WO2021060093A1 - タービン翼 - Google Patents

タービン翼 Download PDF

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Publication number
WO2021060093A1
WO2021060093A1 PCT/JP2020/034988 JP2020034988W WO2021060093A1 WO 2021060093 A1 WO2021060093 A1 WO 2021060093A1 JP 2020034988 W JP2020034988 W JP 2020034988W WO 2021060093 A1 WO2021060093 A1 WO 2021060093A1
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WO
WIPO (PCT)
Prior art keywords
lattice
flow path
side edge
blade
edge portion
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/JP2020/034988
Other languages
English (en)
French (fr)
Japanese (ja)
Other versions
WO2021060093A8 (ja
Inventor
智子 都留
博資 瀧
大毅 鍋島
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Kawasaki Heavy Industries Ltd
Kawasaki Motors Ltd
Original Assignee
Kawasaki Heavy Industries Ltd
Kawasaki Jukogyo KK
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Kawasaki Heavy Industries Ltd, Kawasaki Jukogyo KK filed Critical Kawasaki Heavy Industries Ltd
Priority to GB2203943.2A priority Critical patent/GB2603338B/en
Priority to CN202080067343.3A priority patent/CN114450466B/zh
Priority to DE112020004602.8T priority patent/DE112020004602B4/de
Publication of WO2021060093A1 publication Critical patent/WO2021060093A1/ja
Priority to US17/702,914 priority patent/US11708763B2/en
Publication of WO2021060093A8 publication Critical patent/WO2021060093A8/ja
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/126—Baffles or ribs
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • 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
    • F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • the present invention relates to turbine blades used in a turbine of a gas turbine engine, and particularly to a structure for cooling the turbine blades.
  • the turbines that make up the gas turbine engine are located downstream of the combustor, and because the high-temperature gas burned by the combustor is supplied, they are exposed to high temperatures during the operation of the gas turbine engine. Therefore, it is necessary to cool the turbine blades, that is, the stationary blades and the moving blades.
  • As a structure for cooling such a turbine blade it is known that a part of air compressed by a compressor is introduced into a cooling passage formed in the blade to cool the turbine blade using compressed air as a cooling medium. (See, for example, Patent Document 1).
  • both side edges thereof are closed by side wall surfaces.
  • the cooling medium flowing through one flow path of the lattice structure collides with the side wall surface, turns and flows into the other flow path.
  • the cooling medium flowing through the other flow path of the lattice structure collides with the other side wall surface, turns and flows into one flow path.
  • the cooling medium repeatedly collides with and turns to the wall surfaces on both side edges to promote cooling. Further, cooling is further promoted by generating a vortex when the cooling medium crosses the intersection of the grid-like ribs.
  • the cooling medium flowing through the lattice structure collides with the side wall surface that closes the side edge portion and is turned, the fluid resistance increases remarkably near the side edge portion.
  • the flow paths communicate with each other at the intersection of the flow paths in the portion other than the side edge portion, if the fluid resistance increases in the vicinity of the side edge portion, the flow path does not reach the side edge portion as described above.
  • a short-circuit flow occurs from the communicating portion of the above to the other flow path.
  • the cooling medium does not sufficiently spread over the entire flow path, and the cooling efficiency is lowered. Further, the eddy current that should be generated by passing through the intersection is insufficient, and a sufficient cooling effect cannot be obtained from this point as well.
  • an object of the present invention is to suppress an increase in fluid resistance at the side edge of the lattice structure in a turbine blade having a lattice structure inside in order to solve the above problems, and to efficiently cool the turbine blade. Is to enable.
  • the turbine blade according to the present invention is a turbine blade of a turbine driven by a high temperature gas.
  • a cooling passage formed between the first inner wall surface and the second inner wall surface of the turbine blade facing each other, and the cooling medium moves from the root side to the tip side in the height direction of the turbine blade.
