EP3309359A1 - Ensemble d'aubes mobiles pour un moteur à turbine à gaz - Google Patents

Ensemble d'aubes mobiles pour un moteur à turbine à gaz Download PDF

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Publication number
EP3309359A1
EP3309359A1 EP17195629.5A EP17195629A EP3309359A1 EP 3309359 A1 EP3309359 A1 EP 3309359A1 EP 17195629 A EP17195629 A EP 17195629A EP 3309359 A1 EP3309359 A1 EP 3309359A1
Authority
EP
European Patent Office
Prior art keywords
stiffening
blade
blade assembly
blade carrier
shaped
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP17195629.5A
Other languages
German (de)
English (en)
Other versions
EP3309359B1 (fr
Inventor
Miklos Gäbler
Sven Brüggmann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP3309359A1 publication Critical patent/EP3309359A1/fr
Application granted granted Critical
Publication of EP3309359B1 publication Critical patent/EP3309359B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/022—Blade-carrying members, e.g. rotors with concentric rows of axial blades
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • F01D25/005—Selecting particular materials
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • 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
    • F05D2250/70—Shape
    • F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped
    • 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
    • F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position
    • 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
    • F05D2300/6032—Metal matrix composites [MMC]

Definitions

  • the invention relates to a blade assembly for an engine with a ring or disc-shaped blade carrier with a plurality of blades.
  • Such a blade assembly is for example part of a compressor or a turbine of the engine, in particular of a gas turbine engine.
  • the blades are thereby provided along a circular line about a central axis of the blade assembly, which central axis usually coincides with a rotational or central axis of the engine.
  • the blade carrier, on which the blade is integrally formed or are fixed to the separately manufactured blades via a respective blade root, has a with respect to the blades radially inwardly in the direction of the central axis extending support portion.
  • This support portion usually forms a part of a disk body, which - taking into account the available space - is formed comparatively large area in order to withstand the loads occurring during operation of the engine, which arise due to the rapid rotation of the blade assembly about the central axis.
  • a stiffening structure with first and second stiffening elements of a metal matrix composite ("MMC") on the blade carrier at a connection region of the carrier portion .
  • MMC metal matrix composite
  • a stiffening element is designed as a fiber reinforced MMC ring and arranged on a respective end face of the blade carrier.
  • two MMC rings are defined in mirror image at a connecting region of a radially inwardly extending support section of a blade carrier, namely on a first front end side and on a second rear end side of the blade carrier.
  • the blade carrier can be acted on with a smaller radial extension of the carrier section with higher rotational speeds and thus higher load capacity.
  • the weight of the blade carrier is significantly lower than with a blade carrier of the same load carrying capacity with a larger carrier section through the MMC rings.
  • the stiffening elements in the form of MMC rings are independently of each other positively fixed to one end face of the support portion and optionally additionally shrunk onto an axially extending projection of the connecting portion.
  • Each MMC ring is axially secured separately on the respective end face of the support section and arranged on a radially outwardly facing transverse direction above the associated axially extending projection on the connection region of the support section.
  • the fixation and in particular axial securing of the individual stiffening elements in the form of the MMC rings is thus comparatively complicated.
  • the manufacture of the blade carrier with the connecting region which is additionally intended to integrate a positive axial securing possibility, is complicated and associated with relatively high costs.
  • the invention is therefore based on the object to provide an improved in this respect blade assembly, with which the aforementioned disadvantages are avoided or at least reduced.
  • a rotor blade assembly for an engine with an annular or disk-shaped blade carrier having a plurality of rotor blades is proposed in which at least two first and second reinforcing elements of a reinforcing structure fixed to a connecting region of a carrier section of a blade carrier are not only connected to the connecting region but the first and second stiffening elements are also additionally connected to each other.
