WO2013110792A1 - Statorbauteil mit segmentiertem innenring für eine strömungsmaschine - Google Patents
Statorbauteil mit segmentiertem innenring für eine strömungsmaschine Download PDFInfo
- Publication number
- WO2013110792A1 WO2013110792A1 PCT/EP2013/051508 EP2013051508W WO2013110792A1 WO 2013110792 A1 WO2013110792 A1 WO 2013110792A1 EP 2013051508 W EP2013051508 W EP 2013051508W WO 2013110792 A1 WO2013110792 A1 WO 2013110792A1
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- WO
- WIPO (PCT)
- Prior art keywords
- sub
- segments
- stator component
- component according
- inner ring
- Prior art date
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Classifications
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- 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
- F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
- F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
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- 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
- 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
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
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- 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
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- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
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- 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
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- 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
- F05D2240/55—Seals
-
- 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
- F05D2260/30—Retaining components in desired mutual position
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- 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
- F05D2300/20—Oxide or non-oxide ceramics
-
- 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
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/21—Oxide ceramics
-
- 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
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/21—Oxide ceramics
- F05D2300/2112—Aluminium oxides
-
- 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
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/21—Oxide ceramics
- F05D2300/2118—Zirconium oxides
-
- 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
- F05D2300/50—Intrinsic material properties or characteristics
- F05D2300/502—Thermal properties
- F05D2300/5021—Expansivity
- F05D2300/50212—Expansivity dissimilar
Definitions
- the present invention relates to a stator component of a turbomachine according to the preamble of claim 1.
- a turbine housing of an internal combustion engine which is essentially formed by a hot gas duct through which the hot working gases flow. Due to such operation, a lining made of a heat-resistant material is preferably provided on the inner wall surface of this hot gas passage to prevent the remaining metallic surface of the housing from directly contacting with the hot working gases.
- this heat shield lining consists of a plurality of sub-segments, which are arranged on the inner surface of the turbine housing in the circumferential direction, so that they form a ring per se. To avoid problems of thermal expansion at high temperature, the respective sub-segments are circumferentially spaced from each other.
- a turbine housing which consists of a split ring with a plurality of split sub-segments, which are arranged on the inner wall of the gas turbine housing in the circumferential direction at predetermined intervals so that the sub-segments form a ring which is in operative connection with the Blades is standing.
- Each of the sub-segments has in the circumferential direction on two end faces, which face the ends of the adjacent sub-segments.
- At least one of the end surfaces of the subsegment has a transitional surface, which is formed as a cylindrical or spherical surface.
- the invention aims to remedy this situation.
- the invention as characterized in the claims, the object underlying a Statorbauteil, in which a special spacing of the individual sub-segments to each other in the circumferential direction and with respect to the blade tips, in particular the design of the rotor-side surface of the sub-segments, are dispensed with can.
- the object of the invention is also to propose a configuration and constellation of the sub-segments, in which the problems of thermal expansion and compressive stresses can be solved in a simple manner.
- the stator of a turbomachine is formed so that it consists essentially of an outer ring and an inner ring, wherein the outer ring serves as a version of the inner ring formed from individual sub-segments.
- the subsegments are arranged in such a way that, enclosed by the outer ring, they form on the rotor side a continuous circular peripheral surface.
- These sub-segments of the inner ring have a trapezoidal or quasi-trapezoidal cross-section in the radial direction, ie in the installed state in a turbomachine in a section perpendicular to the axis of rotation of the turbomachine, wherein the parallel or quasi-parallel sides of the trapezoid the radial inner or radial outer side of the ring form.
- a self-supporting inner ring under a during operation of the turbomachine in the design point approximately uniform circumferential and radial pressure, a self-supporting inner ring.
- each sub-segment has a substantially planar, concave, convex or spherical surface relative to the inner peripheral surface of the outer ring, wherein the sub-segment itself may consist of a single monolithically constructed material or of several differently dimensioned or composite composite materials.
