EP2837773A1 - Ringspaltfüller und zugehörige Stufe und Gasturbinentriebwerk - Google Patents

Ringspaltfüller und zugehörige Stufe und Gasturbinentriebwerk Download PDF

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Publication number
EP2837773A1
EP2837773A1 EP14180628.1A EP14180628A EP2837773A1 EP 2837773 A1 EP2837773 A1 EP 2837773A1 EP 14180628 A EP14180628 A EP 14180628A EP 2837773 A1 EP2837773 A1 EP 2837773A1
Authority
EP
European Patent Office
Prior art keywords
lid
engageable portion
annulus filler
engine
rotor disc
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
EP14180628.1A
Other languages
English (en)
French (fr)
Other versions
EP2837773B1 (de
Inventor
Kristofer Bottome
James Lee
Paul Mason
Ewan Thompson
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
Original Assignee
Rolls Royce PLC
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 PLC filed Critical Rolls Royce PLC
Publication of EP2837773A1 publication Critical patent/EP2837773A1/de
Application granted granted Critical
Publication of EP2837773B1 publication Critical patent/EP2837773B1/de
Not-in-force 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
    • 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
    • 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
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • 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
    • F05D2260/95—Preventing corrosion
    • 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
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F05D2300/434—Polyimides, e.g. AURUM
    • 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 annulus fillers for bridging gaps between adjacent blades of a gas turbine engine.
  • a compressor rotor stage in a gas turbine engine comprises a plurality of radially extending blades mounted on a rotor 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.
  • Annulus fillers of this type are commonly used in the fan stage of gas turbine engines.
  • the fillers may be manufactured from relatively lightweight materials and, in the event of damage, may be replaced independently of the blades.
  • Annulus fillers come in various shapes and sizes depending on the design and construction of the gas turbine engine into which they are inserted.
  • annulus fillers have an outer lid which defines an airflow surface for air being drawn through the engine, the lid having a leading edge and a trailing edge in an axial airflow direction, and a support arrangement which connects directly or indirectly to the rotor disc to support the lid thereon.
  • the support arrangement may comprise one or more of a pin formation (e.g. for attaching the front of the filler to the disc), a mounting ring formation (e.g. for attaching the rear of the filler to the disc), and a hook formation (e.g. for attaching the underside of the filler to the disc).
  • Filler release may result from bird strike on the filler or from excessive blade movement.
  • the filler can be formed of lightweight carbon fibre reinforced composite material.
  • the filler is formed of other materials such as other polymer matrix composites, a problem can then arise of galvanic corrosion between the filler and adjacent, typically metallic, parts of the engine. Similarly, this effect can be seen in reverse with composite adjacent parts of the engine and metallic annulus fillers.
  • a first aspect of the invention provides an annulus filler for mounting to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc, the annulus filler having:
  • a second aspect of the invention provides a stage for a gas turbine engine having:
  • a third aspect of the invention provides a gas turbine engine having the stage of the second aspect.
  • the filler is for mounting to a fan disc and bridging the gap between two adjacent fan blades attached to the fan disc.
  • the adjacent engine parts may be metal parts, e.g. aluminium alloy parts.
  • the adjacent engine part of the first engageable portion may include a nosecone fairing or a makeup piece of a nosecone fairing.
  • the adjacent engine part of the second engageable portion may be a fan rear seal.
  • the annulus filler may be for use with metallic or composite blades.
  • the galvanic corrosion barrier of the first engageable portion may have a reduced coefficient of friction relative to the carbon fibre reinforced composite material to facilitate relative movement between the first engageable portion and the respective adjacent engine part. In this way, wear between the first engageable portion and the respective adjacent engine part can be reduced.
  • the galvanic corrosion barrier of the second engageable portion may have an increased coefficient of friction relative to the carbon fibre reinforced composite material to reduce relative movement between the second engageable portion and the respective adjacent engine part.
  • the second engageable portion can help to dampen any undesirable motion of the respective adjacent engine part, such as flutter.
  • the second engageable portion may be spaced a distance radially inwardly from the respective adjacent engine part at cold build, but the filler may be configured such that, under the centrifugal loading experienced by the filler when the engine rotates, the second engageable portion moves radially outwardly to engage the respective adjacent engine part.
  • the support arrangement of the filler may include one or more straps which, in use, hook onto corresponding formations of the rotor disc.
  • the lid of the annulus filler, and optionally the support arrangement as well, may be substantially entirely formed from polymer matrix composite material, such as carbon fibre reinforced composite material.
  • the galvanic corrosion barrier of the first engageable portion may be formed from a polyimide-based plastic. Additionally or alternatively, the galvanic corrosion barrier of the second engageable portion may be formed from a glass fibre reinforced composite material.
  • the glass fibre reinforced composite material may be co-moulded with the carbon fibre reinforced composite material.
