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
  • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
  • F01D25/246—Fastening of diaphragms or stator-rings
• • 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
  • F01D11/005—Sealing means between non relatively rotating elements
• • 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
• • 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
  • F05D2230/00—Manufacture
  • F05D2230/60—Assembly methods
• • 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
  • F05D2240/11—Shroud seal segments
• • 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
  • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
  • F05D2300/603—Composites; e.g. fibre-reinforced
  • F05D2300/6033—Ceramic matrix composites [CMC]

Definitions

• This presentation concerns a sealing ring for a turbomachine turbine, in particular a sealing ring for a turbine that can be dismantled upstream.
• turbomachines In order to facilitate maintenance, and thus reduce operating costs, turbomachines have been provided with a sealing ring that can be removed upstream.
• This presentation aims to propose a turbine aimed at solving the above problems.
• the present presentation concerns a turbine for a turbomachine, the turbine having a main axis and comprising a typically annular casing, an upstream ring support, a downstream ring support, a sealing ring, the sealing ring being configured to extend around and come radially opposite a blade of a rotor of the turbine, in which: the upstream ring support and the downstream ring support are mounted against a radially internal surface of the casing, the upstream ring support and the downstream ring support having an upstream end and a downstream end, the ring of seal being configured to be arranged radially between the blade and the casing, and being mounted against the upstream ring support and the downstream ring support, the sealing ring having a maximum radius with respect to the main axis, and the casing being dimensioned so that the maximum radius of the sealing ring is strictly less than the radius of the upstream end of the casing so as to allow mounting by axial insertion, of the sealing ring sealing and the upstream
• the terms “axial”, “radial”, “circumferential”, “interior”, “exterior” and their derivatives are defined in relation to the main axis of the turbomachine; finally, the terms “upstream”, “downstream”, “front” and “rear” are defined in relation to the main axis, according to the general direction of circulation of the fluid within the turbomachine.
• extends axially, radially or circumferentially we understand “extends in a direction having a non-zero component in an axial, radial or circumferential direction”, respectively.
• a circumferential direction is perpendicular to the axial direction and to a radial direction.
• the main axis of the turbomachine corresponds to the axis of rotation of the turbomachine.
• the upstream ring support is circumferential, preferably over 360°.
• the upstream ring support is continuously mounted in support against a radially internal surface of the casing, along a circumference.
• the downstream ring support is circumferential, preferably over 360°.
• the downstream ring support is sectorized.
• upstream ring support and by downstream ring support we mean respectively an upstream support and a downstream support.
• Such sizing of the sealing ring and the casing allows, after dismantling the upstream ring support, to dismantle the sealing ring by translation along the main axis upstream without the casing does not obstruct.
• assembly from the front can be carried out without tilting, allowing more precise, faster assembly and with a reduced risk of damage to parts.
• any characteristic described relating to a disassembly operation is also applicable to an assembly operation carried out in the reverse order, and vice versa.
• Dismantling the sealing ring upstream thus makes it possible to reduce maintenance time and costs compared to a turbine whose sealing ring can only be dismantled downstream.
• the support of the sealing ring on the upstream ring support is a radial support.
• the support of the sealing ring on the downstream ring support is a radial support.
• radial support we mean support on a surface whose normal has a non-zero radial component.
• the radial support has a positive or zero component along the main axis towards the upstream, further facilitating disassembly from the upstream.
• the sealing ring has axial support on the upstream ring support. According to one example, the sealing ring has axial support on the downstream ring support.
• axial support we mean support on a surface whose normal has a non-zero axial component.
• the axial support ensures axial retention on the upstream ring support.