- the material used for this purpose or the composite materials used for forming such a subsegment have a uniform and / or non-uniform microstructure.
- the subsegment formed in this way has a predeterminable stress and / or expansion behavior as a function of the load ranges of the turbomachine.
- This expansion behavior of the sub-segments can be different in the radial and / or axial direction based on a different structure, this in correlation to the different temperatures, which prevail in the radial and axial direction of the sub-segment.
- the stator of a turbomachine consisting essentially of at least one axial outer ring and an inner ring, wherein the outer ring is used as a version of existing of sub-segments inner ring and wherein the sub-segments are arranged to each other so that they in the installed state rotor side against the rotational movement of Blades form a circular inner ring.
- the sub-segments consist of a uniformly constructed material or at least in the radial direction gradually constructed material or at least in the radial direction of several constructed of different materials sub-bodies.
- the sub-segments thus formed are heated in response to the load ranges of the turbomachine during operation of the turbomachine, so that from radially inside to radially outside a temperature gradient results, the material stratification in the sub-segments is chosen so that the internal materials have a smaller coefficient of expansion than the outer ones, so that the compressive stress resulting from the expansion of the subsegments in the circumferential direction between subsegments of the inner ring assumes a predetermine stress curve,
- the sub-segments abut each other in the circumferential direction to form a point-shaped gap, wherein the spacing in the gap is held so that due to the temperature gradient in operation between the adjacent sub-segments a frictional connection occurs over the entire radial extent or even over radial Sections of the sub-segments now leads to a predetermined course of the compressive stress between sub-segments.
- the sub-segments engage in the circumferential direction to form a toothing, wherein the toothing is spaced in the radial direction so that due to the temperature gradient in operation between the adjacent sub-segments, a frictional connection arises over the entire radial extent or even over radial Sections of the sub-segments leads to a predetermined course of the compressive stress between sub-segments
- the material stratification in the sub-segments is selected so that the inner materials have a smaller coefficient of expansion than the outer, so that the expansion of the sub-segments in the circumferential direction in combination with a circumferentially acute gap between abutting sub-segments, or in Combination with a radially intermeshing with a spaced teeth intermeshing sub-segments, leading to a predetermined course of the compressive stress between sub-segments ..
- a predeterminable course of the compressive stress can be a uniform radial pressure or a practically constant pressure curve. This is, for example, a pressure curve that deviates over at least 80% of the area at which the sub-segments abut each other by no more than 20% of the mean value of the voltage.
- the essential advantage of the invention lies in the fact that the sub-segment formed as an element consists essentially of a ceramic material, which depending on its operational use, especially during the transient load ranges of the turbomachine to full operation, a qualitative and quantitative different behavior with regard to the stress and strain values.
- the ceramic sub-segment will be designed to have a uniform or gradually built-up material structure that allows for a different operating strain and strain behavior.
- the sub-segment can also consist of different nested bodies, which are each constructed of ceramic materials with different chemical and physical properties.
- the incorporated partial bodies for forming a partial segment may also have mutually different material structures, which give a certain physical effect in certain operating conditions.
- a particularly important behavior of such a sub-segment relates to the expansion behavior under different operating conditions of the turbomachine, which are in operative connection with the operating there blades of the turbomachine with respect to the adjusting gap size.
- an operation-dependent expansion behavior of the ceramic element also has a positive effect on the efficiency of the turbomachine, for example, in that the blade tip leaks in the area of the stator / rotor blades can be minimized.
- an element formed from ceramic materials is particularly suitable as a heat shield, in particular when the turbomachine is a gas turbine, since ceramic materials are generally very heat-resistant materials.
- the ceramic element may consist only of a proportion of ceramic, while the remaining portions may consist of less heat-resistant materials.
- strain resp. Voltage behavior must meet such a sub-segment, one behavior can be interpreted in favor of or at the expense of other behavior within acceptable limits.
