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
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/08—Cooling; Heating; Heat-insulation
  • F01D25/14—Casings modified therefor
• • 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
  • F01D11/20—Actively adjusting tip-clearance
  • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
• • 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
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/12—Cooling of plants
  • F02C7/16—Cooling of plants characterised by cooling medium
  • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/24—Heat or noise insulation
• • 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
  • F05D2240/15—Heat shield
• • 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
  • F05D2250/10—Two-dimensional
  • F05D2250/14—Two-dimensional elliptical
• • 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
  • F05D2250/30—Arrangement of components
  • F05D2250/32—Arrangement of components according to their shape
  • F05D2250/322—Arrangement of components according to their shape tangential
• • 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
  • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
• • 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
  • F05D2260/231—Preventing heat transfer
• • 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 invention relates to a device for ventilating a turbine casing of a turbomachine and a turbomachine comprising such a device.
• a turbomachine of an aircraft comprises, in known manner, a rotor 1 rotating in the axis of the machine and surrounded by a stator 2.
• the rotor 1 and the stator 2 define between them a gas flow vein 12 which successively traverses a low-pressure compressor 3, a high-pressure compressor 4, a combustion chamber 13, a high-pressure turbine 5 and a combustion turbine. low pressure 6.
• the low-pressure turbine 6 comprises distributor stages 8 (fixed blades) fixed to a turbine casing 7 and alternating with stages of moving blades 9, fixed to the rotor 1, in the axial direction of the machine.
• the turbine casing 7, which delimits the vein 12 for the flow of hot gases, is provided with abradable rings 10 opposite the platform of the blades 9.
• the turbomachine comprises a ventilation device 15 comprising a plurality of perforated ramps 16 arranged around the outer surface of the turbine casing 7. These ramps 16 are fed with pressurized air corresponding to a mixture of a "cold" air stream taken from a peripheral secondary stream downstream of the compressors by means of a sampling point 14, which is a bailer located in the secondary vein 30 and a "hot" air stream taken from the flow line 12 of the hot gases at the high-pressure compressor 5.
• the flow of cold air taken from the secondary vein 30 is conveyed to the ramps via a first conduit 17 and the flow of hot air taken from the flow line 12 of the hot gases is conveyed to the ramps through a second conduit 19.
• a valve 18 to control the permeability of the two ducts to control the temperature of the mixture of the two flows from the two ducts.
• the pressurized air is projected through the perforations of the ramps on the outer surface of the turbine casing and therefore comes to cool it.
• a ramp 16 is typically in the form of a perforated ring at the right of the turbine casing 7 in order to project the air on the turbine casing 7.
• the ventilation device 15 extends around the low pressure turbine 6.
• the ventilation device makes it possible to adjust the clearances between the blades 9 and the abradable 10.
• the changes in the temperature of the casing cause a variation of the clearance between the blades and the blades of the stator. abradable due to the thermal expansion of the stator housing.
• An object of the invention is to improve the known ventilation devices in order to improve the performance of the low pressure turbine and therefore of the turbomachine.
• the invention proposes a device for ventilating a turbine casing of a turbomachine, comprising a plurality of ramps configured to project air onto the turbine casing, the ramps being arranged next to other, each ramp comprising a main ring in which air circulates, the main ring including orifices configured to project an air flow to the turbine casing, the ramp comprising a shield configured to isolate the main ring a flow of air from the turbine casing to the ramps after being projected towards the turbine casing.
• the invention is advantageously completed by the following characteristics, taken alone or in any of their technically possible combination.
• the shield surrounds the main ring and includes orifices aligned with the orifices of the main ring.
• the shield extends tangentially from the openings of the ramp, the shield being in intimate contact with the main ring at the orifices.
• the shield extends tangentially from the ramp from an intimate contact area between the ramp and the shield, diametrically opposed to the orifices.
• the shield section is elliptical.
• the ellipse has a major axis twice the diameter of the section of the ramp.
• a cavity defined between the shield and the ramp is filled with air or argon.
• the invention also relates to a turbomachine comprising a turbine and a device for ventilating a turbine casing according to the invention.
• FIG. 1 illustrating a schematic view of a turbomachine of known type already discussed:
• Figure 2 illustrates an arrangement of ramps in a known type of ventilation device
• Figure 3 illustrates an arrangement of ramps in a ventilation device according to one embodiment of the invention
• FIG. 4 illustrates a ramp of a ventilation device according to one embodiment of the invention.
• FIG. 1 shows a known type of ventilation device comprising ramps 16 which are typically ring-shaped perforated in line with the turbine casing 7 in order to throw air on the turbine casing 7 .
• the Applicant has modified the ramps of FIG. 2 and FIG. 1 (always arranged at the same place in the turbine engine of FIG. 1) in relation to FIG. 3 and proposes a ventilation device comprising a plurality of ramps 16 ', each comprising a main ring 161 in which circulates a flow of air and a shield 162 configured to isolate the main ring from a flow of air from the turbine casing 7 to the ramps 16 'after having been projected towards the turbine casing 7.
• the main ring 161 comprises orifices 17 'configured to project a flow of air towards the turbine casing 7.
• the shield can completely enclose the main ring and includes orifices aligned with the orifices of the main ring.
• the shield 162 extends tangentially from the orifices of the ramp, the shield being in intimate contact with the main ring at the orifices. Such contact makes it possible to limit the loss of load during the expulsion of the air from the main ring towards the turbine casing 7.
• the shield extends tangentially from the ramp from an intimate contact area between the ramp and the shield, diametrically opposed to the orifices.
• Such contact makes it possible to limit the external bulk and makes it possible to benefit in particular from the cold air flowing in the secondary vein above and from the radiation exchange with the nacelle which is cold.
• the latter In order to limit the radial size of the shields, the latter has an elliptical shape. It may also provide a rectangular shape or even oval.
• the ellipse has a major axis twice the diameter of the section D of the ramp.
• the shield 162 may be of the same material as the ramp, for example chromium-based alloy and nickel.
• the shield may be hollow, the cavity 163 defined between the shield and the ramp may be filled with air or argon. However, we prefer air that is a better insulator and has a lower cost.

Landscapes

• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Turbine Rotor Nozzle Sealing (AREA)

Priority Applications (7)

Applications Claiming Priority (2)

Publications (1)

Family

ID=54329831

Family Applications (1)

Country Status (9)

Cited By (2)

Families Citing this family (1)

Citations (4)

Family Cites Families (11)

• 2015
  • 2015-09-15 FR FR1558619A patent/FR3041037B1/fr active Active
• 2016
  • 2016-09-12 WO PCT/FR2016/052292 patent/WO2017046499A1/fr not_active Ceased
  • 2016-09-12 EP EP16774530.6A patent/EP3350417B2/fr active Active
  • 2016-09-12 US US15/760,219 patent/US10677093B2/en active Active
  • 2016-09-12 CA CA2997939A patent/CA2997939C/fr active Active
  • 2016-09-12 JP JP2018532830A patent/JP6864690B2/ja active Active
  • 2016-09-12 RU RU2018113308A patent/RU2691241C1/ru active
  • 2016-09-12 CN CN201680052926.2A patent/CN108026780B/zh active Active
  • 2016-09-12 BR BR112018005031-8A patent/BR112018005031B1/pt active IP Right Grant

Patent Citations (4)

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