  • a three-shaft ducted fan gas turbine engine incorporating the invention is generally indicated at 10 and 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, an 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 invention can also be applied to other forms of gas turbine engine, such as two-shaft engines.
  • 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 air flow 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.
  • Annulus fillers may be used to bridge the spaces between adjacent blades, for example at the fan 12. This is to ensure a smooth radially inner surface for air to flow over as it passes through the fan 12.
  • Fig. 2 shows an example annulus filler of the present invention.
  • the annulus filler 100 sits between two fan blades 25 and is formed from carbon fibre reinforced composite material.
  • carbon fibre reinforced composite material such as polyethylene, polypropylene, polymethyl methacrylate, polymethyl methacrylate, polymethyl methacrylate, polymethyl methacrylate, polymethyl methacrylate, polymethyl methacrylate, polymethyl methacrylate, polymethyl methacrylate, polystylene-based polystylene, polystylene-based composite, polystylene-based composite and metallic material options can also be used for forming the filler.
  • the filler 100 comprises an outer lid 30 which defines an airflow surface for air being drawn through the gas turbine engine 10, and a support arrangement which includes a body part 32 extending the axial length of the lid.
  • the support arrangement of the filler also includes two axially spaced straps 36 at the radially inward side of the body part 32 which join to complementary hooks 38 on a rotor disc 34.
  • the support arrangement and the rotor disc 34 may each have only one strap/hook, or they may each have more than two straps/hooks.
  • the body part 32 and the lid 30 form a stiff and lightweight box-like structure, which is able to spread and resist the loads on the filler 100.
  • the box-like structure advantageously promotes in-plane tension loading of its composite material under centrifugal loads.
  • the box-like structure can be formed without internal features.
  • the box-like structure, particularly if formed without internal features, is also relatively easy to manufacture, e.g. from an annular arrangement of continuous fibre reinforcement which can then be moulded and machined.
  • the lid may be stitched or z-pinned to the rest of the filler. This can improve the through-thickness strength of the box-like structure, which may be beneficial for hail and birdstrike protection.
  • the support arrangement further includes a first engageable portion 40 at the leading edge of the lid 30 and a second engageable portion 42 at the trailing edge of the lid.
  • the first engageable portion abuts with a support ring 44 attached to the rotor disc 34 and has a pin 43 which fits into a receiving hole formed in the support ring.
  • the first engageable portion also engages a makeup piece 45 which forms an aerodynamic surface between the lid 30 and a spinner fairing 47. Alternatively, the spinner fairing itself may be extended so as to engage with the annulus filler.
  • the second engageable portion engages, in use, with a fan rear seal 46 also attached to rotor disc 34.
  • the fan blades 25 may be metallic or a composite material, e.g. carbon fibre reinforced composite material.
  • a first galvanic corrosion barrier 48 is provided at the first engageable portion 40, as illustrated in Fig. 3 .
  • the first galvanic corrosion barrier 48 is in two parts, a first part 48a being located where the first engageable portion abuts with the support ring 44, and a second part 48b being located where the first engageable portion engages the makeup piece 45.
  • the barrier helps to prevent corrosion by preventing direct contact between the carbon fibres of the composite material of the filler 100 and the metal of the support ring and the makeup piece. However, relative to the composite material, the barrier also has a lower coefficient of friction for sliding against metal. When the filler pivots about the pin 43 (e.g.
  • a suitable material for the low friction first galvanic corrosion barrier 48 can be a polyimide-based plastic, such as VespelTM. However, other materials exhibiting similar characteristics of durability and low friction are also possible.
  • a second galvanic corrosion barrier 49 is provided at the second engageable portion 42, as illustrated in Fig. 4 .
  • the second barrier 49 also helps to prevent corrosion by preventing direct contact between the carbon fibres of the composite material of the filler 100 and the metal of the fan rear seal 46.
  • the second barrier has a higher coefficient of friction relative to the composite material than the first barrier 48, and provides increased friction at the interface between the second engageable portion 42 and the fan rear seal.
  • the second barrier can be a woven glass composite layer, co-moulded with filler outer part 30. The increased friction allows the filler to act as a frictional damper to the fan rear seal. This in turn reduces flutter in the fan rear seal.
  • the second engageable portion 42 fits underneath the fan rear seal 46 and, when the engine is stationary, is spaced a distance radially inwardly therefrom.
  • a nominal cold build clearance may be in the range from 0.5-5.0 mm.
  • the second engageable portion 42 moves outwardly under centrifugal loading.
  • a certain engine speed e.g. about 800 rpm
  • the second engageable portion contacts the fan rear seal 46, and begins to exert a force on the seal.
  • the effect of this force is to change the unsupported length of the seal, as well as to provide a resistive force to any motion, harmonic or otherwise, of the seal.
  • the resistance to such motion is enhanced by the relatively high coefficient of friction of the second barrier 49.
  • damping effects are beneficial to the seal and can increase its life by ⁇ 50%.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP14180628.1A 2013-08-14 2014-08-12 Ringspaltfüller und zugehörige Stufe und Gasturbinentriebwerk Not-in-force EP2837773B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GBGB1314540.4A GB201314540D0 (en) 2013-08-14 2013-08-14 Annulus filler