- the expansion behavior can be provided solely by those material components of the element used, which offer the best conditions on the basis of their chemical and physical properties.
- the element provided as an element can be produced by sintering from pressed ceramic powder, which permits high variability in the choice of material.
- the composition of the element can be varied to work towards different chemical and physical properties of the final material, including porosity, hardness, thermal conductivity or other mechanical, electrical, thermal and / or magnetic properties.
- the ceramic element may also have a solid structure viewed macroscopically, or consist of various macroscopically structured partial bodies, the joining of which results in a firm connection.
- the element may also include targeted structured cavities that can perform various tasks.
- these cavities can be used for internal cooling of the ceramic or quasi-ceramic element, wherein this cooling can also be operated so that at least its expansion behavior is influenced dynamically.
- these cavities are also designed so that they themselves provide a measure of an adaptive strain behavior. A combination of these two structures for a new final purpose is also possible.
- the ceramic or quasi-ceramic element preferably carries an abrasion-compatible layer on the rotor side, which layer is generally designed as a sealing and wearing layer with respect to the rotor blades.
- a good seal is achieved when this wear layer has those properties that match a rubbing layer. This is the case when the wear layer due to the stretching caused by the blade tip notches respectively. Hollows allows, which cause at least in the normal operation of the turbomachine, a maximized seal between the blade tip and element.
- the invention intervenes when it comes to ensuring a maximized seal by the expansion behavior of the element depending on the elongation of the rotor, respectively.
- the blades are supported by internal material dispositions, which additionally support the described effect of the abrasion-compatible layer.
- the rotor-side inner ring is formed by a number of elements, which are preferably of identical shape and size, and have a thickness of 3-8 cm in the radial direction. In the circumferential direction, for example, the elements have an arc angle of 10-15 °, whereby the entire ring will then consist of 24 to 36 individual subsegments.
- the respective ceramic or quasi-ceramic element then preferably has the shape of a trapezoid or a quasi-trapezoid in the radial direction (when installed in a section perpendicular to the axis of rotation of the turbomachine) which then has a positive effect on the prerequisite for a self-supporting structure in connection with the outer ring.
- the rotor-side peripheral surface formed by the sub-segments will form a coherent circular surface for the rotor blades of the turbomachine passing there.
- the rotor-side formed by the elements inner ring consist entirely of a ceramic material.
- compositions of up to 70% or more by weight or by volume may be made of a ceramic material, and the remanence may be 100% dependent on the predefined strain and strain behavior of other materials whose compatibility is matched to the final properties of such element have to be.
- the present description often speaks of quasi-ceramic elements.
- the described stator component can extend as a ring in the axial direction of the turbomachine operatively over all stages of the rotor blades. It is also possible to provide the existing of the sub-segments inner ring in the axial direction only in the area of the operating blades.
- the ceramic or quasi-ceramic elements are enclosed in the radial extent by an outer metal ring, which ensures the stability of the individual elements in the composite. This stability is extremely important, so that the individual elements in the operation mutate into a coherent solid body.
- these elements may have a concave or convex counter-shape, which contributes to the Positioning of these elements relative to the metal ring, in particular during assembly, additionally yield a positive fit.
- the ceramic or quasi-ceramic elements can also, as already briefly tinted above, have intermediate recesses, which can be flowed through as required with a cooling medium.
- grooves can be provided laterally of the individual elements positioned one against the other, which on the one hand reduces the active abutment surface between two adjacent elements, but on the other hand contributes to a defined, richer, positive abutment surface between the two adjacent elements Elements among each other.
- These radially extending grooves can also be used as cooling paths, the cooling of which acts at least in the region of the mutually adjacent elements. This option can also be used to specifically influence the expansion behavior of the elements in certain operational states of the turbomachine.