  • the inventive solution according to the first aspect of the invention is based on the basic idea that at the connecting region of the blade carrier - preferably to a radially extending with respect to the central axis transverse direction symmetrically configured and opposing - stiffening elements are arranged on opposite first and second end faces of the blade carrier, the by their additional connection with each other axially (relative to the central axis) are secured.
  • both stiffening elements of the stiffening structure is in this case realized in an embodiment variant via at least one separate connecting element of the stiffening structure which directly connects the two stiffening elements arranged on different end sides and secures them axially against one another. In this way, none of the stiffening elements should be axially displaceable relative to the other stiffening element. Both stiffening elements are thus held in an intended position on the support portion.
  • the solution according to the invention is basically independent of whether the blades are formed integrally with the blade carrier and the blade assembly is thus manufactured in bling or blisk construction or the blades are made separately and fixed to the blade carrier.
  • the annular or disc-shaped blade carrier is equipped with a plurality of individual blades, which are fixed in each case via a blade root of a blade on the blade carrier.
  • An above-mentioned separate connecting element for the connection of the first and second stiffening elements arranged on different end faces of the blade carrier with one another extends in a variant through a passage opening in the support section.
  • This passage opening may be a central passage opening, for example in the form of a bore, through the blade carrier.
  • the at least one separate connecting element then extends, for example, through such a central passage opening of the blade carrier in order to fix the two reinforcing elements axially relative to one another.
  • the at least one separate connecting element at least partially surround the first and second stiffening elements, so that at least parts of both stiffening elements are received in a cross section along the central axis between two sections of the connecting element.
  • the connecting element is, for example, U-shaped in cross-section, so that both stiffening elements arranged on different end sides of the blade carrier are accommodated at least partially between two radially projecting limbs or edges of the connecting element.
  • the at least one connecting element may be designed as a clamping part, which is held positively and / or non-positively on both first and second stiffening elements and respectively on the first or second stiffening element arranged on the connecting area in the direction of the other, second or first stiffening element acting force exerts.
  • the clamping part thus the stiffening elements are clamped against each other, for example.
  • the clamping part itself is in this case held positively and / or non-positively on both first and second stiffening elements, for example by engaging an extension of the clamping member in an opening or groove in the respective stiffening element or vice versa by the engagement of a lateral extension of the respective stiffening element in an opening or Groove of the clamping part.
  • first or second stiffening element is annular.
  • both stiffening elements are annular.
  • the annular design of a single stiffening element per end face has over several, for example, ring-segment-shaped stiffening elements per end face the advantage of easier and faster installation.
  • At least one of the first and second stiffening elements is at least partially made of a metal matrix composite ("metal matrix composite", in short: "MMC").
  • metal matrix composite in short: "MMC”
  • at least one of the first and second stiffening elements may comprise an externally sheathed core of a metal matrix composite material.
  • the core may for example consist of a reinforced MMC-type titanium, that is, in particular of a titanium matrix with ceramic reinforcement.
  • the blade carrier has a center passage extending axially, for example a central passage opening, which is bounded radially by an inner edge of the carrier section.
  • a portion of the first or second stiffening element formed from a metal matrix composite material extends axially below this inner edge of the support section.
  • the metal matrix composite formed portion of the first or second face first or second stiffening element thus extends below the inner edge toward the other face and thus provides support below that inner edge by the metal matrix composite.
  • the extension of the metal matrix composite material in the axial direction below an inner edge of the carrier section can thus serve for additional support underneath the rotor blades and the circumferentially revolving blade row formed therewith and lead to a more robust stiffening structure.
  • the connecting region forms at least one axial projection, which is encompassed by a first or second stiffening element in a form-fitting manner, so that the axial projection is at least partially received between a radially outer and a radially inner portion of this stiffening element.