• the turbine comprises at least one seal disposed between the downstream ring support and the radially projecting portion.
• the seal between the downstream ring support and the radially projecting portion ensures sealing despite differential thermal expansion within the turbine causing relative displacements, in particular between the sealing ring and the downstream ring support, which can be compensated by deformation of the seal.
• Differential thermal expansion results from temperature differences between the ring and the downstream ring support as well as materials with different thermal expansion coefficients.
• the seal is an axial seal, that is to say extending axially between two contact surfaces.
• an axial seal is compatible with centering by the sealing ring and the downstream ring support, and the relative axial movements between the sealing ring and the support.
• the downstream ring is thus limited, which reduces the shear forces applied to the seal and improves its lifespan.
• the use of an axial seal at the level of a radial support between the downstream ring support and the sealing ring allows increased sealing and the shear forces applied to the seal are reduced as the direction of support between the downstream ring support and the sealing ring and the direction according to which the joint extends forms an angle close to 90°.
• the seal is in direct contact with the downstream ring support and the radially projecting portion.
• the joint is sectorized.
• the seal is sectored similarly to said part, that is to say comprising sectors at circumferential positions common to the sectors of said room.
• Each sector of a sectored seal can move and deform more independently than for a non-sectored seal, making it possible to ensure better sealing performance.
• the seal is an omega seal.
• omega joint we mean a joint whose transverse section has a shape similar to the omega symbol (Q).
• a transverse section of an omega seal can have an open contour or a closed contour.
• omega joint we can also designate an accordion-shaped joint, that is to say formed of a succession of folds in successively alternating directions, which corresponds to the junction of a plurality of omega joints with contours open.
• An omega seal, and a fortiori an accordion-shaped seal allows sealing to be preserved over a wide range of deformation while ensuring a satisfactory level of sealing.
• the casing is a low pressure turbine casing.
• the blade comprises a ceramic matrix composite (CMC) material.
• CMC material generally comprises fiber reinforcement within a matrix that is at least partly ceramic.
• blades made of CMC materials may be sensitive to damage of the FOD type (for Foreign Object Damage in English, or “Damage caused by foreign bodies”) or of the DOD type (for Domestic Object Damage in English, or “Damage caused by internal bodies”, in this case internal to the turbomachine).
• FOD type for Foreign Object Damage in English, or “Damage caused by foreign bodies”
• DOD type for Domestic Object Damage in English, or “Damage caused by internal bodies”, in this case internal to the turbomachine.
• Facilitated maintenance by upstream assembly is therefore particularly desirable in the case of using CMC blading.
• the sealing ring is sectorized.
• At least one support among the upstream ring support and the downstream ring support is sectorized.
• sectorized we mean formed of sectors linked together.
• sectorized we mean sectored in a circumferential direction around the main axis, that is to say formed of sectors extending along a circumference and connected to each other.
• the sectored sealing ring is less susceptible to thermal expansion than a non-sectored sealing ring, thus minimizing the relative movements between the sealing ring and other internal parts of the turbine during of the life of the turbine, thus facilitating the control of the end clearance of the blade with respect to the sealing ring and ensuring good thermal performance and maintaining the sealing of the turbomachine.
• the support(s) is (are) also less susceptible to thermal expansion, further improving the control of the end clearance of the blade.
• the reduction in displacements associated with reduced thermal expansion also makes it possible to reduce the amplitude of deformations applied to intermediate parts, for example a joint, thereby reducing its fatigue damage.
• the turbine comprises at least one locking member configured to hold together a downstream end of the sealing ring and the downstream ring support.
• the locking member is C-shaped and configured to maintain together in contact, inside the C, a downstream end of the sealing ring and the downstream ring support.
• the turbine comprises at least one locking member configured to hold together an upstream end of the sealing ring and the upstream ring support.
