blade of the first embodiment.
- FIG. 10 is a diagram showing the transition in the sweep direction of each cross-sectional profile with respect to the span direction in the transonic blade of FIG.
- FIG. 11A is a top view seen from the tip side of the transonic blade as a reference shape.
- FIG. 11B is a top view of the transonic blade of FIG. 9 as seen from the tip side.
- FIG. 12A is a diagram showing a cross-sectional profile of each of the hub, the mean, and the tip in the transonic blade having a reference shape.
- FIG. 12B is a diagram showing cross-sectional profile files for the hub, mean, and tip in the transonic blade of FIG.
- FIG. 13A is a diagram showing a configuration of a transonic blade in which the position of the cross-sectional profile is changed in the lean direction.
- FIG. 13B is a diagram showing the configuration of a transonic wing in which the position of the cross-sectional profile is changed in the lean direction.
- FIG. 13C is a diagram showing a configuration of a transonic blade in which the position of the cross-sectional profile is changed in the lean direction.
- FIG. 14 is a diagram showing a transition in the lean direction of each cross-sectional profile with respect to the span direction in the transonic blade of the second embodiment.
- FIG. 15 is a diagram showing a blade surface static pressure distribution in a conventional blade.
- FIG. 16 is a diagram showing the efficiency distribution in the span direction in a conventional blade.
- FIG. 17 is a diagram showing a state of shock waves with respect to conventional blades arranged in the circumferential direction of the rotor. Explanation of symbols
- FIG. 1 shows a schematic diagram of the gas turbine.
- the gas turbine includes a compressor 1 that compresses air, a combustor 2 that is supplied with air and fuel compressed by the compressor 1 and performs a combustion operation, and a combustor 2. And a turbine 3 that is rotationally driven by the combustion gas from.
- the compressor 1, the combustor 2, and the turbine 3 are each covered with a casing 4, and the combustor 2 is equidistantly arranged on the outer periphery of the rotor 5 having the compressor 1 and the turbine 3 as one axis. Several are arranged.
- the air compressed by the compressor 1 is supplied to the combustor 2 and the rotor 5 through the inside of the passenger compartment 4.
- the compressed air supplied to the combustor 2 is used for combustion of fuel supplied to the combustor 2.
- the compressed air supplied into the turbine 4 and the rotor 5 on the turbine 3 side is fixed to the stationary blade 31 and the rotor 5 fixed to the casing 4 exposed to high temperature by the combustion gas from the combustor 2. Used for cooling the rotor blade 32.
- the stationary blades 31 and the moving blades 32 are alternately arranged in the axial direction of the rotor 5.
- combustion gas generated by the combustion operation in the combustor 2 is supplied to the turbine 3, and the combustion gas is blown to the moving blade 32 and rectified by the stationary blade 31, thereby rotating the turbine bin 3.
- the rotation drive of the turbine 3 is transmitted to the compressor 1 via the rotor 5 so that the compressor 1 is driven to rotate.
- the moving blade 12 fixed to the rotor 5 rotates, so that the air flowing in the space formed by the stationary blade 11 and the moving blade 12 fixed to the casing 4 is compressed.
- the stationary blades 11 and the moving blades 12 are alternately arranged in the axial direction of the rotor 5.
- the compressor 1 has a transonic speed, that is, a supersonic portion where the Mach number exceeds 1 in the working fluid (air) flowing into the moving blade. It is a transonic or supersonic compressor that is operated with a working fluid (air) at a speed higher than In the compressor 1 that is a transonic or supersonic compressor, a transonic blade is used as the moving blade 12.
- the transonic blade according to the present invention will be described.
- the side into which the working fluid (air) flows is referred to as “upstream side”
- the side from which the working fluid (air) flows out is referred to as “downstream side”.
- the radial direction of the rotor 5 in the gas turbine shown in FIG. 1, that is, the height direction of the transonic blade is defined as the “span direction”.
- the plane parallel to the flow of the working fluid in the axial direction of the rotor 5 is the “meridian plane”, and the cross-sectional shape of the transonic blade perpendicular to the radial direction of the rotor 5 is the “cross-sectional profile”.
- the accumulation of the cross-sectional profile in the span direction in the transonic blade is referred to as "stacking".
- the tip on the side where the working fluid (air) flows is the “leading edge” (reference numeral 121 in FIG. 2), and the working fluid (air) flows out.