  • an axially protruding portion of the connecting portion extends between a radially outer and a radially inner portion of the stiffening member.
  • the axial protrusion may be formed, for example, locally in the manner of a web or protruding in an annular manner at the connecting area, and be received for example between the two sections of the stiffening element in a groove-shaped recess of the stiffening element.
  • the positive encircling an axial projection of the connecting region through at least one of the stiffening elements not only allows an improved force introduction into and support by the respective stiffening element, but also an improved connection of the respective stiffening element to the connecting region of the blade carrier.
  • the stiffening element can be simply pushed or pushed axially onto the end face of the blade carrier and onto the at least one axial projection, for example, and is held radially secured on the blade carrier via the positive encompassing of the axial projection.
  • the blade carrier may have a passage opening extending axially relative to the central axis, which is radially delimited by an inner edge of the carrier section, and may be a first or second stiffening element of the stiffening structure with at least one section below axially extend this inner edge of the connection area.
  • a first or second stiffening element of the stiffening structure thus extends here with at least one section axially on the inner edge of the connecting area along an end face in the direction of the other end face of the blade carrier.
  • connection region as well as the axial extent of at least a portion of a first or second stiffening element below an inner edge of the connection region to improve the mountability of the stiffening structure and the load capacity of the blade carrier are otherwise advantageous with an additional connection the arranged on different end faces of the blade carrier first and second stiffening elements combined, but nevertheless also independently thereof implemented.
  • a rotor blade assembly for an engine having a multi-blade annular or disc-shaped blade carrier in which a stiffening structure is provided having at least one stiffening element on a first or second end face of the blade carrier.
  • the connection region according to the second aspect of the invention forms at least one axial projection which is encompassed by the at least one stiffening element so that the axial projection is at least partially received between a radially outer and a radially inner portion of the stiffening element.
  • the blade carrier has a passage opening extending axially relative to the central axis of the blade assembly, which is radially delimited by an inner edge of the carrier section, and the at least one stiffening element of the reinforcing structure having at least one section below this inner Edge of the connection region extends axially, ie from one end face in the direction of the other end face.
  • connection region can basically extend essentially parallel to the central axis and therefore substantially perpendicular to a radially extending end face of the carrier section. However, the axial projection can also assume a deviating from 90 ° angle to the front side.
  • a transition region between a substantially radially extending end-face support surface at the connection region and one end of the projection integrally formed therewith may be concavely curved.
  • the degree of curvature and thus the course of a straight line to this transition region can be chosen differently depending on the engine and / or position of the blade assembly, depending on how strong the forces occurring at the connection area and with which force components, for example, this run radially and tangentially ,
  • a straight line extends at the transition regions at an angle of 0 ° to 45 ° to the radial direction.
  • the degree of curvature and thus the included angle can be done, for example, depending on the manufacturing material used for the stiffening element.
  • the at least one axial projection may be part of a cross-sectionally T-shaped, I-shaped or fir-tree-shaped profile of the connection region.
  • a T-shaped profile two projections extending axially in opposite directions are integrally formed at the connecting portion.
  • at least two or three pairs arranged radially one above the other and spaced apart from each other are provided in opposite directions of axially extending projections, the axial extent of which gradually decreases or increases along a radial direction.
  • a T-shaped, I-shaped or fir-tree-shaped profile of the connection region extends at least in sections along a circular line around the central axis.
  • the connecting region of the ring-shaped or disc-shaped blade carrier is provided with a T-shaped, I-shaped or fir-tree-shaped profile that completely surrounds the circumference.