  • a cooling passage configured to A first rib set composed of a plurality of ribs arranged so as to extend in a direction inclined with respect to the height direction on the first inner wall surface of the cooling passage, and the height on the second inner wall surface.
  • a lattice structure formed by stacking a second rib set composed of a plurality of ribs arranged so as to extend in a direction inclined in a direction opposite to the first rib set in the longitudinal direction in a grid pattern.
  • a turning part is provided to turn the medium, In the height direction between the first side edge portion, which is one side edge portion of both side edges of the lattice structure, and the first side wall surface of the cooling passage facing the first side edge portion.
  • a first communication flow path is formed which extends and communicates a plurality of lattice flow paths at the first side edge portion.
  • the height is between the second side edge portion, which is the other side edge portion of both side edges of the lattice structure, and the second side wall surface of the cooling passage facing the second side edge portion.
  • a second communication flow path extending in the direction and communicating a plurality of lattice flow paths at the second side edge portion may be formed.
  • the cooling medium flowing through the lattice structure is turned at a turning portion that does not block the lattice flow path provided at the side edge of the lattice structure, and this turning part is outside the lattice structure. It communicates with the formed communication flow path. Therefore, the increase in fluid resistance at the side edges of the lattice structure is suppressed. As a result, the cooling medium is suppressed from flowing in a short circuit in the lattice structure, and the cooling medium is promoted to spread throughout the lattice flow path, so that the turbine blades can be cooled efficiently.
  • the direction in which the cooling medium flows is connected to the root of the turbine blade, that is, the turbine blade such as the rotor of the turbine (in the case of a turbine blade) or the casing (in the case of a turbine blade), and the cooling medium is introduced into the turbine blade. Since the direction is from the place where the introduction port is easily provided toward the tip side, the structure in the cooling passage can be simplified.
  • FIG. 5 is an enlarged vertical cross-sectional view showing the connecting portion of FIG. It is a vertical cross-sectional view which shows one modification of the connection part of FIG.
  • FIG. 1 shows a turbine blade, which is a turbine blade of a gas turbine engine according to an embodiment of the present invention.
  • the “turbine blade” includes a moving blade and a stationary blade of a turbine (hereinafter, simply referred to as “moving blade” and “static blade”, respectively).
  • moving blade and “static blade”, respectively.
  • the rotor blade 1 forms a turbine driven by a high-temperature gas G flowing in the direction of the arrow supplied from a combustor (not shown).
  • the turbine blade 1 has a first blade wall 3 that is concavely curved with respect to the high temperature gas G flow path GP, and a second blade wall 5 that is convexly curved with respect to the high temperature gas flow path GP.
  • the blade wall that is concavely curved with respect to the high temperature gas G flow path GP is referred to as the first blade wall 3, and is convex with respect to the high temperature gas flow path GP.
  • the wing wall curved in the direction of 2 is referred to as a second wing wall 5, but unless otherwise specified, the configuration of the first wing wall 3 and the configuration of the second wing wall 5 can be interchanged with each other.
  • the upstream side (left side in FIG. 1) along the flow direction of the high temperature gas G is referred to as front, and the downstream side (right side in FIG. 1) is referred to as rear.
  • the moving blade 1 is planted in the turbine rotor by connecting the platform 7 to the outer peripheral portion of the turbine disk 9 which is a part of the turbine rotor.
  • a large number of rotor blades 1 are planted in the circumferential direction of the turbine rotor to form a turbine.