- the individual elements are to be joined together to form a ring, in which the abutment surfaces of the adjacent elements, in particular during operation of the turbomachine, form a gastight or virtually gas-tight connection.
- the fit in the stator component between the outer ring and the inner ring formed by the subsegments will aim for at least one positive fit during assembly, possibly with an initial minimized traction component, whereby the initial adhesion will increase during operation and must be designed in this way. that a maximum permissible compressive stress between the individual elements is not exceeded.
- the elements in such a way that they can mutate in operation to a cohesive or quasi-cohesive fit, with the quasi-cohesive fit being used for safety reasons, if any.
- the ceramic used for the subsegments it may consist of zirconium oxides, aluminum oxides, magnesium oxides, the subsegment or Shares thereof may also be composed of different proportions of different ceramics.
- the rotor-side surface has a compressive stress of greater than zero MPa to 500 MPa for all operating temperatures due to the thickness ratios, the temperature dependence of the thermal expansion coefficients and the stiffness of all materials, whereby the sub-segment covers the whole operating load range the turbomachine can cover.
- the compressive stress of the sub-segments is limited to each other during the first installation up to 50 MPa, which on the one hand leads to a rich fit, and on the other hand there is a sufficiently large voltage reserve for full operation.
- the materials are layered so that the materials on the radial inner side of the inner ring have the smallest coefficient of thermal expansion and this increases toward the outside.
- the ratios of the expansion coefficients are chosen from the inside to the outside so that the product of expansion coefficient and temperature increase of cold installation and warm operation remains constant or practically constant for all radial positions. For example, deviations from a constant value are to be understood as practically constant, which result in no more than 20% difference between local compressive stresses in the circumferential direction compared to an average compressive stress in the form fit. Edge areas or local defects in the form fit can naturally lead to higher deviations.
- the ratios of the expansion coefficients from the inside to the outside are chosen so that the product of expansion coefficient, circumference and Temperature increase of cold installation and warm operation remains constant or virtually constant for all radial positions.
- the adjacent sub-segments may also have a toothed surface to each other, which leads in the installed state in the radial course to a labyrinth-like seal.
- a toothed surface to each other, which leads in the installed state in the radial course to a labyrinth-like seal.
- the gap size in the radial direction of the sub-segments may be decreasing, in which connection the gap size, ie the spacing between the adjacent sub-segments, undergoes an expansion-moderate superimposition, in particular if the ceramic or quasi-ceramic element consists of different layers in the radial direction Partial bodies of different material composition is, for example, in terms of porosity, particle size, chemical composition, etc.
- FIG. 1 shows a representation of a stator component made of a continuous outer ring and an inner ring consisting of sub-segments
- FIG. 2 shows a representation of a section through a stator component in a radial section
- Fig. 5a shows a further configuration concerning the cooling of the sub-segments and an exit configuration of the coolant from the sub-segment.
- Fig. 1 shows a schematic representation of a metal ring 10, which forms in the region of the individual sub-elements 20, also called sub-segments, as a ring part of the stator.
- this outer ring 10 for a better integration of the annularly mounted sub-elements 20 may be divided 1 or 1 or more times.
- a coherent outer ring 10 is not excluded. However, this requires that the installation of the sub-segments 20 is ensured by precautions during the placement of the last sub-element.
- the outer ring 10 is made of a metallic material, while the sub-segments 20 at least partially made of ceramic materials.
- the outer rings 10 can be arranged so that they are only in operative connection with a blade row.
- the compressive stress of the sub-segments is limited to each other during the first installation to a maximum of 50 MPa, which on the one hand leads to a rich fit, and on the other hand there is a sufficiently large voltage reserve up for full operation.
- the rotor side surface has a compressive stress of greater than zero MPa up to 500 MPA for all operating temperatures due to the thickness ratios, the temperature dependence of the thermal expansion coefficients and the stiffness of all materials Can cover load range of the turbomachine.
