EP2912281A1 - Boîtier de ventilateur tolérant vis-à-vis du frottement - Google Patents

Boîtier de ventilateur tolérant vis-à-vis du frottement

Info

Publication number
EP2912281A1
EP2912281A1 EP13750773.7A EP13750773A EP2912281A1 EP 2912281 A1 EP2912281 A1 EP 2912281A1 EP 13750773 A EP13750773 A EP 13750773A EP 2912281 A1 EP2912281 A1 EP 2912281A1
Authority
EP
European Patent Office
Prior art keywords
bumper
fan
web
annular
contact surface
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Withdrawn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
EP13750773.7A
Other languages
German (de)
English (en)
Inventor
Michael Edward ERIKSEN
Gerald Alexander PAULEY
Daniel Thomas SCORSE
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP2912281A1 publication Critical patent/EP2912281A1/fr
Withdrawn legal-status Critical Current

Links

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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This invention relates generally to gas turbine engines and more particularly to a containment structure for a fan of a gas turbine engine.
  • a turbofan engine typically includes a fan, a booster, a high pressure compressor, a combustor, a high pressure turbine, and a low pressure turbine in serial axial flow relationship about a longitudinal centerline axis of the engine.
  • the high pressure turbine is drivingly connected to the high pressure compressor via a first rotor shaft
  • the low pressure turbine is drivingly connected to both the fan and booster via a second rotor shaft.
  • the fan includes an annular disk and a plurality of radially extending blades mounted to the disk, wherein the disk and the blades are rotatable about the longitudinal centerline of the engine.
  • Such fans are surrounded by a fan case which is specifically designed to be capable of containing a fan blade in the event that the fan blade is released from its disk during operation. This prevents or minimizes the structural damage to the engine and aircraft should one or more fan blades be released from the disk due to a catastrophic failure of one or more blades, ingestion of debris, or other cause.
  • the fan case also serves as the outer flowpath boundary through the fan rotor and closely circumscribes the tips of the fan blades in order to minimize leakage past the fan blades.
  • Prior art fan cases are typically lined with a sacrificial abradable material in order to protect the fan blades during contact between the fan blades and the fan case (referred to as "rub.") While sacrificial wearing away of the abradable prevents damage to costly fan blades, it also opens up the radial clearance at the blade tips, resulting in loss of engine thrust.
  • a case apparatus for a gas turbine engine includes an annular case having an interior surface with annular recess formed therein; and an annular bumper disposed in the recess, the bumper comprising a frangible material and having a low- friction contact surface, wherein the bumper is configured to permit elastic deflection in response to applied forces below a predetermined threshold.
  • a fan apparatus includes: an annular fan case having an interior surface with annular recess formed therein; an annular bumper disposed in the recess, the bumper comprising a frangible material and having a low- friction contact surface; and a rotor carrying an array of blades mounted for rotation within the case such that the bumper is in axial alignment with tips of the blades, wherein the bumper is configured to permit elastic radial deflection in response to contact between the blades and the bumper generating applied forces below a predetermined threshold.
  • FIG. 1 is a schematic half-sectional view of a fan section of a gas turbine engine incorporating a fan case constructed according to an aspect of the present invention.
  • FIG. 2 is an enlarged view of a portion of a fan case shown in FIG. 1.
  • FIG. 1 shows a portion of an exemplary fan Atty. DM. 261517
  • the fan section 10 of a turbofan gas turbine engine used for powering an aircraft in flight.
  • the fan section 10 includes a fan 12 which is rotated about a central longitudinal axis "A" by a conventional fan shaft 14 powered by a conventional low pressure turbine (not shown).
  • the fan 12 includes a rotor disk 16 from which extends radially outwardly an array of airfoil-shaped fan blades 18 (only one shown in FIG. 1).
  • the rotor disk 16 and the fan blades 18 may be separable from each other or they may be part of an integrally -bladed rotor or "blisk.”
  • Each fan blade 18 has a leading edge 20, a trailing edge 22, a root 24, and a tip 26.
  • GOVs airfoil-shaped outlet guide vanes
  • An annular fan case 28 surrounds the fan 12.
  • the term "annular” refers to a structure with a closed perimeter that is generally ring-shaped and includes both circular and non-circular shapes.
  • the fan case 28 has forward and aft ends 30 and 32.
  • a forward flange 34 mates with a nacelle (not shown) and an aft flange 36 mates with a flange 38 of a downstream engine casing component 40.
  • the fan case 28 has an outer surface 42 and an opposed interior surface 44.
  • the interior surface 44 cooperates with other components, described in more detail below, to define a flowpath surface "F" configured to closely surround the tip 26 of the fan blades 18.
  • the fan case 28 is sized and shaped so as to be able to withstand expected operating loads such as gas pressure loads, body loads, and maneuvering loads.
