EP2511479B1 - Système de remplissage d'espace annulaire - Google Patents

Système de remplissage d'espace annulaire Download PDF

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Publication number
EP2511479B1
EP2511479B1 EP12160837.6A EP12160837A EP2511479B1 EP 2511479 B1 EP2511479 B1 EP 2511479B1 EP 12160837 A EP12160837 A EP 12160837A EP 2511479 B1 EP2511479 B1 EP 2511479B1
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EP
European Patent Office
Prior art keywords
sleeve
foot
disc
annulus filler
layer
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.)
Active
Application number
EP12160837.6A
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German (de)
English (en)
Other versions
EP2511479A2 (fr
EP2511479A3 (fr
Inventor
Dale Evans
Ian Care
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 PLC
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Rolls Royce PLC
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Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of EP2511479A2 publication Critical patent/EP2511479A2/fr
Publication of EP2511479A3 publication Critical patent/EP2511479A3/fr
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Publication of EP2511479B1 publication Critical patent/EP2511479B1/fr
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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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • 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
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced

Definitions

  • the present invention relates to an annulus filler system for bridging the gap between adjacent blades of a gas turbine engine stage.
  • a ducted fan gas turbine engine generally indicated at 10 has a principal and rotational axis X-X.
  • the engine comprises, in axial flow series, an air intake 11, a propulsive fan 12, an intermediate pressure compressor 13, a high-pressure compressor 14, combustion equipment 15, a high-pressure turbine 16, and intermediate pressure turbine 17, a low-pressure turbine 18 and a core engine exhaust nozzle 19.
  • a nacelle 21 generally surrounds the engine 10 and defines the intake 11, a bypass duct 22 and a bypass exhaust nozzle 23.
  • the gas turbine engine 10 works in a conventional manner so that air entering the intake 11 is accelerated by the fan 12 to produce two air flows: a first air flow A into the intermediate pressure compressor 13 and a second airflow B which passes through the bypass duct 22 to provide propulsive thrust.
  • the intermediate pressure compressor 13 compresses the air flow A directed into it before delivering that air to the high pressure compressor 14 where further compression takes place.
  • the compressed air exhausted from the high-pressure compressor 14 is directed into the combustion equipment 15 where it is mixed with fuel and the mixture combusted.
  • the resultant hot combustion products then expand through, and thereby drive the high, intermediate and low-pressure turbines 16, 17, 18 before being exhausted through the nozzle 19 to provide additional propulsive thrust.
  • the high, intermediate and low-pressure turbines respectively drive the high and intermediate pressure compressors 14, 13 and the fan 12 by suitable interconnecting shafts.
  • a compressor rotor stage comprises a plurality of radially extending blades mounted on a disc.
  • the blades are mounted on the disc by inserting a root portion of the blade in a complementary retention groove in the outer face of the disc periphery.
  • annulus fillers can be used to bridge the spaces between adjacent blades.
  • a seal between the annulus fillers and the adjacent fan blades is also provided by resilient strips bonded to the annulus fillers adjacent the fan blades.
  • Annulus fillers of this type are commonly used in the fan stage.
  • the fillers may be manufactured from relatively lightweight materials and, in the event of damage, may be replaced independently of the blades
  • annulus fillers with features for removably attaching them to the rotor disc.
  • An annulus filler may be provided with a hook member at its axially rear end, the hook member sliding into engagement with part of the rotor disc and/or a component located axially behind the rotor assembly, for example a rear fan air seal.
  • a front attachment disc which is fastened over the fronts of all the annulus fillers located around the rotor disc.
  • US 4655687 proposes an annulus filler that can be fitted to the rotor disc in a radial direction of the disc.
  • the annulus filler that has a salient foot that is shaped similarly to re-entrant grooves formed in the disc rim between pairs of adjacent blades. The foot is proportioned so as to pass radially of the disc through the neck of a respective groove. Wedges positioned between opposing walls of the grooves and respective feet then prevent withdrawal of the feet in a direction radially outwardly of the disc.
  • US6132175 proposes a compliant sleeve for ceramic turbine blades that addresses irregularities between the ceramic blade dovetail and the disc.
  • the sleeve also acts as a compliant member to reduce frettage.