Publications (2)

Publication Number Publication Date
EP2837773A1 true EP2837773A1 (de) 2015-02-18
EP2837773B1 EP2837773B1 (de) 2016-11-16

Family

ID=49262151

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14180628.1A Not-in-force EP2837773B1 (de) 2013-08-14 2014-08-12 Ringspaltfüller und zugehörige Stufe und Gasturbinentriebwerk

Country Status (3)

Country Link
US (1) US20150050151A1 (de)
EP (1) EP2837773B1 (de)
GB (1) GB201314540D0 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3663530A1 (de) * 2018-12-07 2020-06-10 Safran Aircraft Engines Fan mit zwischenschaufelplatform
FR3102796A1 (fr) * 2019-10-30 2021-05-07 Safran Aircraft Engines Plateformes inter-aubes

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US12012857B2 (en) 2022-10-14 2024-06-18 Rtx Corporation Platform for an airfoil of a gas turbine engine
US12421860B2 (en) 2023-04-27 2025-09-23 Rolls-Royce Plc Annulus filler for a gas turbine engine
US12352175B2 (en) 2023-07-04 2025-07-08 Rolls-Royce Plc Annulus filler for a gas turbine engine

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1013886A2 (de) * 1998-12-24 2000-06-28 ROLLS-ROYCE plc Zwischenschaufelplattform
EP2253802A2 (de) * 2009-05-18 2010-11-24 Rolls-Royce plc Zwischenstück eines Gasturbinenrotors
EP2463482A2 (de) * 2010-12-09 2012-06-13 Rolls-Royce PLC Ringförmiges Füllerelement für eine Rotorscheibe eines Gasturbinentriebwerks
EP2503102A2 (de) * 2011-03-25 2012-09-26 Rolls-Royce plc Rotor mit Plattformen zwischen den Schaufeln
EP2511479A2 (de) * 2011-04-14 2012-10-17 Rolls-Royce plc Ringförmiges Füllsystem
EP2594773A2 (de) * 2011-11-15 2013-05-22 Rolls-Royce plc Ringspalthalter

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0802834D0 (en) * 2008-02-18 2008-03-26 Rolls Royce Plc Annulus filler
GB201020230D0 (en) * 2010-11-30 2011-01-12 Rolls Royce Plc Nose cone assembly

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1013886A2 (de) * 1998-12-24 2000-06-28 ROLLS-ROYCE plc Zwischenschaufelplattform
EP2253802A2 (de) * 2009-05-18 2010-11-24 Rolls-Royce plc Zwischenstück eines Gasturbinenrotors
EP2463482A2 (de) * 2010-12-09 2012-06-13 Rolls-Royce PLC Ringförmiges Füllerelement für eine Rotorscheibe eines Gasturbinentriebwerks
EP2503102A2 (de) * 2011-03-25 2012-09-26 Rolls-Royce plc Rotor mit Plattformen zwischen den Schaufeln
EP2511479A2 (de) * 2011-04-14 2012-10-17 Rolls-Royce plc Ringförmiges Füllsystem
EP2594773A2 (de) * 2011-11-15 2013-05-22 Rolls-Royce plc Ringspalthalter

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
HUTTUNEN-SAARIVIRTA E ET AL: "Corrosion protection of galvanized steel by polyimide coatings: EIS and SEM investigations", PROGRESS IN ORGANIC COATINGS, ELSEVIER BV, NL, vol. 72, no. 3, 18 April 2011 (2011-04-18), pages 269 - 278, XP028312757, ISSN: 0300-9440, [retrieved on 20110422], DOI: 10.1016/J.PORGCOAT.2011.04.015 *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3663530A1 (de) * 2018-12-07 2020-06-10 Safran Aircraft Engines Fan mit zwischenschaufelplatform
FR3089548A1 (fr) * 2018-12-07 2020-06-12 Safran Aircraft Engines Soufflante comprenant une plateforme inter-aubes fixee a l’amont par une virole
US11162418B2 (en) 2018-12-07 2021-11-02 Safran Aircraft Engines Fan comprising an inter-blade platform attached upstream by a ferrule
FR3102796A1 (fr) * 2019-10-30 2021-05-07 Safran Aircraft Engines Plateformes inter-aubes

Also Published As

Publication number Publication date
US20150050151A1 (en) 2015-02-19
EP2837773B1 (de) 2016-11-16
GB201314540D0 (en) 2013-09-25

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