- the leading edge of this is the “rear edge” (reference numeral 122 in FIG. 2), and the inclination direction of the straight line connecting the front and rear edges with respect to the five rotor axes is the “staggered direction” (arrow S in FIG. 2).
- the surface facing the upstream side of the rotor 5 in the axial direction is referred to as the “rear surface” (reference numeral 126 in FIG. 2), and the surface facing the downstream side in the axial direction of the rotor 5 is referred to as the “abdominal face” (reference numeral 127 in FIG. 2). ).
- the portion connected to the rotor 5 (80 to 100% height direction of the transonic blade 12;
- the tip part (123 in the height direction of the transonic blade 12) is the “tip” (reference number 124 in FIG. 3).
- the central position (position near 50% of the transonic blade 12 in the height direction) is the “mean” (reference numeral 125 in FIG. 3).
- this percentage display indicates each position in the radial direction of the rotor 5 (corresponding to the height direction of the transonic blade 12). It is expressed as a relative position of the height of.
- the tip farthest from the outer peripheral surface of the rotor 5 is 0%, and the connection position on the outer peripheral surface of the rotor 5 is 100%.
- transition direction (arrow P) is set as the “sweep direction”.
- the direction of transition (arrow Q) is the “lean direction”.
- FIGS. 5A to 5C show configurations of three types of transonic blades 12a to 12c that are continuously changed in the sweep direction from the hub 123 to the tip 124 in the span direction.
- the transonic blade 12a shown in FIG. 5A is configured such that the center of gravity G of each cross-sectional profile is parallel to the span direction from the hub 123 toward the tip 124. That is, the center of gravity G of each cross-sectional profile is aligned toward the rotor 5 radial direction, and the configuration shown in FIG. 5A is used as a reference.
- the shape like this transonic blade 12a will be referred to as “reference shape” in the following.
- the transonic blade 12b shown in FIG. 5B has a configuration in which the center of gravity G of each cross-sectional profile continuously transitions from the downstream side to the upstream side in the sweep direction from the hub 123 toward the tip 124. To do. That is, as compared with the transonic blade 12a in FIG. 5A, the configuration is inclined forward toward the upstream side (front edge 121 side) with respect to the radial direction of the rotor 5.
- the shape like this transonic blade 12b will be referred to as “forward sweep shape” in the following.
- the transonic blade 12c shown in FIG. 5C has a structure in which the center of gravity G of each cross-sectional profile file continuously transitions from the downstream side to the upstream side in the sweep direction from the tip 124 to the hub 123. And That is, as compared with the transonic blade 12a of FIG. 5A, the configuration in which the hub 123 side is inclined rearward with respect to the radial direction of the rotor 5 (rear edge 122 side) and the hub 123 side protrudes upstream (front edge 121 side). To do.
- the shape like this transonic wing 12c will be referred to as “backward sweep shape” in the following.
- the distribution of the axial velocity in the span direction is the curve X in FIG. 6;
- the distribution shapes are as shown below.
- the transition is compared with the curve XI for the transonic wing 12a.
- the curve Y1 for the sonic blade 12b the axial flow speed on the tip 124 side increases, and conversely, the axial flow speed on the hub 123 side decreases.
- the transonic wing 12c when comparing the transonic wing 12a with the reference shape in Fig. 5A and the transonic wing 12c with the backward sweep shape in Fig. 5C, compared to the curve XI for the transonic wing 12a, the transonic wing 12c On the other hand, in the curve Zl, the axial flow speed on the tip 124 side is slow, and conversely, the axial flow speed on the hub 123 side is fast.
- the distribution of the efficiency in the span direction (the energy efficiency at which the power for rotating the transonic blade is transmitted to the working fluid) is shown in the curve of FIG.
- the transonic blade is compared with the curve X2 for the transonic blade 12a.
- the efficiency on the tip 124 side is high, but the efficiency on the hub 123 side is low.
- the curve Z2 for the transonic wing 12c is compared to the curve X2 for the transonic wing 12a.
- the efficiency on the chip 124 side is deteriorated, the efficiency in the portion other than the vicinity of the chip 124 is maintained or improved.
- the blade height in the span direction is obtained by forming a forward sweep shape with the tip 124 side tilted forward as shown in the transonic blade 12b in Fig. 5B.
- the difference in static pressure between the back surface 126 and the abdominal surface 127 at the leading edge 121 becomes small.
