Classifications

• • 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
  • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
  • 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
  • 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
  • F05D2250/28—Three-dimensional patterned
• • 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
  • F05D2260/2212—Improvement of heat transfer by creating turbulence
• • 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 a blade, in particular a turbine blade with at least one channel, which is delimited by walls and can be acted upon by a cooling fluid, with several turbulators being provided on at least one wall to improve the heat exchange between the wall and the cooling fluid.
• Such a turbine blade is known for example from EP 0 758 932 B1.
• This known turbine blade is hollow and has four channels.
• the channels are delimited by the two outer walls of the turbine blade and partitions and a cooling fluid flows through them for cooling.
• the outer walls are provided with turbulators.
• the turbulators only serve to improve the heat exchange.
• the loads on the turbine blade that occur during operation are practically absorbed exclusively by the outer walls, which must therefore be made relatively thick. If the load increases, the wall thickness of the outer walls must be increased further. However, this increase in wall thickness reduces the cow's efficiency and thus the overall efficiency.
• the object of the present invention is therefore to provide a blade which enables a higher load capacity without increasing the wall thickness or a reduction in the wall thickness with the same load capacity.
• the turbulators are used for stiffening the wall for the first time and merge into one another. This results in a significant increase in rigidity without additional material and without increasing the wall thickness. At the same time, good heat exchange between the walls and the cooling fluid is achieved. This results in high cow efficiency and a high overall efficiency.
• the stiffening of the wall does not only occur in the area of a single turbulator. Rather, a large-area stiffening is provided by connecting the turbulators to one another.
• the turbulators are advantageously straight.
• all turbulators enclose the same angle with a longitudinal axis of the blade.
• the result is a symmetrical arrangement of the turbulators, which can absorb loads evenly from all directions.
• the turbulators enclose a right angle.
• an acute or obtuse angle can also be selected.
• a first group of turbulators with a longitudinal axis of the blade encloses a first angle and a second group of turbulators with the longitudinal axis of the blade encloses a second angle.
• the two groups of turbulators have thus differed on ⁇ Liche inclinations towards the longitudinal axis of the blade.
• the stiffness of the blade therefore depends on the direction of attack of the load. Due to the different inclination, a specific adaptation of the stiffness can be achieved in different directions.
• the turbulators are advantageously arranged such that they form adjacent and superimposed recesses in the form of polygons, in particular squares, rhombuses or hexagons.
• the inside of the wall is provided with a honeycomb structure.
• the individual polygons or honeycombs each form a closed, highly resilient cross-section and support each other. A substantial increase in rigidity can be achieved.
• the wall thickness of the wall is reduced at least in the area between the turbulators. This reduction in wall thickness is made possible by the fact that the turbulators stiffen the wall.
• the turbulators can advantageously be used as metal feed channels when casting the blade.
• the honeycomb structure is therefore easy to manufacture.
• the blade has a plurality of sections provided with different arrangements of turbulators. These different arrangements allow the stiffness to be specifically influenced in the individual sections of the blade. This results in an optimal adaptation to the loads present in the respective section of the blade.
• the sections are spaced apart from one another. This enables a simple change between different arrangements of turbulators.
• the sections merge into one another. There is a continuous increase in the stiffness of the blade.
• the blade according to the invention can be designed as a guide blade or as a rotor blade of a rotary machine.
• 1 shows a longitudinal section through a rotary machine
• 2 shows a perspective, broken-away representation of a blade
• 3 shows an enlarged view of the detail X from
• Figure 2; 4 shows a plan view of the inside of an outer wall of the blade in the first embodiment
• FIG. 5 shows a view similar to FIG. 4 in the second embodiment
• 6 shows a view similar to FIG. 4 in the third embodiment
• 7 shows a schematic illustration of a rotor blade
• FIG. 8 shows a schematic illustration of a guide vane.
• FIG. 1 shows a longitudinal section through a rotary machine in the form of a turbine 10 with a housing 11 and a rotor 12.
• the housing 11 is provided with guide vanes 13 and the rotor 12 with rotor blades 14.
• the turbine 10 is flowed through according to arrow 15 by a fluid which flows along the guide vanes 13 and rotor blades 14 and rotates the rotor 12 about an axis 16.
• the temperature of the fluid is relatively high in many application cases, particularly in the area of the first row of blades (shown on the left in FIG. 1). Cooling of the guide vanes 13 and rotor blades 14 is therefore provided.