  • each end face of the blade carrier for example, an annular stiffening element which is provided with a correspondingly corresponding cross-sectional profile as a counterpart and engages around a plurality of axial projections which are defined by the fir-tree-shaped cross-sectional profile of the connecting region.
  • an axial projection of the connection region in particular an axial projection of a T-shaped, I-shaped or fir-tree-shaped cross-sectional profile of the connection region, can be used Sealing elements and / or cooling holes are provided. Cooling openings are then used, for example, to supply cooling air to the blade carrier.
  • a gas turbine engine in which one or more rows of blades of a compressor and / or one or more rows of blades of a turbine compared to previously conventional in practice blade rows significantly reduced in terms of their weight
  • the assembly of the stiffening structure and its axial securing is comparatively easy.
  • each of a blade row forming blade assemblies can be arranged axially behind one another with stiffening structures according to the invention fixed thereto and rotationally fixed to each other.
  • a combination of an inventively designed blade assembly for the formation of a blade row with another, not inventively designed blade assembly of another blade row is possible.
  • FIG. 6 illustrates schematically and in section a gas turbine engine T, in which the individual engine components along a rotational axis or center axis M are arranged one behind the other and the engine T is designed as a turbofan engine.
  • a fan F At an inlet or intake E of the engine T, air is drawn in along an inlet direction R by means of a fan F.
  • This arranged in a fan housing FC fan F is driven by a rotor shaft S, which is rotated by a turbine TT of the engine T in rotation.
  • the turbine TT adjoins a compressor V, which has, for example, a low-pressure compressor 11 and a high-pressure compressor 12, and possibly also a medium-pressure compressor.
  • the fan F supplies air to the compressor V and, on the other hand, a secondary flow channel or bypass channel B for generating the thrust.
  • the bypass channel B in this case extends around a compressor V and the turbine TT comprehensive core engine, which includes a primary flow channel for the supplied through the fan F the core engine air.
  • the turbine TT has a high-pressure turbine 13, a medium-pressure turbine 14 and a low-pressure turbine 15.
  • the turbine TT drives the rotor shaft S and thus the fan F via the energy released during the combustion in order to supply the required thrust via the air conveyed into the bypass duct B. produce.
  • the outlet A in this case usually has a discharge nozzle with a centrally arranged outlet cone C.
  • rotating blade assemblies are known to be used about the central axis M, each having a blade row and in which the blades on a ring-shaped or disc-shaped Blade carrier are provided.
  • the ring-shaped or disk-shaped blade carrier can in principle be integrally bladed and thus be manufactured in bling or blisk construction.
  • the fixing of individual blades via their respective blade root on a ring-shaped or disk-shaped blade carrier is possible.
  • a blade root is inserted axially into a mounting groove of the blade carrier and axially secured to the respective blade carrier.
  • FIG. 5 By way of example, a plurality of rotor blade assemblies 2a, 2b and 2c of the turbine TT arranged one behind the other along the central axis M are illustrated.
  • the Indian FIG. 5 shown section shows only a part above the central axis M in the region of the medium-pressure turbine 14 or the low-pressure turbine 15.
  • the individual blade assemblies 2a, 2b and 2c are non-rotatably connected via flange 4.1 and 4.2 together.
  • each blade assembly 2a, 2b and 2c each have an annular or disc-shaped blade carrier 23, 24 or 25, on the individual blades 20, 21 or 22 of a blade row along a circular line about the central axis M arranged one behind the other and on the respective blade carrier 23, 24 or 25 via a blade root 200, 210 or 220 of a blade 20, 21 or 22 are fixed.
  • the guide blade rows each have guide vanes 30 or 31, which are also peripherally arranged circumferentially along a circular line about the central axis M.
  • each blade carrier 23, 24 or 25 of a prior art blade assembly 2a, 2b or 2c has a radially inwardly extending beam portion 230, 240 or 250.
  • a disk-shaped support portion 250 of the rear blade assembly 2c serves, for example, for the rotatable mounting of the rotatably connected blade assemblies 2a, 2b and 2c.
  • a central through hole 01 or 02 is provided primarily for weight reduction, for example in the form of a bore.
  • each illustrated variants of stiffening structures 5a and 5b that two opposing annular stiffening elements in the form of (MMC) stiffening rings 50 and 51 at the end faces of the respective blade carrier 23 or 24 are arranged.
  • the stiffening rings 50 and 51 are on the one hand directly connected to each other - preferably via at least one additional connecting element.
