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
  • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
  • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
  • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
• • 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
  • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
• • 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
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/10—Metals, alloys or intermetallic compounds
  • F05D2300/17—Alloys

Definitions

• TITLE Maintenance process for a high-pressure turbine bladed wheel of a turbomachine
• the invention relates to a method of maintaining a high-pressure turbine blade wheel of a turbomachine, such as a turbojet or an aircraft turboprop.
• Figure 1 represents a turbomachine 1 with double flow and double body.
• the axis of the turbomachine is referenced X.
• the terms axial and radial are defined in relation to the axis X.
• the high pressure turbine 6 and the high pressure compressor 4 are coupled in rotation via a first shaft 10 so as to form a high pressure body.
• the low pressure turbine 7, the low pressure compressor 3 and the fan 2 are coupled in rotation via a second shaft (not shown) so as to form a low pressure body.
• the high pressure turbine 6 conventionally comprises a disk 11 on which blades 12 are mounted.
• Each blade 12 comprises a blade 13 extending radially outwards from a blade root 14 mounted in a cell 15 of disc 11.
• the top 16 of the blade 12 is formed by the radially outer end of the blade 12.
• the root 14 and the blade 13 are here separated by a radially internal platform 17.
• the foot 14 has a general fir tree shape , here with four branches or lobes 18.
• the shape of the cell 15 is complementary to the shape of the foot 14.
• Each branch or lobe 18 rests on an opposing complementary surface of the disk 11.
• the surfaces of the foot 14 and of the disk 11 resting on each other are called bearing surfaces 19.
• the foot 14 has four spans 19, arranged symmetrically with respect to a median radial plane P.
• the blades 12 are surrounded by an annular casing 20.
• a clearance j is formed between the vertices 16 of the blades 12 and the casing 20 surrounding the blades 12.
• At least one foil can be mounted between the foot of each blade and the disc, at the level of the corresponding surfaces, all of the foils being removed if the radial clearance is greater than said determined value.
• the foil can have a thickness of between 0.1 and 0.9 mm.
• FIG. 1 is a schematic sectional view of a turbomachine of the prior art
• FIG. 5 is a perspective view of a blade base equipped with two side foils, according to another embodiment
• FIG. 7 is a view corresponding to Figure 3, in which the foil has been removed following a maintenance operation.
• the foil 21 thus has a general shape in II and comprising recesses capable of housing the lobes 18 of the foot 14 of the corresponding blade 12.
• the foil 21 thus has surfaces
• surfaces 22 intended to come into contact with the surfaces of the root 14 of the blade 12. These surfaces are called surfaces 22 of the foil 21.
• the foil 21 is formed by a sheet of thickness between 0.1 and 0.9 mm, and made of a cobalt-based alloy.
• the foot 14 of the blade 12 comes to rest on the bearing surfaces 22 of the foil 21 after assembly in the cell 15.
• the radial position of the top 16 of the blade 12 takes into account the thickness of the foil 21 in its specifications so as to obtain the desired clearance j.
• the foil 21 has a shape complementary to that of the foot 14 and comprises a radial wall 23 capable of forming an axial stop bearing against a radial end surface 24 of the foot 14, which can be an upstream surface or a downstream surface of the foot 14.

Landscapes

• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

Applications Claiming Priority (2)

Publications (2)

Family

ID=82319618

Family Applications (1)

Country Status (5)

Family Cites Families (6)

• 2022
  • 2022-03-18 FR FR2202428A patent/FR3133640A1/fr active Pending
• 2023
  • 2023-03-08 US US18/842,862 patent/US12392253B2/en active Active
  • 2023-03-08 EP EP23713710.4A patent/EP4493797B1/de active Active
  • 2023-03-08 WO PCT/FR2023/050308 patent/WO2023175256A1/fr not_active Ceased
  • 2023-03-08 CN CN202380025717.9A patent/CN118829777A/zh active Pending

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