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EP2503102A2 - Rotor doté de plateformes inter-aubes - Google Patents

Rotor doté de plateformes inter-aubes Download PDF

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Publication number
EP2503102A2
EP2503102A2 EP12156804A EP12156804A EP2503102A2 EP 2503102 A2 EP2503102 A2 EP 2503102A2 EP 12156804 A EP12156804 A EP 12156804A EP 12156804 A EP12156804 A EP 12156804A EP 2503102 A2 EP2503102 A2 EP 2503102A2
Authority
EP
European Patent Office
Prior art keywords
rotor
disc
annulus filler
post
annulus
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.)
Withdrawn
Application number
EP12156804A
Other languages
German (de)
English (en)
Other versions
EP2503102A3 (fr
Inventor
Paul Mason
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 EP2503102A2 publication Critical patent/EP2503102A2/fr
Publication of EP2503102A3 publication Critical patent/EP2503102A3/fr
Withdrawn legal-status Critical Current

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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

Definitions

  • This invention relates to a rotor comprising a rotor disc, an array of blades received in blade slots provided in the disc, and annulus fillers disposed between adjacent blades.
  • the invention is particularly, although not exclusively, concerned with a rotor in the form of a fan of a turbofan gas turbine engine.
  • the fan of such an engine typically comprises a rotor disc which has an array of slots at its periphery, which receive individual fan blades.
  • the regions of the disc between the slots constitute posts.
  • annulus fillers it is common for annulus fillers to be provided between adjacent blades of the fan in order to provide an airwashed surface which has the desired aerodynamic profile, and provides a transition between forward and aft components such as a spinner fairing and a fan rear seal.
  • annulus fillers It is known to mount annulus fillers by securing them at their forward and aft ends to the surrounding structure. Annulus fillers are subjected to substantial centrifugal forces as the rotor rotates, and, if they are unsupported between their ends, these centrifugal forces can cause deformation. It is therefore necessary to design the annulus fillers so that they deform under rotation to provide the desired aerodynamic profile. Furthermore, the stresses imposed on the annulus filler during an operating cycle need to be analysed to ensure that the fatigue life of the component lies within acceptable limits.
  • each annulus filler in the form of a structural beam, for example an I-section beam, so that it is resistant to bending. This increases the bulk, and consequently the weight, of the component.
  • An alternative measure is to provide connections, for example in the form of hooks, between the ends of the annulus filler, which engage cooperating formations on the periphery of the rotor disc. It is possible for annulus fillers with such hook connections to be fitted incorrectly, so that they may become detached in operation. Also, the hook connections can be susceptible to Low Cycle Fatigue cracking which, again, can result in release of the annulus filler.
  • the additional diameter means that the effective depth of the blade-retaining slots is increased, which reduces the stability of the cutting tools required to form the slots.
  • the provision of hook features on the rotor disc thus increases the cost of the rotor discs.
  • a rotor disc having an array of blade slots each slot retaining a blade root, in which disc posts are defined between adjacent blade slots and annulus fillers are disposed between adjacent blade slots, each annulus filler comprising a body having an airwashed surface and an oppositely disposed chocking surface which contacts a surface of the respective disc post, the disc post having a post formation extending across the axial width of the disc post, and the annulus filler having an annulus filler formation adjacent the chocking surface which abuts both the post formation and the blade root to retain the annulus filler radially with respect to the disc; in which the chocking surface has at least one contact region (42, 44) in contact with the post formation and at least one non-contact region (24) spaced from the disc post formation.
  • Each disc post may comprise a stem and a head with a larger circumferential dimension than the stem, in which case the channel walls may be directed inwardly of the channel and may engage the disc post beneath the head so that the head is firmly engaged between the channel walls and the chocking surface.
  • the channel walls may be situated at the circumferentially outer edges of the chocking surface.
  • the channel may extend over substantially the full axial extent of the disc post.
  • two of the contact regions are disposed at opposite axial ends of the chocking surface, with the non-contact region, or one of the non-contact regions, disposed between them.
  • Locating means may be provided for establishing the axial position of the annulus filler with respect to the rotor disc.