  • US3317988 describes a method of fastening metallic blades into a turbine rotor by filling the gap between the root of the blade and the rotor with a metallic powder.
  • DE19859477 describes a wear-resistant layer that substantially consists of amorphous or amorphous-nanocrystalline metals.
  • EP2154334 describes a two-part annulus filler.
  • An aim of the present invention is to provide annulus fillers that are suitable for use with composite blades, and in particular carbon fibre reinforced plastic (CFRP) blades.
  • CFRP carbon fibre reinforced plastic
  • a first aspect of the present invention provides an annulus filler system for bridging the gap between two adjacent blades attached to a rim of the rotor disc of a gas turbine engine, the system including:
  • the composite material foot (and typically other composite material parts) of the filler can reduce the filler mass.
  • the sleeve enables a filler having at least a composite material foot to be used with, for example, a metal disc by preventing galvanic corrosion between the foot and the disc.
  • the sleeve can also provide a suitable interface between a relatively soft filler foot and a relatively hard disc.
  • the annulus filler system may have any one or, to the extent that they are compatible, any combination of the following optional features.
  • the disc is a metal disc.
  • the foot is formed of fibre-reinforced plastic, e.g. carbon-fibre reinforced plastic. Galvanic corrosion can be a particular problem between carbon fibres and metals.
  • the foot may be proportioned to pass through the neck of the groove in a radial direction on installation of the filler.
  • the sleeve can then be proportioned to prevent withdrawal of the foot through the neck, after installation of the filler, in a radially outward direction of the disc.
  • the groove extends in substantially an axial direction of the engine, i.e. substantially aligned with retention slots in the disc rim for retaining the blades.
  • the groove may follow a straight or a curved path from the front to the rear of the disc.
  • the walls of the groove may be parallel, or the groove may taper from one end to another.
  • the sleeve may have a stop which engages with the rim to prevent the sleeve from sliding beyond its intended location position.
  • the sleeve wraps around the foot to extend from one side of the neck to the other.
  • the sleeve may be configured to protrude past the neck of the groove and to flare outwardly away from the support body. In this way, free edges of the sleeve outside the groove can be kept away from the support body of the annulus filler, avoiding damage to the support body from those edges.
  • the annulus filler may further have sealing strips along the edges of the lid to seal to the adjacent blades.
  • the sleeve has a layer of ballotinis within the galvanic isolation layer.
  • the ballotinis can ensure a minimum thickness for the galvanic isolation layer.
  • the layer of ballotinis may be at the inner surface of the sleeve and contact, in use, the foot.
  • the ballotinis which can be formed e.g. of glass or resin, are generally effective galvanic isolators and can reliably space the foot from other parts of the sleeve which offer less galvanic corrosion protection.
  • the ballotinis may be completely or partially embedded in a matrix such as a layer of resin or an adhesive. For example, with partial embedding, a portion of each ballotini may be proud of the matrix such that only the ballotinis and not the matrix contact the foot. This can help to improve the galvanic isolation of the foot by reducing the foot surface area in contact with the sleeve.
  • a galvanic isolation layer can be provided by: a layer of glass fibre in a non-conductive matrix; a glass layer formed or fused onto the surface of the sleeve; or a paint layer or coating. Whichever type of layer is adopted, it should be resilient to direct loading, for example from forced rocking of the annulus filler by the blades, or from foreign objects impacting the airflow surface of the lid of the filler.
  • the sleeve may be bonded to the foot after the sleeve is located in the gap, e.g. by a resin or adhesive.
  • a resin or adhesive For example, a cyno-acrylic adhesive may be applied to the inner surface of the sleeve before location of the sleeve. The adhesive then cures after location of the sleeve in the presence of water to bond the sleeve to the foot.
  • Such adhesives are relatively strong in tension, helping the sleeve to remain in location in use, but relatively weak in shear, allowing the sleeve to be removed for servicing, inspection or maintenance.
  • the ballotinis may be embedded in the resin or adhesive, such as a paste adhesive.
  • a paste adhesive e.g.
  • a nitrile phenolic adhesive or a two part catalytic set epoxy adhesive such as 3M Scotch-Weld 2216TM or a thermoset epoxy adhesive such as 3M Scotch-Weld AF500TM
  • 3M Scotch-Weld AF500TM thermoset epoxy adhesive
  • the foot may have an outer layer of glass fibre, e.g. woven or braided glass fibre. Such a layer can also improve the galvanic isolation of the foot.