• the locking member is C-shaped and configured to hold together in contact, inside the C, an upstream end of the sealing ring and the upstream ring support.
• the locking member ensures the downstream and/or upstream centering of the sealing ring, thus held in position within the turbine.
• the locking member is a clip.
• Such a locking member is compatible with stable locking and easy removal prior to a maintenance operation on the blade.
• the sealing ring comprises a radially projecting portion, the maximum radius of the sealing ring being equal to the maximum radius of the radially projecting portion at the main axis, c that is to say the distance from the main axis of the position of the radially projecting portion furthest from the main axis.
• the sealing ring comprises a radially projecting portion, the maximum radius of the sealing ring being measured on the radially projecting portion.
• At least one sealing sheet is provided between the seal and the downstream ring support and/or between the seal and the radially projecting portion.
• the sheet ensures good contact with the joint, thus ensuring sealing performance.
• the sheet is a circumferential sheet.
• a circumferential sheet provides the joint with a larger bearing surface, improving its efficiency and reducing its wear.
• the sheet is a non-sectored circumferential sheet.
• sheet metal is invariant by rotation around the principal axis.
• the sheet is detachably mounted on the radially projecting portion, for example the sheet is clipped onto the radially projecting portion.
• the sheet metal is in direct contact with the seal and one of the downstream ring support and the radially projecting portion.
• the measurement of the maximum section of the sealing ring includes the sheet metal mounted on the sealing ring.
• the turbine comprises a sheet mounted between the seal and the downstream ring support.
• downstream end of the sealing ring and a downstream end of the downstream ring support is received in a housing of an exterior platform of a downstream distributor.
• downstream distributor we mean for example a distributor downstream of the sealing ring.
• the housing is a groove in which at least one end is inserted axially.
• This presentation also concerns a turbomachine comprising the turbine according to the present presentation.
• Figure 1 is a half-section view of a turbomachine.
• Figure 2 is a schematic representation in a cross-sectional view comprising the main axis of a low pressure turbine according to a first embodiment.
• Figure 3 is a schematic representation in a cross-sectional view comprising the main axis of a low pressure turbine according to a second embodiment.
• Figure 4 is a schematic representation in a cross-sectional view including the main axis of a low pressure turbine according to a third embodiment.
• Figure 5 is a schematic representation in a cross-sectional view including the main axis of a low pressure turbine according to a fourth embodiment.
• FIG 1 represents a turbomachine 101 in longitudinal half-section along a plane passing through its main axis A1 -A1.
• the turbomachine 101 is a double-body, double-flow turbomachine, but other turbomachines can accommodate a turbine according to one embodiment.
• the turbomachine 101 comprises, from upstream to downstream according to the circulation of the air flow, a fan 102, a low pressure compressor 103 (also called “booster” in English), a high pressure compressor 104, a chamber of combustion 105, a high pressure turbine 106, and a low pressure turbine 107. These different elements are installed inside a nacelle 120, so as to obtain a propulsion assembly comprising the nacelle 120 and the turbomachine 101.
• the air flow Downstream of the blower 102, the air flow is divided into a first air flow part (also called primary flow) F1 passing through the low pressure compressor 103, and a second air flow part (also called secondary flow) F2 flowing in bypass around the low pressure compressor 103.
• first air flow part also called primary flow
• second air flow part also called secondary flow
• the fan 102 and the low pressure compressor 103 are driven by the low pressure turbine 107 via a low pressure main shaft SL, while the high pressure compressor 104 is driven by the turbine high pressure 106 via a high pressure main shaft SH.
• the low pressure main shaft SL typically extends inside the high pressure main shaft SH.
• the low pressure turbine 107 comprises a casing 1, an upstream ring support 3 (or upstream support 3), a downstream ring support 4 (or downstream support 4), a ring sealing 2 and a vane 6.
• the casing 1 is an annular casing having an internal surface.
• the upstream support 3 and the downstream support 4 are mounted to bear against the internal surface of the annular casing 1, thus delimiting a casing segment.