• the flow of the cooling fluid is indicated schematically by the arrows 17, 18. Air can in particular be used as the cooling fluid.
• FIG. 2 schematically shows a broken view of a guide vane 13.
• the guide vane 13 has curved outer walls 19, 20.
• the interior lying between the outer walls 19, 20 is divided into a total of three channels 22 via two partition walls 21 m.
• the channels 22 are charged with a cooling fluid.
• the outer walls 19, 20 are provided with a plurality of turbulators 23.
• the turbulators 23 m are shown in a very simplified manner in FIG. However, it can be seen that the turbulators 23 merge into one another and form a honeycomb structure. This honeycomb structure stiffens the outer walls 19, 20.
• Figure 3 shows an enlarged view of the detail X from Figure 2.
• the turbulators 23 are straight and merge.
• a recess 24 is delimited by four turbulators each.
• the wall thickness d of the outer wall 19 decreases continuously from the turbulators 23 to
• the turbulators 23 are approximately triangular in cross-section and taper starting from the outer wall 19. They can therefore serve as metal feed channels when casting the guide vane 13.
• the guide vane 13 according to the invention is thus easy to manufacture.
• Figures 4 to 6 show a schematic plan view of the inside of the outer wall 19 m in three different configurations.
• all turbulators 23a, 23b enclose the same angle, ⁇ with a longitudinal axis 25 of the guide vane 13.
• the turbulators 23a, 23b form a right angle 26 with one another.
• the recesses 24 delimited by the turbulators 23a, 23b thus form squares.
• a turbulator 23a, 23b extends between two contact points 31. In the area of the contact points 31, the turbulators 23a, 23b merge into one another. The manufacture is simplified by using straight turbulators 23a, 23b. There is also a high degree of rigidity.
• a first group of turbulators 23a includes a first angle with the longitudinal axis 25, while a second group of turbulators 23b includes a second angle ⁇ with the longitudinal axis 25.
• the angle 26 between the turbulators in this embodiment is greater than 90 °.
• the result is a recess 24 m in shape of a diamond.
• the different inclination of the turbulators 23a, 23b with respect to the longitudinal axis results in a different stiffness of the guide vane 13 m as a function of the load direction. A good adaptation to different boundary conditions is thus achieved.
• turbulators 23 each form a recess 24 in the form of a hexagon.
• the result is a honeycomb structure which significantly increases the rigidity of the guide vane 13.
• turbulators 23 are advantageously arranged such that the recesses 24 shown in FIGS. 4 to 6 are formed. These recesses 24 have a closed cross section in plan view and therefore have a high degree of rigidity.
• the turbulators 23 can also be arranged in the form of a V or X.
• the turbulators 23 can also be provided with a moving blade 14.
• a blade 14 is shown schematically in FIG. 7, which has a plurality of sections 28, 29, 30 provided with different arrangements of turbulators 23.
• the arrangement of the section 28 corresponds to the illustration according to FIG. 4, while the sections 29, 30 are designed according to FIGS. 5 and 6.
• the individual sections 28, 29, 30 are spaced apart.
• cross-sectional or shape changes of the rotor blade 14 can be carried out with little manufacturing effort.
• the wall thickness d of the outer walls 19, 20 m is increased corresponding to these transition areas.
• the use of different arrangements of turbulators 23 enables the stiffness of the blade 14 to be influenced in a targeted manner in the individual sections 28, 29, 30. This results in an optimal adaptation to different boundary conditions along the longitudinal axis 25.
• the sections 28, 29, 30 can also merge into one another, as shown schematically using a guide vane 13 m in FIG. 8.
• the turbulators 23 of the individual sections 28, 29, 30 merge into one another at contact points (not shown in more detail). This results in a continuous stiffening of the guide vane 13 along its longitudinal axis 25.
• the present invention enables the rigidity to be increased by a targeted arrangement of the turbulators provided to improve the heat exchange.
• the wall thickness d of the outer walls 19, 20 can be reduced. This reduction in the wall thickness increases the cow's efficiency, so that the overall efficiency of the turbine 10 is higher overall.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Architecture (AREA)
• Turbine Rotor Nozzle Sealing (AREA)

Priority Applications (3)

Applications Claiming Priority (2)

Publications (1)

Family

ID=8168202

Family Applications (1)

Country Status (6)

Cited By (2)

Families Citing this family (11)

Citations (8)

Family Cites Families (3)

• 2001
  • 2001-03-15 WO PCT/EP2001/002982 patent/WO2001071164A1/de active IP Right Grant
  • 2001-03-15 CN CNB018067913A patent/CN100376766C/zh not_active Expired - Fee Related
  • 2001-03-15 US US10/221,309 patent/US20030049125A1/en not_active Abandoned
  • 2001-03-15 JP JP2001569125A patent/JP4610836B2/ja not_active Expired - Fee Related
  • 2001-03-15 DE DE50105063T patent/DE50105063D1/de not_active Expired - Lifetime
  • 2001-03-15 EP EP01927732A patent/EP1266128B1/de not_active Expired - Lifetime

Patent Citations (8)

Non-Patent Citations (1)

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