- the transonic blade 12c in FIG. 5C by adopting a backward sweep shape in which the tip 124 side is tilted backward, the leading edge on the hub 123 side where the blade height in the span direction is 70% or less.
- the difference in static pressure between the back surface 126 and the abdominal surface 127 at 121 becomes smaller.
- the forward sweep shape as shown in FIG. 5B allows the working fluid (air) to flow on the tip 124 side, and the matching at the leading edge 121 is good. Furthermore, shock waves can be weakened. As a result, on the chip 124 side, loss due to the shock wave itself, loss due to interference between the shock wave and the solid wall boundary layer, and loss due to interference between the shock wave and the chip clearance leakage flow can be reduced.
- Air flows to make matching at the leading edge 121 other than the tip 124 good.
- Good matching means that the inflow angle of the working fluid to the blade is an appropriate value with respect to the blade metal angle, and the loss generated in the blade is at or near the minimum.
- the solid wall boundary layer on the hub 123 side can be made thinner and the peeling resistance can be enhanced. Therefore, the force S reduces the loss due to the interference between the shock wave on the hub 123 side and the solid wall boundary layer.
- FIG. 9 is a schematic perspective view showing the configuration of the transonic blade of the present embodiment.
- Figure 10 shows the It is a figure which shows the transition in the sweep direction of each cross-sectional profile with respect to the span direction from a hub to a chip.
- the transonic wing 12x of the present embodiment combines the forward sweep shape of the transonic wing 12b of Fig. 5B with the backward sweep shape of the transonic wing 12c of Fig. 5C.
- Shape That is, the transonic blade 12x shown in FIG. 9 has a shape in which the cross-sectional profile on the tip 124 side protrudes upstream in the sweep direction, similar to the forward sweep shape of the transonic blade 12b in FIG. 5B.
- the cross-sectional profile in the portion between the hub 123 and the mean; 125 is a shape protruding upstream in the sweep direction.
- the transonic blade 12x shown in FIG. 9 has an S-shaped configuration with respect to the span direction because each cross-sectional profile is adjusted in the sweep direction.
- Figure 10 shows the amount of position adjustment in the sweep direction that is continuously changed in the span direction.
- the transonic blade 12x shown in FIG. 9 has a protruding portion 90 on the upstream side in the sweep direction at the tip 124 (at a position of 100% in the span direction), between the nove 123 and the mean 125.
- the protrusion 91 on the upstream side in the sweep direction is formed so as to protrude on the upstream side in the sweep direction, thereby forming an S-shape.
- the transonic blade 12x has a three-dimensional blade shape for reducing profile loss, and the staggered direction of each cross-sectional profile is changed with respect to the span direction.
- Figures 11A and 11B show top views of the change in staggered direction of each step profile from the tip side of the transonic blade.
- FIG. 11B shows a top view of the transonic wing 12x of the present embodiment, and for easier understanding,
- FIG. 11A shows a transonic wing 12a having a reference shape with no displacement in the sweep direction. Contrast with Transonic Wings 12x.
- the transonic blades 12a and 12x are shown in FIGS. 12A and 12B, respectively.
- the cross-sectional profiles at Knob 123, Mean; 125, and Tip 124 are shown.
- both the transonic blades 12a and 12x are staggered so that the tip 124 side is at an angle that is nearly perpendicular to the axial direction of the rotor 5.
- the direction is determined, and the staggered direction is determined so that the hub 123 side is at an angle nearly parallel to the axial direction of the rotor 5.
- the staggered direction of each cross-sectional profile is set so that the staggered direction continuously changes from the hub 123 toward the chip 124.
- the angle of the staggered direction of the rotor 5 at the mean 125 with respect to the axial direction of the rotor 5 of the staggered direction at the tip 124 and the hub 123 is the intermediate value of the angle with respect to the axial direction of the rotor 5 of the staggered direction.
- a second embodiment of a transonic blade constructed by adjusting each cross-sectional profile in the span direction in the sweep direction based on the above basic structure will be described with reference to the drawings.
- the cross-sectional profile in the span direction is adjusted in the sweep direction, and the position of the cross-section profile is changed in the lean direction as well.
- the configuration is as follows.
- the transonic blade 12y of the present embodiment is similar to the transonic blade 12x of the first embodiment in the span direction from the hub to the tip as shown in FIG.
