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
  • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
  • F01D5/186—Film 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
  • 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
  • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
  • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
• • 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
  • 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
  • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
• • 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

Definitions

• the present invention relates to the general field of turbomachine blades, and more particularly to the evacuation at the trailing edge of cooling air from the blades of a high-pressure turbine of a turbomachine.
• the blades of a turbomachine high-pressure turbine are subjected to the high temperatures of the gases from the combustion chamber which pass through the high-pressure turbine. These temperatures reach values much higher than those that the blades which are in contact with these gases can withstand, which has the consequence of limiting their service life.
• cooling air which is generally introduced into the blade by its foot, passes through the latter by following a path formed by cavities made in the blade before being ejected through slots. opening to the surface of the blade, between the root and the top of the latter.
• the trailing edge of the moving blade is a critical area from a point of view. thermal and mechanical due to the difficulty in cooling it effectively. This is mainly due to the lack of space, in particular because of the minimum thicknesses of material required for the manufacture of the blade, and in particular to the junction of the lower surface and upper surface at the trailing edge.
• the vane area upstream of the exhaust slits is a difficult to cool area which regularly displays a high thermal level. This is mainly due to the lack of space to put turbulence promoters for cooling and to have two cooling cavities in the thickness of the blade.
• the object of the present invention is therefore to provide a movable blade of
• turbomachine which does not have the aforementioned drawbacks.
• a mobile turbine engine blade comprising a blade extending radially between a blade root and a blade top and axially between a leading edge and a trailing edge.
• at least one cooling circuit comprising at least one cavity extending radially between the foot and the top, at least one air intake opening at a radial end of the cavity, a plurality of first exhaust slots provided along the trailing edge between the foot and the crown, and a plurality of second exhaust slits distinct from the first slits and provided along the trailing edge between the foot and the crown, the second exhaust slits being offset axially upstream of the first discharge slots and each of the first discharge slots being radially offset from each of the second discharge slots, with no overlap between the first and second discharge slots cuation.
• the invention is remarkable in that it provides an additional row of discharge slots upstream and radially offset without overlapping vis-à-vis. from the usual row of exhaust slots.
• this additional row makes it possible to benefit from cooling upstream of the usual slots.
• the intrados face of the blade is then cooled on a larger curvilinear abscissa at the level of the trailing edge of the blade.
• upstream of this row
• the first discharge slots and the second discharge slots may open into the same cavity of the cooling circuit.
• evacuation can lead into two separate cavities of the cooling circuit.
• the cavity into which the second discharge slots open is preferably offset axially upstream with respect to the cavity into which the first discharge slots open.
• the first evacuation slits open at the level of the trailing edge and the second evacuation slits can open at the level of a lower surface of the blade.
• drainage can open at a lower surface of the blade.
• the first discharge slots and the second discharge slots can be arranged in columns. Likewise, the second exhaust slits can exactly occupy each of the radial spaces left between the first exhaust slits.
• the invention also relates to a process for manufacturing by foundry of a blade as defined above, comprising the production of a ceramic core by additive manufacturing, the core making it possible to produce the first slots
• a further subject of the invention is a high-pressure turbine for a turbomachine, comprising a disc which has a plurality of cells which open out at the periphery of the disc and a plurality of blades as defined above.
• Figure 1 is a perspective view of an exemplary dawn to which the invention applies.
• Figure 2 is a cross-sectional view of a vane according to one embodiment of the invention showing the cooling circuit of the trailing edge of the vane.
• FIG. 3 is a partial perspective view from the lower surface of a blade according to another embodiment of the invention showing the exhaust slots of the cooling circuit of the trailing edge of the blade.
• FIG. 4 is a partial and perspective view from the lower surface of a blade according to yet another embodiment of the invention.
• FIG. 1 shows in perspective a turbine blade 2, for example a moving blade of a high-pressure turbine of a turbomachine.
• the blade 2 is attached to a turbine rotor (not shown) via a socket 4 generally in the shape of a fir tree.
• the blade 2 comprises a blade 6 which extends radially between a blade root 8 and a blade top 10, and axially between a leading edge 12 and a trailing edge 14.
• the blade 6 of the blade thus defines the lower surface 6a and the upper surface 6b of the blade.
• the blade 2 which is subjected to the high temperatures of the combustion gases passing through the turbine, needs to be cooled.
• the blade 2 comprises one or more internal cooling circuits, and in particular an internal cooling circuit for the trailing edge.
• the internal circuit for cooling the trailing edge of the blade comprises at least one cavity 16 extending radially between the foot 8 and the top 10.
• the cavity 16 is supplied with cooling air at one of its radial ends by an air intake opening (not shown) which is generally provided at the level of the root 4 of the blade. .
• the internal cooling circuit of the trailing edge of the blade comprises two distinct cavities 16a, 16b which are axially offset from one another.
• the cooling circuit of the trailing edge also comprises a plurality of first evacuation slots 18 which are arranged along the trailing edge 14 of the vane between the root 8 and the top 10, and a plurality 20 second evacuation slits which are distinct from the first slits
• the first discharge slots 18 open into the cavity 16b of the cooling circuit and open onto the underside face 6a of the blade near its trailing edge 14.
• the second evacuation slots 20 they open into the cavity 16a of the cooling circuit and also open onto the lower surface face 6a of the blade near its trailing edge 14.
• the second discharge slots 20 are offset axially upstream with respect to the first discharge slots 18 and arranged to be radially offset with respect to the first discharge slots without overlap between them, that is, the bottom wall of a given slot does not overlap the top wall of the adjacent radially offset slot and vice versa.
• first and second discharge slots 18, 20 are arranged to form two distinct rows of slots which are axially and radially offset from each other.
• FIG. 3 represents a second embodiment of the invention in which the first discharge slits 18 and the second discharge slots 20 open into the same cavity 16 of the cooling circuit of the trailing edge of the blade. More precisely, in this example, which cannot be limited to this supply by a single cavity, the lower walls of the first slots 18 coincide with the upper walls of the adjacent second slits 20 and the upper walls of the first slits 18 coincide with the lower walls of the adjacent second slits 20, so that the second slits exactly occupy each of the radial spaces left between the first slits.
• FIG. 4 shows a third embodiment of the invention in which the first evacuation slots 18 of the cooling circuit of the trailing edge open out at the level of the trailing edge 14 of the vane, while the second slots of evacuation 20 open at the level of the lower surface 6a of the blade 2.
• the blade 2 according to the invention is obtained directly by molding.
• the vane is made by pouring a metal into a mold containing a ceramic core which has the particular function of reserving a location for the circuit.
• blade cooling and in particular for the cavity 16 and the first and second discharge slots 18, 20 of the cooling circuit of the trailing edge of the blade.
• the ceramic core is advantageously produced by additive manufacturing.

Landscapes

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

Applications Claiming Priority (2)

Publications (1)

Family

ID=69468619

Family Applications (1)

Country Status (6)

Family Cites Families (13)

• 2019
  • 2019-07-30 FR FR1908655A patent/FR3099522B1/fr active Active
• 2020
  • 2020-07-22 WO PCT/FR2020/051338 patent/WO2021019156A1/fr unknown
  • 2020-07-22 US US17/597,549 patent/US11913354B2/en active Active
  • 2020-07-22 CA CA3146412A patent/CA3146412A1/fr active Pending
  • 2020-07-22 EP EP20757636.4A patent/EP4004345A1/de active Pending
  • 2020-07-22 CN CN202080055705.7A patent/CN114207249B/zh active Active

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