  • the fan case 28 is also configured to serve as a containment member, or in other words to resist penetration if it should be struck by a fan blade 18 released from the rotor disk 16.
  • a blade release would typically be the result of a foreign object being ingested by the fan 12 during engine operation and is commonly referred to as a "blade-out" event.
  • the fan case 28 is of monolithic construction and is made from an alloy such as aluminum, titanium, or steel. Fan cases may be made from composite materials as well.
  • the term "axial alignment" implies a common or overlapping position of two components as measured along the central longitudinal axis A. Atty. DM. 261517
  • an annular recess 46 is formed in a portion of the interior surface 44 and a bumper 48 is disposed in the recess.
  • the bumper 48 may be an annular component having a contact surface 50 positioned in axial alignment with the fan blades 18.
  • the bumper 48 is configured so as to have low friction at the contact surface 50, to permit elastic radial deflection with linear stress- strain behavior during blade contact under relatively low loads, and to be frangible during blade contact under relatively high loads.
  • the term "low friction" is relative and refers to a generally hard, smooth condition without a rough finish.
  • the bumper 48 has a "hat section" shape including a generally axially-aligned web 52, a pair of spaced-apart, radially-extending legs 54, and optionally a pair of flanges 56 extending axially forward and aft from the distal ends of the legs 54.
  • the flanges 56 are shaped to fit against the interior of the recess 46.
  • the web 52 of the bumper 48 defines the contact surface 50 and is slightly crowned or convex-curved relative to the fan blades 18.
  • the bumper 48 is sized and shaped such that it does not require any change in the recess 46 or the fan case 28 as compared to a prior art fan case design. It use therefore has no significant effect on the containment function of the fan case 28.
  • the bumper 48 is constructed so as to be frangible during a blade impact.
  • frangible refers to a material that will essentially disintegrate into very small, low-mass particles upon failure, i.e. it will experience brittle failure rather than ductile failure.
  • the bumper 48 is made from a composite system, for example intermediate-modulus graphite fibers in a toughened epoxy matrix.
  • the radially-inboard surface of the bumper 48 may incorporate a glass fiber layer to minimize damage to the blade tips 26 in case of contact.
  • the bumper 48 may be secured in position in the recess 46 with a known adhesive.
  • An optional filler 58 is disposed in the annular channel defined by the shape of the bumper 48.
  • the purpose of the filler 58 is to permit control of the bumper's harmonics by providing stiffness and/or damping to the bumper 48.
  • Materials such as composite honeycomb (e.g. incorporating an aramid fiber such as NOMEX) or elastomers may be used for this purpose.
  • the filler 58 may be provided as one piece or as Atty. DM. 261517
  • multiple pieces may be bonded to the bumper 48 and/or the recess 46 using a known adhesive.
  • An abradable material 60 of a known type may be disposed in the recess 46 in the spaces forward and aft of the bumper 48.
  • the abradable material 60 comprises a phenolic resin embedded with glass microspheres.
  • the exposed surface of the abradable material 60 cooperates with the bumper 48 and the interior surface 44 of the fan case 28 to define the flowpath surface F.
  • some or all of the interior surface 44, the abradable material 60, and the bumper 48 may be machined in one or more process steps to form the contours of the flowpath surface F.
  • the bumper 48 In operation, there normally will be no contact between the bumper 48 and the fan blades 18. Occasionally the fan 12 may experience a minor unbalanced condition causing it to deflect radially from a nominal position (i.e. to whirl or gyrate instead of purely rotating). As a result the tips 36 of the fan blades 18 may deflect radially and contact the bumper 48, specifically the web 52.
  • the contact surface 50 of the web 52 is low- friction, allowing the fan blade 18 to skate or skid along its surface, while the legs 54 permit linear elastic deflection of the bumper 48 in the radial direction when the applied forces are below a predetermined threshold.
  • the bumper 48 may thus be considered a "rub tolerant" structure.
  • the action of the bumper 48 prevents the fan blade tip 36 from contacting the abradable material 60. This is desirable as contact with the abradable material 60 causes the radial clearance between the flowpath surface F and the fan blades 18 to open up, and can lead to unacceptable loss of engine thrust.
  • the bumper 48 will act as a frangible fuse. Upon blade contact the bumper 48 will essentially be crushed or disintegrate into very small, low-mass particles. This avoids affecting the fan blade out loads or causing secondary damage.
  • the load at which the bumper 48 will fuse may be on the order of 40-50% greater than the load expected during occasional rubs.
  • the characteristics of the bumper 48 may be adjusted for a particular application by selection of the dimensions of the web 52 and legs 54 as well as the type of composite material, and the number, size, and orientation of plies. Atty. DM. 261517