  • the sleeve may have an anti-frettage coating at its outer surface, the anti-frettage coating contacting, in use, the disc.
  • the anti-frettage coating may be formed of molybdenum disulphide, tungsten disulphide or polytetrafluoroethylene.
  • the anti-frettage coating may be selectively located at positions on the outer surface most susceptible to fretting.
  • the anti-frettage coating may be applied e.g. by thermal spraying, PVD or ebPVD, as appropriate.
  • the sleeve may have a main body, for example with the galvanic isolation layer on an inner surface of the body and/or an anti-frettage coating on its outer surface.
  • the main body can be metallic.For example, it can be formed from a conventional titanium alloy, or a high damping alloy such as a titanium-niobium alloy or a titanium-hafnium alloy of the type known as gum metal. A damping alloy can help to resist shear motion at the sleeve-disc interface and hence to reduce fretting. Other metallic or non-metallic materials can be used to form the main body of the sleeve depending on, loading, and filler foot interaction required.
  • the foot has a dovetail-shaped cross-section.
  • the groove can be correspondingly dovetail-shaped in cross-section.
  • the foot may have a circular cross-section, e.g. on a stalk extending from the support body.
  • the lid is formed from fibre-reinforced plastic, e.g. CFRP.
  • the support body may have a pair of side walls, each side wall joining a respective edge of the lid to the foot to give the support body a V-shaped cross-section. As the V-shaped cross-section supports the lid at its edges, the edges of the lid are less likely to disintegrate during an extreme event.
  • the side walls are formed from fibre-reinforced plastic, e.g. CFRP.
  • a cavity formed by the lid and the two side walls contains a foam core, e.g. formed from a plastic material such as a foamed resin or syntactic foam.
  • the foam core can provide a stiffer filler structure, more able to retain its shape.
  • the cavity may contain a chopped fibre composite, e.g. a chopped carbon fibre in a resin such as epoxy.
  • An annulus filler in which the lid, support body and foot are all formed of composite or plastic material can be made very lightweight, helping to increase the efficiency of the engine.
  • a second aspect of the present invention provides a sleeve of the annulus filler system according to the first aspect.
  • a third aspect of the present invention provides a rotor assembly according to the first aspect.
  • a fourth aspect of the present invention provides a rotor assembly for a gas turbine engine including:
  • the rotor disc is a fan disc.
  • the blades may be formed of composite material.
  • FIGS 2 and 3 show schematically perspective views of respectively an annulus filler 30 and a retention sleeve 35 of an annulus filler system according to an embodiment of the present invention.
  • the filler has a lid 31 which, in use, extends between two adjacent composite fan blades, and a support body 32 extending beneath the lid and terminating in an elongate foot 33.
  • the support body is formed by two side walls 34 which join to the lid along respective edges of the lid and meet at the foot to give the body a V-shaped cross-section.
  • the foot has a dovetail cross-section, e.g. with about 55° flank angles.
  • the retention sleeve 35 is shaped to wrap around the foot 33.
  • Figure 4 shows schematically an end on view of the annulus filler 30 and the retention sleeve 35 when fitted to a groove 36 of a metal rotor disc
  • Figure 5 shows schematically a side view on the engine axial line of the fitted filler and sleeve.
  • the groove is dovetail-shaped in cross-section, like the foot 33, and is located on the disc rim in the outside face of post 38 formed between slots 39 which hold the fan blades 40 to the disc.
  • An alternative arrangement has a circular foot cross-section and a correspondingly circular groove cross-section.
  • the groove may follow a straight or a curved path from the front to the rear of the disc, and the sleeve is correspondingly straight or curved.
  • the annulus filler is positioned outwardly of the groove and then moved radially inwardly.
  • the widest part of the foot is proportioned to pass through the neck 41 of the groove so that the foot can be located completely in the groove. This enables fitting annulus fillers between blades that are shaped such that the fillers cannot be slid into position along the groove in a generally rearward direction of the engine.
  • the retention sleeve 35 is slidingly located into the gap formed between the groove and the foot.
  • the sleeve wraps around the foot and protrudes past the neck of the groove to flare outwardly away from the support body so that the free edges 42 of the sleeve are kept away from the support body 32. This helps to prevent the free edges from damaging the support body or posts 38 if there is relative movement between the sleeve and the body.
  • a stop 43 at the end of the sleeve 35 prevents the sleeve from sliding in one direction out of the groove 36. Sliding of the sleeve in the other direction can be prevented by a support ring 44 fitted to the face of the disc 37 after location of the sleeve.