- Each cross-sectional profile is changed, and the tip 124 side has a forward sweep shape, and the hub 123 side has a backward sweep shape.
- each cross-sectional profile in the span direction from the hub to the chip is configured to be shifted in the lean direction.
- FIGS. 13A to 13C show configurations of three types of transonic blades 12a, 12d, and 12e that are continuously changed in the lean direction from the hub 123 to the tip 124 in the span direction.
- the transonic wing 12a in FIG. 13A is a “standard shape” transonic wing similar to FIG. 5A.
- the transonic blade 12d shown in FIG. 13B has the cross-sectional profile center of gravity G from the hub 123 toward the tip 124 with respect to the lean direction from the downstream side (abdominal surface 127 side) to the upstream side (back surface 126 side). It is set as the structure which changed to continuously. That is, as compared with the transonic blade 12a of FIG. 13A, the configuration is inclined forward toward the upstream side (front edge 121 side) with respect to the radial direction of the rotor 5.
- the shape like this transonic wing 12d will be referred to as “forward lean shape” in the following.
- the transonic blade 12e shown in FIG. 13C has the center of gravity G of each cross-sectional profile file from the tip 124 toward the hub 123 with respect to the lean direction from the downstream side (abdominal surface 127 side) to the upstream side (rear surface). 126 side). That is, as compared with the transonic blade 12a of FIG. 13A, the hub 123 side is inclined rearward with respect to the radial direction of the rotor 5 (rear edge 122 side), and the hub 123 side protrudes upstream (front edge 121 side). To do.
- the shape like this transonic wing 12e will be referred to as “backward lean shape” hereinafter.
- the forward sweep shape of the transonic wing 12b in FIG. 5B and the backward sweep shape of the transonic wing 12c in FIG. 5C In addition to the S-shape combined with the above, the forward lean shape of the transonic wing 12d in FIG. 13B or the backward lean shape of the transonic wing 12e in FIG. 13C is combined. As a result, as compared with the transonic blade 12x of the first embodiment, the degree of freedom in adjusting the axial flow velocity profile is increased, so that the aerodynamic performance can be improved.
- Fig. 14 shows a transition state in the lean direction of each cross-sectional profile with respect to the span direction from the hub to the tip when the forward lean shape is combined.
- a forward lean shape is combined with an S-shape with a forward sweep shape and a backward sweep shape, for example, the amount of transition force from the hub 123 to the upstream side (back side 126) in the lean direction It is set so that it gradually increases toward 124, and the rate of change of the transition amount is larger on the hub 123 side and smaller on the tip 124 side.
- the present invention is applicable to a transonic blade used in a transonic or supersonic working fluid atmosphere. Further, the present invention is applicable to an axial flow rotating machine provided with this transonic blade as a moving blade. Further, the axial flow rotating machine can be applied to a compressor such as a gas turbine, an aircraft fan engine, or an aircraft jet engine.
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Description
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Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN200780040888XA CN101535654B (zh) | 2006-11-02 | 2007-09-11 | 跨音速翼和轴流旋转机 |
US12/447,951 US8133012B2 (en) | 2006-11-02 | 2007-09-11 | Transonic airfoil and axial flow rotary machine |
EP07807054.7A EP2080909B1 (en) | 2006-11-02 | 2007-09-11 | Transonic airfoil and axial flow rotary machine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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JP2006-298841 | 2006-11-02 | ||
JP2006298841A JP4664890B2 (ja) | 2006-11-02 | 2006-11-02 | 遷音速翼及び軸流回転機 |
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WO2008053635A1 true WO2008053635A1 (fr) | 2008-05-08 |