  • the locating means may comprise an abutment provided at one axial end of the respective disc post, and engaging the respective annulus filler to limit axial displacement of the annulus filler.
  • the locating means may comprise a retaining element fixed to the annulus filler at one axial end of the annulus filler, the retaining element being secured to the rotor disc by a support ring which is releasably secured to the disc.
  • Another form of locating means may comprise a shear key which is fitted to the rotor disc and is accommodated within a recess in at least one of the channel walls.
  • each annulus filler may comprise a box section having an outer wall providing the airwashed surface, an inner wall providing the chocking surface, and oppositely disposed side walls extending between the outer wall and the inner wall.
  • the outer wall may project circumferentially beyond the side walls, and sealing means may be provided between the circumferential edges of the outer wall and respective blades fitted in the blade slots.
  • Each annulus filler may be made from a composite material, for example a fibre reinforced material reinforced with carbon fibre, glass fibre, Kevlar or similar materials.
  • the rotor may be a fan rotor of a gas turbine engine.
  • the present invention also provides an annulus filler for a rotor as defined above.
  • Figure 1 shows a rotor disc 2 of a fan rotor of a gas turbine engine. It will be appreciated that the rotor disc is in the form of an annulus, only part of which is shown in Figure 1 .
  • the rotor disc 2 has a circumferential array of blade slots 4, only two of which are shown in Figure 1 . Between the two slots 4, there is a disc post 6, which comprises a stem or neck 8, and a head 10 which has a larger circumferential dimension of the stem 8.
  • annulus filler 12 is mounted on the post 6.
  • the annulus filler 12 is a box-section component having a trapezoidal cross-section as shown in Figure 2 , which is a sectional view taken approximately half way along the axial length of the annulus filler 12.
  • the annulus filler 12 has an outer wall 14, an inner wall 16, and side walls 18.
  • the side walls 18 extend substantially radially with respect to the central axis of the disc 2.
  • the outer wall 14 presents an airwashed surface 20 over which flows the air stream through the fan in operation.
  • the circumferential edges 22 of the outer wall 14 project in the circumferential direction beyond the side walls 18. Seals (not shown) are provided between each edge 22 and the adjacent blade (not shown) in order to seal the gaps between the annulus filler 12 and the blades.
  • the blades may be provided with short stub platforms which project from the blades towards the edges 22.
  • the inner wall 16 provides a chocking surface 24 which faces the radially outer periphery 26 of the post 6.
  • the channel walls 28 define, with the chocking surface 24, a channel 30 which accommodates the head 10 of the post 6.
  • the channel walls 28 are profiled to conform closely to the contours of the head 10, and consequently are directed inwardly of the channel 30 towards their free edges.
  • the chocking surface 24 does not contact the outer surface 26 of the post 6 at all axial locations.
  • the outer surface 26 is profiled to provide two pedestals 32, 34, between which there is a recess 36, visible also in Figure 2 .
  • the inner wall 16 of the annulus filler 12 includes a joggle 38, which means that the aft region 40 of the inner wall 16 is spaced radially outwardly with respect to the forward region 42.
  • the result is that the chocking surface 24 contacts the outer surface 26 of the post 6 only at the pedestals 32, 34. Nevertheless, the channel walls 28 engage the head 10 of the post 6 over substantially the full axial length of the post 6, so that the annulus filler 12 is retained on the disc 2 in the radial direction, over the full axial length of the inner wall 16.
  • annulus filler 12 By providing contact between the chocking surface 24 and the outer surface 26 only at the separate regions of the pedestals 32, 34, and providing the recessed region 36 between them, installation of the annulus filler 12 is assisted.
  • the annulus filler 12 is fitted to the post 6 by sliding from the forward direction towards the aft direction, and the configuration shown in Figure 3 reduces the frictional resistance to this sliding movement until the raised region 40 of the inner wall 16 contacts the aft pedestal 34.
  • the forward ends of the pedestals 32, 34 are ramped in order to guide the annulus filler 12 so that sequential engagement of the chocking surface 24 first with the pedestal 32 and then with the pedestal 34 is assisted.
  • the head 10 of the post 6 When fitted, the head 10 of the post 6 is firmly engaged within the channel 30 by the chocking action extended between the chocking surface 24 and the channel walls 28.
  • Axial displacement of the annulus filler in the aft direction is limited by an abutment 44 on the head 10.
  • the aft edge of the inner wall 16 contacts the abutment 44, so defining the correctly installed position.