  • the stop and support ring can ensure repeatable axial positioning and retention of the sleeve.
  • the lid 31 of the annulus filler 30 When fitted, the lid 31 of the annulus filler 30 forms a continuous airflow surface along with a nose cone 45 at the front of the lid and a seal ring 46 at the rear of the lid. Sealing strips 47 extending along the edges of the lid seal the lid to the sides of the adjacent blades 40.
  • the foot 33 and groove 36 retention system can distribute loads over the entire axial length of the filler 30.
  • the weight of the filler can be reduced, for example, by forming the lid 31, the side walls 34 and the foot 33 from carbon fibre reinforced plastic.
  • the lid may be secured to the side walls by stitching through laminate layers, which can help to stiffen the edges of the lid, thereby providing a secure base for the sealing strips 47.
  • the cavity formed by the lid and side walls can be filled with a foam core 48 or have an internal lattice structure, which can provide a lightweight resilient support to the lid and side walls. Such support can absorb impact energy and help the lid and side walls to retain their shape after impact deformation.
  • the filler may be produced by foaming the material of the core within a pre-preg envelope of the lid, side walls and foot, and then completing the lid, side walls and foot by resin transfer moulding.
  • the basic filler structure can be formed as a pre-preg tube by 3D Braiding or 3D weaving carbon fibres.
  • An outer layer of glass fibre, e.g. woven or braided glass fibre can be applied to the foot to improve the galvanic isolation of the foot.
  • a former can be placed inside the preform, which is then resin transfer moulded.
  • the foam core is foamed in situ in the cavity and the surfaces sealed.
  • the lid may have a coating, such as an elastomer (e.g. polyurethane), applied to resist sand, debris, and tool drops. Typically the coating would be applied as a sheet or sprayed on.
  • a more sophisticated 3D braided or woven structure can be made to provide internal struts or lattice within the cavity, in which case more than one former may be required during moulding.
  • FIG. 6 shows schematically a transverse cross-section through the sleeve 35.
  • the inner surface of the sleeve is covered with a layer of ballotinis 48.
  • the ballontinis are partially or fully embedded in a layer of resin or adhesive 49 such that the ballotinis ensure a minimum thickness for the galvanic isolation layer formed by the ballotinis and the resin.
  • the galvanic isolation layer isolates the carbon fibres in the foot from the rest of the sleeve and the metal disc 37. If the ballotinis are partially embedded in the resin, only the proud portions of the ballotinis may make contact, in use, with the foot 33. This can reduce the contact area of the foot with the sleeve.
  • a paste adhesive may be used to fill the gaps between the ballotinis and provide a loose bond to the filler foot. Such a paste adhesive is preferably chosen to provide damping to the filler foot.
  • Two sizes of ballotinis may be used: the larger size being only partially embedded and having proud portions penetrating to an extent into the surface of the foot and thereby improving the locking between the foot and the sleeve, and the smaller size being fully embedded with the resin or paste adhesive to ensure a minimum thickness for the galvanic isolation layer.
  • the sleeve has a main body 50 which carries the layer of ballotinis 48 on its inner surface.
  • the main body can be formed, for example, of a conventional titanium alloy, or a high damping alloy such as a titanium-niobium-oxygen alloy or a titanium-hafnium-oxygen alloy.
  • a damping alloy can help to resist shear motion at the sleeve-disc interface and hence to reduce fretting.
  • the outer surface of the main body 50 may be treated with an anti-frettage coating 51, such as molybdenum disulphide, tungsten disulphide or polytetrafluoroethylene.
  • an anti-frettage coating 51 such as molybdenum disulphide, tungsten disulphide or polytetrafluoroethylene.
  • the coating may be applied only where needed rather than over the entire outer surface.
  • the coating may be a sprayed on or applied by PVD/ebPVD.
  • Figure 7 shows schematically a transverse cross-section through another embodiment of the sleeve 35.
  • the sleeve is formed with various layers.
  • the main body 52 is preferably metallic and may, for example, be an alloy of titanium, or a high damping titanium alloy such as Ti 3 (Ta, Nb, V)+(Zr, Hf, O) (known as gum metal).
  • the outer surface of the main body carries an anti-fretting coating 53.
  • the inner surface of the main body carries a galvanic isolation layer 54 formed, for example, by a layer of glass fibre in a non-conductive matrix.
  • the filler may be slid into position along the groove in a generally rearward direction of the engine, i.e. the sleeve may not need to prevent withdrawal of the annulus filler in a radially outward direction.
  • the exemplary embodiments of the invention set forth above are considered to be illustrative and not limiting.