• the upstream support 3 and the downstream support 4 are in contact along a radial normal surface, thus making it easier to assemble and disassemble the parts relative to each other.
• the upstream support 3 may have a radial projection abutting an upstream face of the casing 1, in order to facilitate the correct relative positioning of the different parts of the casing 1 during assembly.
• a blade 6 of a rotor of the turbine 107 is provided inside the casing 1, to draw mechanical power from the combustion gases coming from the combustion chamber by the high pressure turbine.
• the blade 6 is provided in a CMC material.
• the sealing ring 2 is provided radially between the blade 6 and the casing 1.
• An abradable element 11 can be provided between the sealing ring 2 and the blade 6, making it possible to ensure better control of the tolerances relative to the blade 6 and thus limit the flow of leaks bypassing the blade. 6.
• the sealing ring 2 is mounted between the upstream support 3 and the downstream support 4, bearing against the upstream support 3 and the downstream support 4.
• the sealing ring 2 has a radially outermost end, at a distance R1 from the main axis.
• the sealing ring 2 comprises a radially projecting portion 2A, one end of which is at a radially outermost position of the sealing ring 2, at a distance R1 from the main axis.
• the sealing ring 2 is included in a virtual cylinder of revolution centered on the main axis, extending axially in positions common with the sealing ring 2 and of radius equal to the distance R1, the cylinder of revolution being tangent to the sealing ring 2 (and to the radially projecting portion 2A, if applicable) at the radially outermost position.
• the casing 1 can thus be virtually split into an upstream half of the casing 1 and a downstream half of the casing 1, where the upstream half of the casing 1 corresponds to a half of the casing 1 positioned upstream of the end of the casing 1. sealing ring 2 radially outermost, and the downstream half of casing 1 corresponds to a half of casing 1 positioned downstream of the end of sealing ring 2 radially outermost.
• a radially innermost position of the upstream half of casing 1 is located at a distance R2 from the main axis.
• R1 and R2 are provided such that R1 ⁇ R2 (“R1 strictly less than R2”).
• the turbine is dimensioned so that the maximum section of the sealing ring 2 is strictly included in any section of the casing 1 along the main axis upstream of the main axis.
• the turbine is dimensioned so that the maximum radius R1 of the sealing ring 2 is strictly less than the radius R2 of the upstream end of the casing 1, the upstream end corresponding to the upstream half of casing 1.
• the sealing ring 2 can then be dismantled upstream and taken out from the inside of the casing 1 by axial translation towards the upstream, the different means of attachment with the other parts of the turbine, which will be described below, being previously unhooked and/or disassembled.
• the upstream support 3 extends radially, and an interior surface of the upstream support 3 is in contact with an exterior surface of the sealing ring 2.
• the contact surface between the interior surface of the upstream support 3 and the exterior surface of the sealing ring 2 can be provided between two respective ends of the upstream support 3 and the sealing ring 2.
• the surface contact surface can be a radial contact surface.
• radial surface we mean a surface whose normal has a non-zero radial component.
• the locking member 8 can for example be a C-shaped clip, that is to say a clip configured to surround the two respective ends of the sealing ring 2 and the upstream support 3 in order to to keep them in contact with each other.
• the downstream support 4 extends radially, and an interior surface of the casing 1 is in contact with an exterior surface of the downstream support 4.
• the contact surface between the interior surface of the casing 1 and the exterior surface of the downstream support 4 can be provided between two respective ends of the casing 1 and the downstream support 4.
• the contact surface can be a radial contact surface.
• a locking member 8 for example a C-shaped clip.
• a downstream end of the sealing ring 2 is in contact with one end of the downstream support 4.
• the downstream end of the sealing ring 2 has a radial bearing surface on the end of the support downstream 4.
• the radial surface between the sealing ring 2 and the downstream support 4 can be purely radial, that is to say radially normal, or have an inclination so that the surface moves away from the main axis in the upstream direction. In this way, contact against the radial surface does not prevent the upstream dismantling of the sealing ring 2.
• the turbine comprises a distributor 7 which can have a first end inserted in an opening provided in the casing 1, and a second C-shaped end provided so as to enclose the downstream end of the sealing ring 2 and the end of the downstream support 4 in contact with each other.