  • This abutment, along with the frictional engagement created by the chocking effect between the chocking surface 24 and the channel walls 28, may be sufficient to retain the annulus filler 12 in the correct position on the disc 2. Nevertheless, additional or alternative fastening measures may be employed, if required.
  • Figure 4 shows an alternative securing means which may be used with, or instead of, the abutment 44.
  • a forward extension 46 is provided on the disc 2.
  • a support ring 48 is secured to the extension 46 and extends around the entire disc 2.
  • the support ring serves to mount further structure on the disc 2, for example a spinner fairing which follows the line of the outer wall 14 of the annulus filler 12 and encloses the forward end of the disc 2.
  • a retaining element in the form of an axial stop lug 50 is secured, for example by adhesive bonding or integral moulding, to the inner wall 16, and is trapped between the disc 2 and the support ring 48.
  • the stop lug 50 thus serves to prevent axial displacement of the annulus filler 12 on the disc 2.
  • Figure 5 shows an alternative retaining measure, in the form of a recess or cut-out 52 in each channel wall 28.
  • a shear key may be provided which acts as a bridge between the disc 2 and the root of a blade accommodated in one of the slots 4.
  • a slot 54 for a shear key is shown in Figure 1 .
  • the shear key extends into the cut-out 52, to anchor the annulus filler 12 axially with respect to the disc 2.
  • Figure 6 is a view from the aft end of the annulus filler 12 shown in Figure 5 , and illustrates the curvature which an annulus filler may have in order to conform to the profiles of adjacent blades.
  • Figure 6 also shows weight-saving apertures 56 provided in the side walls 18 and the inner wall 16 in order to reduce the weight of the annulus filler.
  • the annulus filler 12 may be made from any suitable material such as an aerospace metallic alloy or a composite material.
  • the configuration of the annulus filler 12 lends itself particularly to manufacture from a composite material, for example by lay-up using pre-impregnated pre-forms, or dry pre-forms impregnated with resin in a resin transfer moulding process, or using automated fibre placement techniques.
  • the composite material may comprise carbon fibre, glass fibre, or Kevlar reinforcements. If carbon fibre is used, provision for protection against galvanic corrosion will be required where the annulus filler 12 interfaces with aluminium alloy components.
  • the annulus filler 12 could alternatively be manufactured by an extrusion operation followed by pultruding or hydroforming to shape, or by injection moulding.
  • annulus filler as described above is locked firmly with respect to the disc post 6, and is further retained in position by blade roots accommodated in the blade slots 4 on assembly of the complete fan rotor. Radial loading on the annulus filler 12 is distributed over the full axial length of the disc post 6, so reducing stresses in the annulus filler 12 and enabling significant weight savings. As shown in Figure 2 , the side walls 18 extend radially of the disc 2, with the result that the side walls 18 are able to withstand centrifugal forces without bending stresses, further enabling weight reduction.
  • the geometry of the annulus filler 12 described above is relatively simple compared with known annulus filler components, and consequently manufacturing costs can be reduced. Similarly, the elimination of any requirement for projecting features at the periphery of the fan disc 2 reduces the diameter of the fan disc forging, and reduces the time required for machining complex features such as retaining hooks. Where a shear key is provided, the absence of any hook feature provides greater freedom for the positioning of the shear key slot 54, since it is not necessary to avoid alignment of the shear key slot with the hook features.
  • the annulus filler 12 need not be straight, but could be arcuate, provided that the general cross-section of the disc post 6 is substantially constant over its full length.
  • the local flexibility of the annulus filler can be controlled by varying the thickness of the cross-sections of the outer and inner walls 14, 16 and the side walls 18 in order to accommodate blade rock.
  • Appropriate formations may be provided on the annulus filler 12, such as pips, bumps or ridges, in order to avoid water retention and to mitigate contact fretting.
  • the annulus filler described above comprises the channel 30 which accommodates the head 10 of the disc post 6, other means of retaining the annulus filler 12 radially with respect to the disc 2 may be employed.
  • the post 6 may be a secondary dovetail or retaining post in or on the head 10 for engagement by a complementary formation provided on the annulus filler 12 adjacent the chocking surface 24.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12156804.2A 2011-03-25 2012-02-24 Rotor doté de plateformes inter-aubes Withdrawn EP2503102A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GBGB1104994.7A GB201104994D0 (en) 2011-03-25 2011-03-25 a rotor having an annulus filler