  • a cooling passage 11 for cooling the rotor blade 1 from the inside is formed inside the rotor blade 1 (the space between the first blade wall 3 and the second blade wall 5 in FIG. 1).
  • blade height direction H the height direction of the turbine blade (moving blade 1 in this example), that is, the radial direction of the turbine is referred to as “blade height direction H”, and is substantially along the blade chord perpendicular to the blade height direction H.
  • blade width direction W The direction in which the first blade wall 3 and the second blade wall 5 face each other (direction perpendicular to the paper surface in FIG. 2) is referred to as “blade width direction W”, and is referred to as "blade thickness direction D”.
  • the cooling medium CL which is a part of the compressed air from the compressor, passes through the refrigerant introduction passage 13 formed inside the turbine disk 9 on the inner side in the radial direction and toward the outer side in the radial direction.
  • the flow is introduced into the cooling passage 11 via the refrigerant introduction port 15 formed on the end surface on the root portion (the portion connected to the turbine disk 9) 1a side of the moving blade 1.
  • the entire cooling medium CL flows in the direction from the root portion 1a side to the tip portion 1b side in the blade height direction H.
  • the cooling medium CL supplied to the cooling passage 11 is discharged to the outside (passage GP of the high temperature gas G) from the refrigerant discharge hole 17 provided at the tip portion 1b of the moving blade 1.
  • the refrigerant discharge hole 17 may be provided.
  • the flow direction of the cooling medium CL is set to the root portion 1a side of the turbine blade, that is, the turbine blades such as the rotor (in the case of the moving blade 1) or the casing (in the case of the stationary blade) of the turbine, and the cooling medium CL is connected.
  • the structure in the cooling passage 11 can be simplified by making the direction from the position where it is easy to provide the introduction port (the refrigerant introduction port 15 in the example of the figure) into the turbine blade toward the tip portion 1b side.
  • the cooling passage 11 is provided over the entire blade width direction W of the moving blade 1, but only a part of the moving blade 1 in the blade width direction W, for example, only the rear half region. It may be provided.
  • a lattice structure 21 is provided as a cooling structure for cooling the moving blade 1.
  • the lattice structure 21 is composed of a plurality of ribs erected on the wall surface of the first wing wall 3 and the wall surface of the second wing wall 5 facing the cooling passage 11.
  • the wall surface of the first wing wall 3 facing the cooling passage 11 is referred to as a first inner wall surface 3a
  • the wall surface of the second wing wall 5 facing the cooling passage 11 is referred to as a second inner wall surface 5a.
  • the lattice structure 21 is provided only on a part of the cooling passage 11 on the root portion 1a side in the blade height direction H.
  • the cooling medium CL discharged from the lattice structure 21 is guided to the refrigerant discharge hole 17 in the remaining portion of the cooling passage 11 on the tip 1b side in the blade height direction H (that is, the downstream portion in the cooling passage 11).
  • the refrigerant lead-out unit 23 is formed.
  • the refrigerant lead-out portion 23 is formed in a portion of the cooling passage 11 in a region from the outlet of the lattice structure 21 to the refrigerant discharge hole 17.
  • the first inner wall surface 3a and the second inner wall surface 5a (FIG. 3) of the refrigerant lead-out portion 23 are provided with flat surfaces, that is, protrusions and recesses, except for the portion where the connecting column 25, which will be described later, is provided. It is formed as a non-surface.
  • the lattice structure 21 has a plurality of rib sets 33 composed of a plurality of ribs 31 provided parallel to each other and at equal intervals on both wall surfaces 3a and 5a facing the cooling passage 11. It is formed by stacking and combining in a grid pattern.
  • a first rib set (in FIG. 4) composed of a plurality of ribs 31 arranged so as to extend in a direction inclined with respect to the blade height direction H on the first inner wall surface 3a.
  • the lattice structure 21 is formed by combining the two rib sets (upper rib set in FIG. 4) 33B in a grid pattern in the blade thickness direction D.