• the second end of the distributor 7 may include only one branch in contact with an internal surface of the downstream end of the sealing ring 2 alone, as shown in the embodiments of Figures 4 and 5 , or in contact with an internal surface of the end of the downstream support 4 alone.
• the second end of the distributor 7 may comprise only one branch in contact with a radially interior surface, for example a radially interior surface of the end of the downstream support 4 as shown in the embodiment of the figure 3, or a radially interior surface of the end of the sealing ring 2.
• the end of the downstream support 4 can grip the sealing ring 2, as shown in Figure 3. According to one example, the end of the downstream support 4 grips the sealing ring 2 so as to do not obstruct dismantling from upstream
• a seal 5 is provided between the downstream support 4 and the radially projecting portion 2A.
• the seal 5 is provided between an axial surface of the downstream support 4 and an axial surface of the radially projecting portion 2A.
• axial surface we mean a surface whose normal has a non-zero axial component.
• the seal 5 is provided between a radial surface of the downstream support 4 and a radial surface of the radially projecting portion 2A. Such additional contact allows better retention in position
• the seal 5 can for example be an omega seal, in particular an accordion-shaped seal.
• the seal 5 can be in direct contact with the respective axial surfaces of the radially projecting portion 2A and the downstream support 4.
• the seal 5 can also be in contact with these surfaces via sheets.
• the seal 5 can be in contact with at least one of the radial surfaces among the radial surface of the downstream support 4 and the radial surface of the radially projecting portion 2A, in direct contact or via sheets .
• a sheet metal 10 can be provided against the radially projecting portion 2A.
• the sheet metal 10 of the radially projecting portion 2A can for example surround the radially projecting portion 2A like a C-shaped clip, in order to be held in position against the radially projecting portion 2A.
• a sheet metal 10 can be provided against the downstream support 4.
• the metal sheet 10 of the downstream support 4 can for example surround a part of the downstream support 4 like a C-shaped clip, in order to be held in position. position against the downstream support 4.
• the sheets 10 can be circumferential, for example non-sectored circumferential, and thus improve the seal between the downstream support 4 and the sealing ring 2 by improving the seal between the seal 5 and the portion radially projecting 2A and/or by improving the seal between the seal 5 and the downstream support 4.
• the distance R1 can be defined relative to the assembly of the sealing ring 2 and the sheet mounted on the sealing ring 2.
• the distance R1 can be defined at the radially outermost position of the assembly formed by the sealing ring 2 and the sheet 10 mounted on the sealing ring.
• the turbine 107 can be devoid of one or two plates 10 between the downstream support 4 and the sealing ring 2 and between the seal 5 and the radially projecting portion 2A.
• the turbine 107 does not have any sheet metal between the seal 5 and the radially projecting portion 2A.
• the turbines 107 are devoid of metal sheets between the downstream support 4 and the sealing ring 2 and between the seal 5 and the radially projecting portion 2A.
• the turbine 107 can also be without a seal between the sealing ring 2 and the downstream support 3.
• the radially projecting portion 2A can for example have a first radial contact surface with a radially interior part of the downstream support 4, and a second radial contact surface with a radially exterior part of the downstream support 4.
• the radially projecting portion 2A can enclose the downstream support 4, so as to exert a force on the downstream support 4 making it possible to ensure sealing between the downstream support 4 and the sealing ring. 2.
• the downstream support 4 and/or the sealing ring 2 can be sectorized. Where applicable, the number of sectors forming the downstream support 4 is strictly less than the number of sectors forming the sealing ring 2. [0135]

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=85036955

Family Applications (1)

Country Status (4)

Family Cites Families (2)

• 2022
  • 2022-10-24 FR FR2211012A patent/FR3141207B1/fr active Active
• 2023
  • 2023-10-16 CN CN202380078956.0A patent/CN120187937A/zh active Pending
  • 2023-10-16 EP EP23810121.6A patent/EP4609059A1/de active Pending
  • 2023-10-16 WO PCT/FR2023/051605 patent/WO2024089339A1/fr not_active Ceased

Also Published As

Similar Documents

Legal Events