- Figure 2 shows a schematic representation of a section of the Statortbaueils in the region of the sub-segment 20.
- the illustrated in Figure 2 made of a ceramic or quasi-ceramic material element forms part of a continuous inner ring, which is particularly apparent in Fig. 1.
- the sub-segment 20 is shown here in the sense of a uniformly constructed body.
- This unitary body may consist of a uniform material or of different materials, the z. B. be joined by sintering to a monolithic body.
- the thus sintered body may then have desired and predefined gradual chemical and physical properties.
- the sub-segment may consist at least in the radial direction of a number of sub-body, which may also consist of different materials with different material structures, with the final purpose that the stress and strain behavior of the inner ring during operation fulfill predeterminable values. Accordingly, such variations may readily affect the sub-segment in the axial direction as well. Furthermore, it is not mandatory that the entire sub-segment 20 must be made integrally of ceramic materials: Configurations can readily be provided in which the incorporation of metallic components, in particular for the predetermination of the stress and strain behavior, can be useful.
- the geometric configuration of the sub-segment 20 has a polygonal shape at least in the radial direction, which deviates from a pure rectangular shape on the corner. This is preferably provided so that the stress critical edges 22 of the sub-segment 20 undergo a significant relief in the installed state.
- sealing elements are provided between outer diameter outer ring and inner diameter inner ring, which generally prevent a radial flow of the working medium from the main flow channel into the stator.
- sealing elements are constituents of positioning elements 23 acting on the sub-segment 20, which ensure that the expansions between the sub-segments and the outer ring can be absorbed at least axially.
- the sealing element is then part of this dynamic positioning element 23, the active effect of the sealing element is maximized in operation.
- the sealing elements are arranged in the region of each sub-segment on both sides thereof and in the circumferential direction.
- the rotor-side surface of the Partial segment has an abradable layer 21, which contributes in certain operating configurations of the turbomachine that by active removal of this layer by the passing past the tip of the blade 30, the gap between the sub-segment and blade tip is minimized and thus the blade tip leakage is minimized.
- the outer ring 10 is further penetrated by a supply channel 24, via which a coolant is introduced to the sub-segments 20.
- Fig. 3 and 4 show an alternative in the combination of adjacent sub-segments, in the sense that no direct form or adhesion is created here during installation, but the sub-segments in the circumferential direction to form a pointed gap 29 more or less loose together.
- This gap 25 runs sharply in the radial direction, wherein the angle ⁇ is held between 5 ° and 30 °.
- the basic idea behind this training is the fact that the strains in the radial direction decrease as a result of the temperature profile, so the spacing must be disposed inside larger than outside.
- the gap formed can be formed over the entire radial extension of the sub-segment as in FIG. But it is also conceivable that the gap is present only over part of the radial extent.
- the gap is formed in the rotor-side region of the sub-segment.
- the gap can be made straight or curved.
- the spacing is maintained so that in operation between the adjacent sub-segments, a frictional connection arises, which leads over the entire radial extent or only over radial portions of the sub-segments to a predetermined course of the compressive stress.
- the compressive stress will be uniform or nearly uniform.
- Figure 4 as a view of the circular surface of the inner ring then shows how a toothing of the two adjacent sub-segments 20 can be performed by a labyrinth curve is created, which prevents the flow of hot working gases between the sub-segments.
- the spacing is maintained so that in operation between the adjacent sub-segments, a frictional connection arises, which now almost uniform over the entire radial extent or even only over radial portions of the sub-segments, just by a initially different gap size is provided, as the arrows at X and Y want to characterize.
- a labyrinth design there does not have to be a force fit everywhere, since the form fit of the labyrinth itself provides the seal.
- FIG. 5 shows FIGS. 5a and 6 a possible cooling configuration of the subsegments starting from the coolant supply channel 24.