  • the gap between the adjacent ribs 31 and 31 of each rib set 33 forms the flow path (lattice flow path) 35 of the cooling medium CL.
  • Each lattice flow path 35 extends so as to be inclined with respect to the blade height direction H between the two side edge portions 21a, 21a extending in the blade height direction H of the lattice structure 21.
  • the "side edge portion 21a" of the lattice structure 21 refers to the edge portion of the lattice structure 21 in the blade width direction W.
  • the inclination angle ⁇ 1 of the first rib set 33A with respect to the height direction H is set to 45 °.
  • the inclination angle ⁇ 2 of the second rib set 33B with respect to the height direction H is set to 45 ° in the direction opposite to that of the first rib set 33A. Therefore, the angle formed by the extending direction of the first rib set 33A and the extending direction of the second rib set 33B is approximately 90 °.
  • the values of these inclination angles ⁇ 1 and ⁇ 2 are not limited to 45 °.
  • the side edge portions 21a and 21a of the lattice structure 21 are opened at each side edge portion 21a, and the other rib assembly is formed from the lattice flow path 35 formed in one rib assembly 33.
  • a turning portion 37 for turning the cooling medium CL to the lattice flow path 35 formed in 33 is provided.
  • the turning portion 37 of the lattice structure 21 is at least downstream of the two ribs 31 and 31 forming each lattice flow path 35 (tip portion 1b in the blade height direction H).
  • the side edge portion 21a of the rib 31 located on the upper side of FIG. 6 has a portion deflected inward of the lattice flow path 35 with respect to the inclination direction of the rib 31.
  • the turning portion 37 has a portion of the side edge portion 21a of the rib 31 located on the downstream side of the lattice flow path 35, which is bent by bending along the blade width direction W at the bent portion 37a.
  • the side edge portion 21a of the rib 31 located on the upstream side of the lattice flow path 35 is also deflected along the blade width direction W in order to easily form the turning portion 37.
  • the shape of the turning portion 37 of the lattice structure 21 is deflected inward of the lattice flow path 35 with respect to the inclination direction of the rib 31 at the side edge portion 21a of the rib 31 located on the downstream side of the lattice flow path 35. If so, it is not limited to the above example.
  • the side edge portion 21a of the rib 31 located on the downstream side of the lattice flow path 35 may be curved inward of the lattice flow path 35 with respect to the inclination direction of the rib 31. ..
  • the rib 31 located on the upstream side of the lattice flow path 35 does not have to be deflected as shown in the figure.
  • the blade height is further between the side edge portions 21a of the lattice structure 21 and the side wall surfaces 39 and 39 of the cooling passage 11 facing each side edge portion 21a.
  • Communication flow paths 41 extending in the longitudinal direction H are formed respectively.
  • the lattice structure 21 is formed so that its wingspan direction dimension Lx is smaller than the blade width direction dimension Cx of the cooling passage 11, and is positioned at equal intervals from the wall surfaces 39 and 39 on both sides of the cooling passage 11. It is provided in.
  • the gaps between the side edge portions 21a and 21a of the lattice structure 21 installed in this way and the side wall surfaces 39 and 39 of the cooling passage 11 form the communication flow path 41.
  • the turning portions 37 provided on both side edge portions 21a of the lattice structure 21 are open at each side edge portion 21a, a plurality of turning portions 37 at each side edge portion 21a are provided by each communication flow path 41.
  • Lattice flow path 35 (turning portion 37) communicates with each other.
  • the cooling medium CL introduced into the lattice structure 21 is first of one rib set 33 (in the illustrated example, the lower first rib set 33A) as shown by the broken line arrow in the figure. It flows through the lattice flow path 35, crosses the other rib set 33 (upper second rib set 33B in the illustrated example), and collides with the turning portion 37 provided on the side edge portion 21a. As shown by the solid arrow in the figure, the cooling medium CL that has collided with the turning portion 37 is turned and flows into the lattice flow path 35 of the other rib set 33 (in the illustrated example, the upper second rib set 33B). At the time of this conversion, a strong eddy current is generated in the cooling medium CL.