  • both stiffening rings 50, 51 each surround a connection region 231 or 241 of the respective support section 230 or 240 in a form-fitting manner at least in sections, which has a profile which is continuous in the circumferential direction and has at least two projections extending axially in opposite directions.
  • the connection region 231 is provided with a fir-tree-shaped (cross-sectional) profile, while in the case of the other blade assembly 2b the FIG. 1 a T-shaped cross-sectional profile is provided.
  • each stiffening ring 50, 51 of the respective stiffening structure 5a or 5b a sheathed MMC core 500, for example, a TiMMC core.
  • a sheathed MMC core 500 for example, a TiMMC core.
  • each stiffening ring 50 or 51 extends a stiffening ring 50 or 51 with a Umgriffabêt 50.1 or 51.2 axially below one of the respective passage opening O1 or O2 facing edge of the connecting portion 231 or 241 in the direction of the other end face.
  • a radially inner edge of the respective blade carrier 23 or 24 is thus encompassed by each stiffening ring 50 or 51 at least partially L-shaped.
  • both stiffening rings 50 and 51 each with an encompassing section 50.1 or 51.2, extend axially below the inner edge of the carrier section 231 or 241 of the blade carrier 23 or 24 such that the stiffening rings 50 and 51 abut one another directly via their encompassing sections 50.1 and 51.2.
  • the stiffening rings 50 and 51 provided on both sides of the connecting portion 231 or 241, which are each held in a form-fitting manner to the respective connecting portion 231 or 241, are thus immediately adjacent to each other and the stiffening structure 5a or 5b formed therewith extends completely through the through-hole O1 or O2.
  • stiffening structure 5a or 5b With the stiffening rings 50 and 51 arranged on the end faces of the blade carrier 23 or 24 facing away from one another, radially acting forces can be absorbed in particular.
  • radially acting forces can be absorbed in particular.
  • circumferentially encircling profiling of the connecting portion 231 or 241 but at the same time a simpler installation and simple radial securing of the blade carrier 23 or 24 to be mounted stiffening rings 50 and 51 is given.
  • the connecting region 231 exemplarily illustrated here forms pairs of projections 2310.1 / 2310.2, 2311.1 / 2311.2 and 2312.1 / 2312.2 that extend in opposite directions.
  • Each of these axial projections 2310.1 to 2312.2 protrudes annularly on an end face of the support portion 230.
  • the axial length of the individual axial projections 2310.1 to 2312.1 or 2310.2 to 2312.2 per end face decreases in the radial direction, in the present case radially inwards.
  • a pair of axial protrusions 2312.1 / 2312.2 closest to the through hole O1 have the least axial Extension on and radially further outwardly arranged pairs of axial projections 2311.1 / 2311.2 and 2310.1 / 2310.2 each axially further.
  • each projection 2310.1 to 2312.1 or 2310.2 to 2312.2 engages positively on the respective end side and consequently each projection 2310.1 to 2312.2 is respectively received between a radially further inward and radially further outward portion of the respective stiffening ring 50 or 51.
  • the two stiffening rings 50 and 51 are at least one in the FIGS. 2A and 2B not shown in detail connecting element provided.
  • the two stiffening rings 50 and 51 are additionally connected directly to one another, so that an undesired displacement and in particular a separation of the stiffening rings 50 or 51 from the blade carrier 23 in the axial direction is prevented.
  • Each stiffening ring 50 or 51 is also held on the other stiffening ring 51 or 50 via the at least one connecting element, whereby a displacement is prevented relative thereto.
  • connection element can be used.
  • this individual connection element may extend annularly around the stiffening structure 5a or at least over a large part of a radially inner circumference of the stiffening structure 5a.
  • a plurality of local connection elements for axial securing along the circumference can be provided offset from one another.
  • a connecting element 6 is formed with a U-shaped cross section, as shown in the Figure 2C for the stiffening structure 5b is shown, wherein such a connecting element 6 also in the stiffening structure 5a of FIGS. 2A and 2B can be used.
  • a connecting element 6 is via two legs or edges 60, 61 of the connecting element 6 positively and / or non-positively connected to two stiffening rings 50 and 51.
  • a narrow groove in each edge or legs 60, 61 is provided, in each of which an extension in the form of a circumferentially extending, axially projecting edge or nose of the respective stiffening ring 50, 51 engages.
  • both stiffening rings 50 and 51 are received between the two legs or edges 60, 61 of the connecting element 6.
  • a force can be exerted on each of the stiffening rings 50, 51, which presses the stiffening ring 50, 51 in the direction of the other stiffening ring 51 or 50 via the two end-side engaging and radially extending edges or legs 60, 61.