- the subsegment 20 then has in the circumferential direction an inner chamber, which is in operative connection with the feed channel 24 and is connected by all subsegments 20, from which angled Branch flow channels 26, which ensure an integral cooling of the sub-segment.
- the cooling medium is then led to the outside via the continuation 27 provided with each flow channel 26.
- FIG. 5 a shows that the chamber 25 a is disposed in each case only for a partial segment 20, so that a corresponding number of supply channels 24 must be provided.
- 20 grooves can also be provided laterally in the region of the radially extending boundary surface of the individual partial segments 20 positioned one on the other, which on the one hand provide the active abutment surface between two reduce adjacent elements, but on the other hand contribute to the fact that it leads to a defined richer positive abutment surface between the elements with each other.
- These radially extending grooves which are not shown in greater detail in the figures, can also be used as cooling paths, the cooling of which acts at least in the region of the sub-segments adjoining one another. This option can also be used to selectively influence the expansion behavior of the subsegments relative to one another in certain operational states of the turbomachine.
- the individual sub-segments should be able to be joined together to form a ring, that the abutment surfaces of the adjacent elements form a gas-tight connection, in particular during operation of the turbomachine, and also leads to a compressive stress which does not exceed 500 MPa.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Iron Core Of Rotating Electric Machines (AREA)
Abstract
Description
Claims
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2014134721A RU2615292C2 (ru) | 2012-01-26 | 2013-01-25 | Деталь статора с сегментированным внутренним кольцом для турбомашины |
CA2860928A CA2860928C (en) | 2012-01-26 | 2013-01-25 | Stator component with segmented inner ring for a turbomachine |
EP13702011.1A EP2807344B1 (de) | 2012-01-26 | 2013-01-25 | Statorbauteil mit segmentiertem innenring für eine strömungsmaschine |
JP2014553740A JP5920856B2 (ja) | 2012-01-26 | 2013-01-25 | ターボ機械用のセグメント化された内環を備えるステータ構成部材 |
KR1020147023793A KR20150002595A (ko) | 2012-01-26 | 2013-01-25 | 터보 기계를 위한 분할된 내부 링을 갖는 스테터 부품 |
CN201380006649.8A CN104066934B (zh) | 2012-01-26 | 2013-01-25 | 用于涡轮机的具有分段式内部环的定子构件 |
US14/335,203 US9702262B2 (en) | 2012-01-26 | 2014-07-18 | Stator component with segmented inner ring for a turbomachine |
Applications Claiming Priority (2)
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EP12152718 | 2012-01-26 | ||
EP12152718.8 | 2012-01-26 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US14/335,203 Continuation US9702262B2 (en) | 2012-01-26 | 2014-07-18 | Stator component with segmented inner ring for a turbomachine |
Publications (1)
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WO2013110792A1 true WO2013110792A1 (de) | 2013-08-01 |
Family
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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PCT/EP2013/051508 WO2013110792A1 (de) | 2012-01-26 | 2013-01-25 | Statorbauteil mit segmentiertem innenring für eine strömungsmaschine |
Country Status (8)
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US (1) | US9702262B2 (de) |
EP (1) | EP2807344B1 (de) |
JP (1) | JP5920856B2 (de) |
KR (1) | KR20150002595A (de) |
CN (1) | CN104066934B (de) |
CA (1) | CA2860928C (de) |
RU (1) | RU2615292C2 (de) |