  • FIG. 4 shows only the turning portions 37 at both ends of one lattice flow path 35, and the others are omitted.
  • the heights of the ribs 31 of the first rib set 33A and the second rib set 33B that is, the lattice flow path heights h1 and h2 in the blade thickness direction are the same. is there. Further, the distance between the ribs 31 in the first rib set 33A and the distance between the ribs 31 in the second rib set 33B are the same. That is, the lattice flow path width P1 in the first rib set 33A and the lattice flow path width P2 in the second rib set 33B are the same.
  • the ratio of the lattice flow path heights h1 and h2 to the lattice flow path widths P1 and P2 in each lattice flow path 35 is not particularly limited, but as described above, in the lattice structure 21. From the viewpoint of avoiding deformation of the vortex flow and peeling from the wall surface, it is preferably in the range of about 0.5 to 1.5. In this embodiment, the aspect ratio of the lattice flow path 35 is 1.
  • the turning portion 37 for turning the cooling medium CL is open at each side edge portion 21a, that is, each lattice flow path 35 is not blocked. Moreover, each turning portion 37 communicates with the communication flow path 41 formed on the outside thereof. Therefore, the increase in the fluid resistance of the cooling medium CL is suppressed in the vicinity of the turning portion 37. As a result, the cooling medium CL surely reaches the side edge portion 21a of the lattice structure 21 without short-circuiting in the middle of the lattice flow path 35, and is turned at the turning portion 37.
  • the flow path width Px of the communication flow path 41 is not particularly limited. However, if the flow path width Px is too wide, the cooling medium CL will flow from the turning portion 37 into the communication flow path 41, and the cooling medium CL will not be sufficiently turned at the turning portion 37. On the other hand, if the flow path width Px is too narrow, the effect of suppressing an increase in the fluid resistance of the cooling medium CL in the turning portion 37 cannot be sufficiently obtained. From this point of view, the flow path width Px of the communication flow path 41 is about 1 to 3 times the lattice flow path heights h1 and h2, in other words, the cooling passage height (in the blade thickness direction D of the cooling passage 11). Dimension) It is preferable that it is in the range of about 0.5 to 1.5 times Cz.
  • the communication flow path 41 is shown to have a constant flow path width Px over the entire length for the sake of simplification of illustration.
  • the chord direction dimension of the moving blade 1 is not constant along the blade height direction H, and the dimension that can be assigned to the communication flow path 41 may change accordingly.
  • the blade height direction dimension Ly with respect to the blade width direction dimension Lx of the lattice structure 21 is preferably a dimension that reaches the side edge portion 21a at least once in any lattice flow path 35. From this point of view, Lx is preferably in the range of 1.5 to 2 times Ly / tan ⁇ 1.
  • the communication flow paths 41 and 41 corresponding to the side edge portions 21a and 21a of the lattice structure 21 are provided, respectively, but the communication flow path 41 corresponding to one of the side edge portions 21a is provided. Only may be provided.
  • each communication flow path 41 is opened to the above-mentioned refrigerant outlet 23, and the refrigerant discharge hole 17 is provided downstream of the refrigerant outlet 23.
  • the cooling medium CL flowing through the communication flow path 41 is smoothly discharged from the outlet, so that the increase in fluid resistance at the side edge portion 21a of the lattice structure 21 is more effectively suppressed.
  • the length Fy in the blade height direction H is not particularly limited, but is within a range of about 3 to 7 times the cooling passage height Cz (FIG. 4) at the outlet of the lattice structure 21. It is preferable to have.
  • the refrigerant lead-out unit 23 is provided with a connecting column 25 for connecting the first inner wall surface 3a and the second inner wall surface 5a.
  • a cylindrical pin-shaped member is used as the connecting column 25.