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Application Number | Title | Priority Date | Filing Date |
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PCT/JP2007/067645 WO2008053635A1 (fr) | 2006-11-02 | 2007-09-11 | Profil aérodynamique transsonique et machine rotative à écoulement axial |
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US (1) | US8133012B2 (ja) |
EP (1) | EP2080909B1 (ja) |
JP (1) | JP4664890B2 (ja) |
KR (1) | KR101040825B1 (ja) |
CN (1) | CN101535654B (ja) |
WO (1) | WO2008053635A1 (ja) |
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JP4923073B2 (ja) | 2009-02-25 | 2012-04-25 | 株式会社日立製作所 | 遷音速翼 |
WO2012053024A1 (ja) | 2010-10-18 | 2012-04-26 | 株式会社 日立製作所 | 遷音速翼 |
US8702398B2 (en) | 2011-03-25 | 2014-04-22 | General Electric Company | High camber compressor rotor blade |
US8684698B2 (en) | 2011-03-25 | 2014-04-01 | General Electric Company | Compressor airfoil with tip dihedral |
JP6110544B2 (ja) * | 2011-06-29 | 2017-04-05 | 三菱日立パワーシステムズ株式会社 | 超音速タービン動翼及び軸流タービン |
EP2568114A1 (de) * | 2011-09-09 | 2013-03-13 | Siemens Aktiengesellschaft | Verfahren zum Profilieren einer Ersatzschaufel als ein Eratzteil für eine Altschaufel für eine Axialströmungsmaschine |
US9909425B2 (en) * | 2011-10-31 | 2018-03-06 | Pratt & Whitney Canada Corporation | Blade for a gas turbine engine |
JP5917243B2 (ja) * | 2012-04-06 | 2016-05-11 | 三菱日立パワーシステムズ株式会社 | ガスタービン改造方法及び改造を施したガスタービン |
US9121285B2 (en) * | 2012-05-24 | 2015-09-01 | General Electric Company | Turbine and method for reducing shock losses in a turbine |
FR2991373B1 (fr) * | 2012-05-31 | 2014-06-20 | Snecma | Aube de soufflante pour turboreacteur d'avion a profil cambre en sections de pied |
US9908170B2 (en) * | 2014-02-03 | 2018-03-06 | Indian Institute Of Technology, Bombay | Blade for axial compressor rotor |
CN105090098A (zh) * | 2014-05-09 | 2015-11-25 | 贵州航空发动机研究所 | 一种跨音风扇转子叶片 |
US10443390B2 (en) | 2014-08-27 | 2019-10-15 | Pratt & Whitney Canada Corp. | Rotary airfoil |
CN104533537B (zh) * | 2015-01-06 | 2016-08-24 | 中国科学院工程热物理研究所 | 大折转亚音速涡轮叶片及应用其的涡轮 |
US11248622B2 (en) * | 2016-09-02 | 2022-02-15 | Raytheon Technologies Corporation | Repeating airfoil tip strong pressure profile |
GB201702384D0 (en) | 2017-02-14 | 2017-03-29 | Rolls Royce Plc | Gas turbine engine fan blade |
GB201702382D0 (en) | 2017-02-14 | 2017-03-29 | Rolls Royce Plc | Gas turbine engine fan blade |
GB201702383D0 (en) * | 2017-02-14 | 2017-03-29 | Rolls Royce Plc | Gas turbine engine fan blade with axial lean |
GB201702380D0 (en) * | 2017-02-14 | 2017-03-29 | Rolls Royce Plc | Gas turbine engine fan blade with axial lean |
US11193377B2 (en) | 2019-11-26 | 2021-12-07 | General Electric Company | Turbomachine airfoil to reduce laminar separation |
US12065942B2 (en) | 2019-11-27 | 2024-08-20 | Rolls-Royce Plc | Gas turbine engine fan |
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- 2007-09-11 EP EP07807054.7A patent/EP2080909B1/en active Active
- 2007-09-11 KR KR1020097009461A patent/KR101040825B1/ko active IP Right Grant
- 2007-09-11 WO PCT/JP2007/067645 patent/WO2008053635A1/ja active Application Filing
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JPH07224794A (ja) | 1993-12-14 | 1995-08-22 | Mitsubishi Heavy Ind Ltd | 軸流機械の動翼 |
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US6071077A (en) * | 1996-04-09 | 2000-06-06 | Rolls-Royce Plc | Swept fan blade |
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JP2001214893A (ja) * | 1999-12-21 | 2001-08-10 | General Electric Co <Ge> | 湾曲したバレルエーロフォイル |
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US20100068064A1 (en) | 2010-03-18 |
CN101535654B (zh) | 2012-06-13 |
EP2080909A4 (en) | 2012-05-16 |
JP4664890B2 (ja) | 2011-04-06 |
EP2080909B1 (en) | 2015-11-18 |
KR101040825B1 (ko) | 2011-06-14 |
US8133012B2 (en) | 2012-03-13 |
KR20090078345A (ko) | 2009-07-17 |
CN101535654A (zh) | 2009-09-16 |
EP2080909A1 (en) | 2009-07-22 |
JP2008115736A (ja) | 2008-05-22 |
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