Publications (2)

Publication Number Publication Date
EP2503102A2 true EP2503102A2 (fr) 2012-09-26
EP2503102A3 EP2503102A3 (fr) 2017-08-09

Family

ID=44067330

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12156804.2A Withdrawn EP2503102A3 (fr) 2011-03-25 2012-02-24 Rotor doté de plateformes inter-aubes

Country Status (3)

Country Link
US (1) US20120244003A1 (fr)
EP (1) EP2503102A3 (fr)
GB (1) GB201104994D0 (fr)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2837773A1 (fr) * 2013-08-14 2015-02-18 Rolls-Royce plc Plateforme entretoise annulaire, étage et motor à turbine à gaz associés
FR3029563A1 (fr) * 2014-12-08 2016-06-10 Snecma Plateforme a faible rapport de moyeu
EP3121386A1 (fr) * 2015-07-21 2017-01-25 United Technologies Corporation Plate-forme d'aube de ventilateur avec élément de raidissement, correspondant ensemble et procédé
GB2541114A (en) * 2015-07-08 2017-02-08 Safran Aircraft Engines An aviation turbine engine fan assembly including a fitted platform
US9739162B2 (en) 2013-08-14 2017-08-22 Rolls-Royce Plc Annulus filler
US9752449B2 (en) 2013-08-14 2017-09-05 Rolls-Royce Plc Annulus filler
FR3048997A1 (fr) * 2016-03-21 2017-09-22 Snecma Plateforme d'aube et disque de soufflante de turbomachine aeronautique
EP2463482A3 (fr) * 2010-12-09 2017-12-27 Rolls-Royce plc Elément de remplissage annulaire pour un disque rotor d'un moteur à turbine à gaz
US10458425B2 (en) 2016-06-02 2019-10-29 General Electric Company Conical load spreader for composite bolted joint
US10612558B2 (en) * 2015-07-08 2020-04-07 Safran Aircraft Engines Rotary assembly of an aeronautical turbomachine comprising an added-on fan blade platform
US12012857B2 (en) 2022-10-14 2024-06-18 Rtx Corporation Platform for an airfoil of a gas turbine engine

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130149130A1 (en) * 2011-12-09 2013-06-13 General Electric Company Fan Hub Frame for Double Outlet Guide Vane
US9303531B2 (en) 2011-12-09 2016-04-05 General Electric Company Quick engine change assembly for outlet guide vanes
US9303520B2 (en) 2011-12-09 2016-04-05 General Electric Company Double fan outlet guide vane with structural platforms
FR2991372B1 (fr) * 2012-06-04 2014-05-16 Snecma Roue de turbine dans une turbomachine
WO2014126704A1 (fr) * 2013-02-12 2014-08-21 United Technologies Corporation Aube de ventilateur comprenant des cavités extérieures
WO2015076900A2 (fr) 2013-10-11 2015-05-28 United Technologies Corporation Rotor de ventilateur ayant une fixation de plate-forme intégrée
US10024234B2 (en) * 2014-09-08 2018-07-17 Rolls-Royce Deutschland Ltd & Co Kg Panels of a fan of a gas turbine
US9988920B2 (en) * 2015-04-08 2018-06-05 United Technologies Corporation Fan blade platform seal with leading edge winglet
US10746031B2 (en) 2017-07-18 2020-08-18 Rolls-Royce Corporation Annulus filler
US11078839B2 (en) 2018-01-22 2021-08-03 Rolls-Royce Corporation Composite nosecone
US10724390B2 (en) 2018-03-16 2020-07-28 General Electric Company Collar support assembly for airfoils
US11815017B2 (en) * 2020-04-16 2023-11-14 Rtx Corporation Fan blade platform for gas turbine engine
US11421538B2 (en) 2020-05-12 2022-08-23 Rolls-Royce Corporation Composite aerofoils
US11506083B2 (en) 2020-06-03 2022-11-22 Rolls-Royce Corporalion Composite liners for turbofan engines

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US6832896B1 (en) 2001-10-24 2004-12-21 Snecma Moteurs Blade platforms for a rotor assembly