  • a plurality of (8 in this example) connecting columns 25 are arranged in a staggered pattern.
  • the shape, size, number and arrangement of the connecting columns 25 are sufficient to prevent deformation of the blade walls 3 and 5, and are appropriate so as not to excessively prevent the cooling medium CL from being led out to the refrigerant discharge hole 17. Be selected.
  • the diameter d of the connecting columns 25 is preferably about 0.5 to 1.5 times the lattice flow path widths P1 and P2, and the arrangement interval between the connecting columns 25 is preferable.
  • S is in the range of 0.5 times the flow path pitch (W dimension in the blade width direction of the unit lattice flow path 35) Pc at the outlet of the lattice flow path 35 to 0.5 times the blade width direction dimension Lx of the lattice structure 21. It is preferably inside.
  • the shape, number, and arrangement of the connecting columns 25 may be appropriately selected according to the size of the refrigerant lead-out unit 23, the distance between the blade walls, that is, the height of the cooling passage 11. Further, even when the refrigerant lead-out unit 23 is provided, the connecting column 25 may be omitted.
  • the cooling medium CL flowing in the lattice structure 21 is converted so as not to block the lattice flow path 35 provided in the side edge portion 21a of the lattice structure 21. It is converted in the portion 37, and the converted portion 37 communicates with the communication flow path 41 formed on the outside of the lattice structure 21. Therefore, the increase in fluid resistance at the side edge portion 21a of the lattice structure 21 is suppressed. As a result, the cooling medium CL is suppressed from flowing short-circuited in the lattice structure 21, and the circulation of the cooling medium CL throughout the lattice flow path 35 is promoted.
  • the cooling medium CL is surely turned at the side edge portion 21a of the lattice structure 21 to generate a vortex flow, so that the turbine blades can be cooled efficiently.
  • the flow direction of the cooling medium CL is connected to the root side of the turbine blade, that is, the turbine blades such as the rotor of the turbine (in the case of the turbine blade 1) or the casing (in the case of the turbine blade), and the turbine of the cooling medium CL is connected. Since the direction is such that the introduction port into the blade is easily provided toward the tip end side, the structure inside the cooling passage 11 can be simplified.
  • the turning portion 37 is a side edge portion 21a of a rib located at least downstream of the two ribs 31 and 31 forming the lattice flow path 35 with respect to the inclination direction of the rib. It may have a portion deflected inside the lattice flow path 35. According to this configuration, the cooling medium CL that has reached the side edge portion 21a of the lattice structure 21 can be turned at the turning portion by a simple structure.
  • the tip portion 1b is provided with a refrigerant discharge hole 17 for discharging the cooling medium CL in the cooling passage 11 to the outside, and the region of the cooling passage 11 on the tip portion 1b side is provided.
  • the cooling medium CL may be formed as a refrigerant lead-out unit 23 that leads out the cooling medium CL to the refrigerant discharge hole 17. According to this configuration, by providing the refrigerant lead-out portion 23, the cooling medium CL flowing through the communication flow path 41 is smoothly discharged from the installation region of the lattice structure 21 toward the tip portion 1b of the turbine blade 1. .. Therefore, the increase in static pressure at the side edge portion 21a of the lattice structure 21 is more effectively suppressed.
  • the refrigerant outlet may be provided with a connecting column 25 for connecting the first inner wall surface 3a and the second inner wall surface 5a. According to this configuration, deformation of the blade walls 3 and 5 in the refrigerant lead-out portion 23 is prevented, and the height of the cooling passage 11 is secured.
  • Cooling passage 10 Cooling structure 17 Refrigerant discharge hole 21 Lattice structure 21a Side edge of the lattice structure 23 Refrigerant outlet 25 Connecting column 31 Rib 33 of the lattice structure Lattice Rib assembly of structure 37 Turning part 39 Side wall surface of cooling passage 41 Communication flow path CL Cooling medium G High temperature gas