WO (1) | WO2013110792A1 (de) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
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DE102015201782A1 (de) * | 2015-02-02 | 2016-08-18 | MTU Aero Engines AG | Leitschaufelring für eine Strömungsmaschine |
EP3109520A1 (de) * | 2015-06-24 | 2016-12-28 | MTU Aero Engines GmbH | Dichtungsträger, leitschaufelkranz und strömungsmaschine |
EP3712386A1 (de) * | 2019-03-21 | 2020-09-23 | Pratt & Whitney Canada Corp. | Zwischensegmentendlückenkontrolle einer deckbandsegmentanordnung |
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CA2924866A1 (en) * | 2015-04-29 | 2016-10-29 | Daniel K. Vetters | Composite keystoned blade track |
US10358932B2 (en) * | 2015-06-29 | 2019-07-23 | United Technologies Corporation | Segmented non-contact seal assembly for rotational equipment |
US10287920B2 (en) * | 2015-11-24 | 2019-05-14 | General Electric Company | System of supporting turbine diffuser |
EP3290642A1 (de) * | 2016-08-31 | 2018-03-07 | Siemens Aktiengesellschaft | Ringsegment für eine turbine und anordnung zur äusseren be-grenzung eines strömungspfades einer turbine |
DE102017209682A1 (de) * | 2017-06-08 | 2018-12-13 | MTU Aero Engines AG | Axial geteilter Turbomaschinen-Innenring |
US11015485B2 (en) * | 2019-04-17 | 2021-05-25 | Rolls-Royce Corporation | Seal ring for turbine shroud in gas turbine engine with arch-style support |
JP2023042786A (ja) * | 2021-09-15 | 2023-03-28 | 東芝エネルギーシステムズ株式会社 | タービン段落シール機構およびタービン段落シール機構の製造方法 |
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- 2013-01-25 JP JP2014553740A patent/JP5920856B2/ja not_active Expired - Fee Related
- 2013-01-25 EP EP13702011.1A patent/EP2807344B1/de active Active
- 2013-01-25 CA CA2860928A patent/CA2860928C/en not_active Expired - Fee Related
- 2013-01-25 RU RU2014134721A patent/RU2615292C2/ru active
- 2013-01-25 CN CN201380006649.8A patent/CN104066934B/zh active Active
- 2013-01-25 WO PCT/EP2013/051508 patent/WO2013110792A1/de active Application Filing
- 2013-01-25 KR KR1020147023793A patent/KR20150002595A/ko not_active Application Discontinuation
-
2014
- 2014-07-18 US US14/335,203 patent/US9702262B2/en not_active Expired - Fee Related
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Cited By (6)
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---|---|---|---|---|
DE102015201782A1 (de) * | 2015-02-02 | 2016-08-18 | MTU Aero Engines AG | Leitschaufelring für eine Strömungsmaschine |
US10280775B2 (en) | 2015-02-02 | 2019-05-07 | MTU Aero Engines AG | Guide vane ring for a turbomachine |
EP3109520A1 (de) * | 2015-06-24 | 2016-12-28 | MTU Aero Engines GmbH | Dichtungsträger, leitschaufelkranz und strömungsmaschine |
US10533569B2 (en) | 2015-06-24 | 2020-01-14 | MTU Aero Engines AG | Seal carrier, guide vane ring and turbomachine |
EP3712386A1 (de) * | 2019-03-21 | 2020-09-23 | Pratt & Whitney Canada Corp. | Zwischensegmentendlückenkontrolle einer deckbandsegmentanordnung |
US10876429B2 (en) | 2019-03-21 | 2020-12-29 | Pratt & Whitney Canada Corp. | Shroud segment assembly intersegment end gaps control |
Also Published As
Publication number | Publication date |
---|---|
JP5920856B2 (ja) | 2016-05-18 |
JP2015505588A (ja) | 2015-02-23 |
CN104066934B (zh) | 2016-12-28 |
KR20150002595A (ko) | 2015-01-07 |
CN104066934A (zh) | 2014-09-24 |
EP2807344A1 (de) | 2014-12-03 |
US9702262B2 (en) | 2017-07-11 |
RU2014134721A (ru) | 2016-03-20 |
RU2615292C2 (ru) | 2017-04-04 |
EP2807344B1 (de) | 2022-11-30 |
CA2860928C (en) | 2016-10-18 |
CA2860928A1 (en) | 2013-08-01 |
US20140328672A1 (en) | 2014-11-06 |
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