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FR2608674B1 (fr) * 1986-12-17 1991-04-19 Snecma Roue de turbine a aubes ceramique
GB2299834B (en) * 1995-04-12 1999-09-08 Rolls Royce Plc Gas turbine engine rotary disc
US6290466B1 (en) * 1999-09-17 2001-09-18 General Electric Company Composite blade root attachment
FR2844562B1 (fr) * 2002-09-18 2004-10-29 Snecma Moteurs Maitrise de la position axiale d'une aube de rotor de soufflante
US7094033B2 (en) * 2004-01-21 2006-08-22 General Electric Company Methods and apparatus for assembling gas turbine engines
FR2913735B1 (fr) * 2007-03-16 2013-04-19 Snecma Disque de rotor d'une turbomachine
US8616849B2 (en) * 2009-02-18 2013-12-31 Pratt & Whitney Canada Corp. Fan blade platform

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6832896B1 (en) 2001-10-24 2004-12-21 Snecma Moteurs Blade platforms for a rotor assembly

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2463482A3 (fr) * 2010-12-09 2017-12-27 Rolls-Royce plc Elément de remplissage annulaire pour un disque rotor d'un moteur à turbine à gaz
EP2837773A1 (fr) * 2013-08-14 2015-02-18 Rolls-Royce plc Plateforme entretoise annulaire, étage et motor à turbine à gaz associés
US9739162B2 (en) 2013-08-14 2017-08-22 Rolls-Royce Plc Annulus filler
US9752449B2 (en) 2013-08-14 2017-09-05 Rolls-Royce Plc Annulus filler
FR3029563A1 (fr) * 2014-12-08 2016-06-10 Snecma Plateforme a faible rapport de moyeu
US10253640B2 (en) 2014-12-08 2019-04-09 Safran Aircraft Engines Platform of small hub-tip ratio
GB2541114B (en) * 2015-07-08 2020-04-15 Safran Aircraft Engines An aviation turbine engine fan assembly including a fitted platform
US10612558B2 (en) * 2015-07-08 2020-04-07 Safran Aircraft Engines Rotary assembly of an aeronautical turbomachine comprising an added-on fan blade platform
GB2541114A (en) * 2015-07-08 2017-02-08 Safran Aircraft Engines An aviation turbine engine fan assembly including a fitted platform
US10519784B2 (en) 2015-07-21 2019-12-31 United Technologies Corporation Fan platform with stiffening feature
EP3121386A1 (fr) * 2015-07-21 2017-01-25 United Technologies Corporation Plate-forme d'aube de ventilateur avec élément de raidissement, correspondant ensemble et procédé
US9976426B2 (en) 2015-07-21 2018-05-22 United Technologies Corporation Fan platform with stiffening feature
CN108884720A (zh) * 2016-03-21 2018-11-23 赛峰飞机发动机公司 航空涡轮发动机的叶片平台和风扇盘
WO2017162975A1 (fr) * 2016-03-21 2017-09-28 Safran Aircraft Engines Plateforme, disque et ensemble de soufflante
FR3048997A1 (fr) * 2016-03-21 2017-09-22 Snecma Plateforme d'aube et disque de soufflante de turbomachine aeronautique
RU2728547C2 (ru) * 2016-03-21 2020-07-30 Сафран Эркрафт Энджинз Платформа лопасти и диск вентилятора для авиационного турбинного двигателя
US11021973B2 (en) 2016-03-21 2021-06-01 Safran Aircraft Engines Blade platform and a fan disk for an aviation turbine engine
CN108884720B (zh) * 2016-03-21 2021-11-02 赛峰飞机发动机公司 航空涡轮发动机的叶片平台和风扇盘
EP3433469B1 (fr) * 2016-03-21 2023-04-26 Safran Aircraft Engines Plateforme, ensemble pour soufflante et soufflante
US10458425B2 (en) 2016-06-02 2019-10-29 General Electric Company Conical load spreader for composite bolted joint
US12012857B2 (en) 2022-10-14 2024-06-18 Rtx Corporation Platform for an airfoil of a gas turbine engine

Also Published As

Publication number Publication date
EP2503102A3 (fr) 2017-08-09
GB201104994D0 (en) 2011-05-11
US20120244003A1 (en) 2012-09-27

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