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention porte sur un appareil de boîtier pour un moteur à turbine à gaz, lequel appareil comprend un boîtier annulaire ayant une surface intérieure avec un creux annulaire formé à l'intérieur de celle-ci ; et un butoir annulaire disposé dans le creux, le butoir comprenant un matériau cassable et ayant une surface de contact à faible frottement, le butoir étant configuré de façon à permettre un infléchissement radial élastique en réponse à des forces appliquées inférieures à un seuil prédéterminé.
EP13750773.7A 2012-09-06 2013-08-01 Boîtier de ventilateur tolérant vis-à-vis du frottement Withdrawn EP2912281A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/604,722 US20140064938A1 (en) 2012-09-06 2012-09-06 Rub tolerant fan case
PCT/US2013/053190 WO2014039188A1 (fr) 2012-09-06 2013-08-01 Boîtier de ventilateur tolérant vis-à-vis du frottement

Publications (1)

Publication Number Publication Date
EP2912281A1 true EP2912281A1 (fr) 2015-09-02

Family

ID=49001051

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13750773.7A Withdrawn EP2912281A1 (fr) 2012-09-06 2013-08-01 Boîtier de ventilateur tolérant vis-à-vis du frottement

Country Status (7)

Country Link
US (1) US20140064938A1 (fr)
EP (1) EP2912281A1 (fr)
JP (1) JP6184036B2 (fr)
CN (1) CN104603400B (fr)
BR (1) BR112015003808A2 (fr)
CA (1) CA2883295A1 (fr)
WO (1) WO2014039188A1 (fr)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10612560B2 (en) * 2015-01-13 2020-04-07 General Electric Company Composite airfoil with fuse architecture
CA2955646A1 (fr) 2016-01-19 2017-07-19 Pratt & Whitney Canada Corp. Boitier d'aube de rotor de turbine a gaz
US10648511B2 (en) 2016-07-15 2020-05-12 Ihi Corporation Seal structure and turbocharger
US10724403B2 (en) 2018-07-16 2020-07-28 Raytheon Technologies Corporation Fan case assembly for gas turbine engine
JP6990639B2 (ja) * 2018-09-26 2022-01-12 本田技研工業株式会社 ターボファンエンジン
US20200308986A1 (en) * 2019-03-26 2020-10-01 Hamilton Sundstrand Corporation Turbine containment arrangement
US11499448B2 (en) * 2019-05-29 2022-11-15 General Electric Company Composite fan containment case
US20240011410A1 (en) * 2022-07-05 2024-01-11 General Electric Company Variable flowpath casings for blade tip clearance control
US12012859B2 (en) 2022-07-11 2024-06-18 General Electric Company Variable flowpath casings for blade tip clearance control
US11808157B1 (en) 2022-07-13 2023-11-07 General Electric Company Variable flowpath casings for blade tip clearance control

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4490092A (en) * 1981-12-21 1984-12-25 United Technologies Corporation Containment structure
US4534698A (en) * 1983-04-25 1985-08-13 General Electric Company Blade containment structure
CA2042198A1 (fr) * 1990-06-18 1991-12-19 Stephen C. Mitchell Ecran protecteur contre les projectiles
US5545007A (en) * 1994-11-25 1996-08-13 United Technologies Corp. Engine blade clearance control system with piezoelectric actuator
US6619913B2 (en) * 2002-02-15 2003-09-16 General Electric Company Fan casing acoustic treatment
GB2407343B (en) * 2003-10-22 2006-04-19 Rolls Royce Plc An acoustic liner for a gas turbine engine casing
US7094033B2 (en) * 2004-01-21 2006-08-22 General Electric Company Methods and apparatus for assembling gas turbine engines
GB0501284D0 (en) * 2005-01-21 2005-03-02 Rolls Royce Plc Aerofoil containment structure
US7909335B2 (en) * 2008-02-04 2011-03-22 General Electric Company Retractable compliant plate seals
US8333558B2 (en) * 2008-03-05 2012-12-18 General Electric Company Containment cases and method of manufacture
GB0914523D0 (en) * 2009-08-20 2009-09-30 Rolls Royce Plc A turbomachine casing assembly
GB0914679D0 (en) * 2009-08-24 2009-09-30 Rolls Royce Plc Adjustable fan case liner and mounting method
GB201103682D0 (en) * 2011-03-04 2011-04-20 Rolls Royce Plc A turbomachine casing assembly
CA2875928C (fr) * 2012-06-21 2017-01-17 Kawasaki Jukogyo Kabushiki Kaisha Carter de ventilateur destine a un moteur d'avion

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
None *
See also references of WO2014039188A1 *

Also Published As

Publication number Publication date
CN104603400A (zh) 2015-05-06
BR112015003808A2 (pt) 2018-04-10
JP2015531444A (ja) 2015-11-02
WO2014039188A1 (fr) 2014-03-13
CN104603400B (zh) 2017-03-08
US20140064938A1 (en) 2014-03-06
CA2883295A1 (fr) 2014-03-13
JP6184036B2 (ja) 2017-08-23

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