  • the connecting element 6 thus acts as a clamping part, which biases the two stiffening rings 50 and 51 axially against one another.
  • connection portion 241 provided with no fir-tree-shaped profile, but with a T-shaped profile.
  • the connection area 241 of the Figure 2C thus, there are two protrusions 2410.1 and 2410.2 projecting axially in opposite directions. These are each in this variant, each form-fitting embraced by the associated, arranged on the respective end side reinforcing ring 50 or 51.
  • the respective MMC core 500 of a stiffening ring 50 or 51 extends with at least a portion 500.1 or 500.2 of the metal matrix composite material below the inner edge of the support portion 230 or 240.
  • the MMC core is substantially L-shaped in cross-section.
  • the MMC core 500 of each stiffening ring 50 or 51 is C-shaped in cross-section.
  • the MMC core 500 is only axially adjacent to the connection region 231 and in particular adjacent to the projections 2310.1 to 2312.2 arranged.
  • FIG. 2B the MMC core 500 of a stiffening ring 50 or 51 extends with at least a portion 500.1 or 500.2 of the metal matrix composite material below the inner edge of the support portion 230 or 240.
  • the MMC core is substantially L-shaped in cross-section.
  • the MMC core 500 of each stiffening ring 50 or 51 is C-shaped in cross-section.
  • the MMC core 500 is only axially adjacent to the connection region 231 and in particular adjacent to the projections 2310.1
  • the MMC core 500 is arranged axially next to the connection region 231 and at least partially below the connection region 231 and consequently in particular adjacent to the projections 2310.1 to 2312.2 and at least partially below the projections 2310.1 to 2312.2. Due to the C-shaped cross section, a respective section 500.3 or 500.4 of the MMC core 500 is additionally arranged above a projection 2410.1 or 2410.2 and consequently there is an axial projection 2410.1 or 2410.2 of the respective front or rear End face between two sections 500.1 / 500.3 or 500.2 / 500.4 of the metal matrix composite material.
  • FIGS. 3A and 3B Two different variants of the blade carrier 23 of the blade assembly 2a are illustrated.
  • the blade carrier 23 has a fir-tree-shaped cross-sectional profile extending in the circumferential direction on the connection region 231 for the stiffening structure 5a and its stiffening rings 50 and 51 to be attached here.
  • the blade carrier 23 While in the variant of FIG. 3A the blade carrier 23 is formed with blades 20 integrally formed thereon, the blade carrier 23 has the FIG. 3B a plurality of circumferentially arranged side by side mounting grooves 232 for thereto to be fixed blade roots 200 of the blades 20.
  • a radius Ra is shown for a transition area between a radially extending end face of the support section 230 and a radially outermost projection 2310.1 of an end face, the size of which influences the degree of concavity of the transition area.
  • a geometry of the fir-tree-shaped profile can also be characterized by an angle ⁇ , the two tangents to each other, which are each applied in a cross-sectional view along the central axis M to the ends of the axial projections 2310.1 to 2312.1 or 2310.2 to 2312.2 an end face.
  • the greater the angle ⁇ the greater the axial extent of the fir-tree-shaped profile and / or the greater the gradation in the axial extent between the projections 2310.1 to 2312.1 or 2310.2 to 2312.2 provided on an end face.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP17195629.5A 2016-10-12 2017-10-10 Ensemble d'aubes mobiles pour un moteur à turbine à gaz Active EP3309359B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102016219815.7A DE102016219815A1 (de) 2016-10-12 2016-10-12 Laufschaufelbaugruppe mit ring- oder scheibenförmigem Schaufelträger und radial innenliegender Versteifungsstruktur

Publications (2)

Publication Number Publication Date
EP3309359A1 true EP3309359A1 (fr) 2018-04-18
EP3309359B1 EP3309359B1 (fr) 2019-07-03

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EP17195629.5A Active EP3309359B1 (fr) 2016-10-12 2017-10-10 Ensemble d'aubes mobiles pour un moteur à turbine à gaz

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DE102018205480A1 (de) * 2018-04-11 2019-10-17 Rolls-Royce Deutschland Ltd & Co Kg Laufschaufelbaugruppe mit einem Sperrelement zur axialen Sicherung eines Versteifungselements einer radial innenliegenden Versteifungsstruktur
US11549373B2 (en) 2020-12-16 2023-01-10 Raytheon Technologies Corporation Reduced deflection turbine rotor
CN114934815B (zh) * 2022-05-12 2023-10-31 中国航发四川燃气涡轮研究院 一种金属基复合材料箍环式发动机转子叶环结构

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US5660526A (en) * 1995-06-05 1997-08-26 Allison Engine Company, Inc. Gas turbine rotor with remote support rings

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US10794188B2 (en) 2020-10-06
DE102016219815A1 (de) 2018-04-12
US20180100398A1 (en) 2018-04-12
EP3309359B1 (fr) 2019-07-03

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