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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)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (9)

  1. Système de charge annulaire comblant l'écart entre deux aubes adjacentes (40) fixées sur le rebord d'un disque de rotor d'un moteur à turbine à gaz, le système comprenant :
    une charge annulaire (30) dotée d'un couvercle (31) s'étendant entre les aubes adjacentes et définissant une surface d'écoulement d'air pour l'air aspiré à travers le moteur, et un corps de support (32) s'étendant sous le couvercle, et aboutissant à une pied allongé (33) qui, lors de l'utilisation, s'étend le long d'une cannelure (36) pratiquée dans le rebord du disque, la cannelure possédant un col (41) empêchant l'extraction du pied à travers le col dans une direction radialement vers l'extérieur du disque, et
    une gaine (35), qui, après l'installation de la charge, peut être positionnée par coulissement dans un écart entre le pied et les côtés de la cannelure ;
    le pied étant composé d'une matière composite ;
    caractérisé en ce que la gaine forme une couche d'isolation galvanique (54), la gaine possédant une couche de microbilles (48) au sein de la couche d'isolation galvanique, qui empêche toute corrosion galvanique entre le pied et le disque.
  2. Système de charge annulaire selon la revendication 1, la matière composite comprenant des fibres de carbone.
  3. Système de charge annulaire selon la revendication 1 ou la revendication 2, la couche d'isolation galvanique étant sélectionnée dans le groupe composé : d'une couche de fibre de verre dans une matrice non conductrice ; d'une couche de verre formée ou fondue sur la surface de la gaine ; ou d'une couche ou d'un revêtement de peinture.
  4. Système de charge annulaire selon une quelconque des revendications précédentes, la couche de microbilles se trouvant à la surface interne de la gaine, et étant en contact, en cours d'usage, avec le pied.
  5. Système de charge annulaire selon une quelconque des revendications précédentes, les microbilles étant encastrées dans un adhésif ou une résine (49).
  6. Système de charge annulaire selon une quelconque des revendications précédentes, la gaine possédant un revêtement anticorrosion par abrasion (51, 53) sur sa surface extérieure, le revêtement anticorrosion par abrasion se trouvant, en cours d'usage, au contact du disque.
  7. Système de charge annulaire selon une quelconque des revendications précédentes, la gaine possédant un corps principal métallique (50, 52) avec la couche d'isolation galvanique sur la surface interne de la gaine.
  8. Système de charge annulaire selon une quelconque des revendications précédentes, le couvercle étant réalisé en plastique renforcé par verre.
  9. Ensemble rotor pour moteur à turbine à gaz, comprenant :
    un disque de rotor,
    une pluralité d'aubes fixées sur un rebord du disque d'un moteur à turbine à gaz, et
    des systèmes de charge annulaire selon une quelconque des revendications 1 à 8 comblant les écarts entre aubes adjacentes ;
    des cannelures respectives étant placées dans le rebord, les pieds des charges annulaires s'étendant le long des cannelures, et les gaines étant situées dans les écarts entre les pieds et les côtés des cannelures.
EP12160837.6A 2011-04-14 2012-03-22 Système de remplissage d'espace annulaire Active EP2511479B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GBGB1106276.7A GB201106276D0 (en) 2011-04-14 2011-04-14 Annulus filler system

Publications (3)

Publication Number Publication Date
EP2511479A2 EP2511479A2 (fr) 2012-10-17
EP2511479A3 EP2511479A3 (fr) 2017-04-19
EP2511479B1 true EP2511479B1 (fr) 2018-01-24

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US (1) US20120263596A1 (fr)
EP (1) EP2511479B1 (fr)
GB (1) GB201106276D0 (fr)

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US20120263596A1 (en) 2012-10-18
EP2511479A2 (fr) 2012-10-17
EP2511479A3 (fr) 2017-04-19
GB201106276D0 (en) 2011-05-25

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