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
PCT/JP2020/034988 2019-09-26 2020-09-15 タービン翼 Ceased WO2021060093A1 (ja)

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GB2203943.2A GB2603338B (en) 2019-09-26 2020-09-15 Turbine Airfoil
CN202080067343.3A CN114450466B (zh) 2019-09-26 2020-09-15 涡轮叶片
DE112020004602.8T DE112020004602B4 (de) 2019-09-26 2020-09-15 Turbinenflügel
US17/702,914 US11708763B2 (en) 2019-09-26 2022-03-24 Turbine airfoil

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JP2019-175092 2019-09-26
JP2019175092A JP7681382B2 (ja) 2019-09-26 2019-09-26 タービン翼

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113623010A (zh) * 2021-07-13 2021-11-09 哈尔滨工业大学 涡轮叶片

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2023286206A1 (ja) * 2021-07-14 2023-01-19 ヤマハ発動機株式会社 筐体
WO2023286624A1 (ja) * 2021-07-14 2023-01-19 ヤマハ発動機株式会社 筐体具備装置
WO2023286205A1 (ja) * 2021-07-14 2023-01-19 ヤマハ発動機株式会社 筐体

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS4829917A (enExample) * 1971-08-25 1973-04-20
JP2002516944A (ja) * 1998-05-25 2002-06-11 エービービー アクチボラゲット ガスタービン用要素
US20070172354A1 (en) * 2004-02-27 2007-07-26 Mats Annerfeldt Blade or vane for a turbomachine
JP2009221995A (ja) * 2008-03-18 2009-10-01 Ihi Corp 高温部品の内面冷却構造
US20130034429A1 (en) * 2010-04-14 2013-02-07 Dave Carter Blade or vane for a turbomachine
JP2013181543A (ja) * 2012-03-01 2013-09-12 General Electric Co <Ge> 先端漏洩流れガイドを有する回転ターボ機械部品
JP2016125380A (ja) * 2014-12-26 2016-07-11 川崎重工業株式会社 タービン翼の冷却構造
WO2018164149A1 (ja) * 2017-03-10 2018-09-13 川崎重工業株式会社 タービン翼の冷却構造
WO2018164148A1 (ja) * 2017-03-10 2018-09-13 川崎重工業株式会社 タービン翼の冷却構造

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5603606A (en) 1994-11-14 1997-02-18 Solar Turbines Incorporated Turbine cooling system
JP4957131B2 (ja) 2006-09-06 2012-06-20 株式会社Ｉｈｉ 冷却構造
CN100557199C (zh) 2007-07-13 2009-11-04 北京航空航天大学 一种适用于涡轮叶片等内冷部件中的渐宽型开槽交错肋通道
US10247015B2 (en) * 2017-01-13 2019-04-02 Rolls-Royce Corporation Cooled blisk with dual wall blades for gas turbine engine
JP6898104B2 (ja) * 2017-01-18 2021-07-07 川崎重工業株式会社 タービン翼の冷却構造
US10895157B2 (en) * 2017-04-24 2021-01-19 Honeywell International Inc. Gas turbine engine components with air-cooling features, and related methods of manufacturing the same
JP2019175092A (ja) 2018-03-28 2019-10-10 三菱プレシジョン株式会社 Ｉｃカードリーダシステム

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS4829917A (enExample) * 1971-08-25 1973-04-20
JP2002516944A (ja) * 1998-05-25 2002-06-11 エービービー アクチボラゲット ガスタービン用要素
US20070172354A1 (en) * 2004-02-27 2007-07-26 Mats Annerfeldt Blade or vane for a turbomachine
JP2009221995A (ja) * 2008-03-18 2009-10-01 Ihi Corp 高温部品の内面冷却構造
US20130034429A1 (en) * 2010-04-14 2013-02-07 Dave Carter Blade or vane for a turbomachine
JP2013181543A (ja) * 2012-03-01 2013-09-12 General Electric Co <Ge> 先端漏洩流れガイドを有する回転ターボ機械部品
JP2016125380A (ja) * 2014-12-26 2016-07-11 川崎重工業株式会社 タービン翼の冷却構造
WO2018164149A1 (ja) * 2017-03-10 2018-09-13 川崎重工業株式会社 タービン翼の冷却構造
WO2018164148A1 (ja) * 2017-03-10 2018-09-13 川崎重工業株式会社 タービン翼の冷却構造

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113623010A (zh) * 2021-07-13 2021-11-09 哈尔滨工业大学 涡轮叶片

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CN114450466B (zh) 2023-08-29
CN114450466A (zh) 2022-05-06
US11708763B2 (en) 2023-07-25
GB2603338B (en) 2023-02-08
US20220213792A1 (en) 2022-07-07
GB202203943D0 (en) 2022-05-04
JP7681382B2 (ja) 2025-05-22
WO2021060093A8 (ja) 2022-03-24
DE112020004602T5 (de) 2022-06-09
JP2021050688A (ja) 2021-04-01
GB2603338A (en) 2022-08-03
DE112020004602B4 (de) 2024-08-29

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