• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a fan housing (1) for an aircraft engine (2) in the region of its fans (3) with a plurality of substantially cylindrically arranged and interconnected layers (3) made of fiber-reinforced plastic. According to the invention, a reinforcing layer (6) of glass-fiber reinforced plastic is arranged between an inner layer (4) and an outer layer (5) and deformation layers (7) are arranged on both sides of the reinforcing layer (6), which deformation layers (7) have lower strength than the reinforcing layer (6) ).
    公开号:AT516322A1
    申请号:T50723/2014
    申请日:2014-10-10
    公开日:2016-04-15
    发明作者:
    申请人:Facc Ag；
    IPC主号:
    专利说明:

    Fan case for an aircraft engine
    The invention relates to a fan housing or fan housing for an aircraft engine in the region of its fans, with a plurality of generally cylindrically arranged and interconnected layers of fiber-reinforced plastic.
    Fan housings of aircraft engines serve to secure the engine in the area of the fan in case of damage of the separation of a blade of the fans from destruction and to protect the passengers on the plane from damage. The materials for such fan housings must be chosen so that the high kinetic energy of the separated fan blade can be absorbed. While metals, especially highly ductile steels or titanium alloys, used to be used mainly for the manufacture of catch casings, more recently plastics have also been used for these aircraft components.
    For example, US 2012/0148392 A1 describes a fan housing for an aircraft engine made of fiber-reinforced plastic, wherein a plurality of interconnected composite layers are combined with honeycomb structures arranged therebetween. A Kevlar® jacket provides adequate protection in the event of damage when a fan blade is separated and enters the engine shell.
    US 2008/0128073 A1 describes a fan housing for aircraft engines of various plastic composite materials in layer construction, wherein different fiber materials and combinations thereof are used.
    Many constructions of fiber-reinforced plastic catcher housings are relatively expensive to produce or require a large number of layers of material, as a result of which the weight advantage over metal catcher housings is no longer or only to a lesser extent.
    The object of the present invention is therefore to provide a catcher housing for an aircraft engine which is as light and secure as possible. Disadvantages of known devices should be avoided or at least reduced.
    The object of the invention is achieved in that between an inner layer and an outer layer, a reinforcing layer is made of glass fiber reinforced plastic, and that on both sides of the reinforcing layer deformation layers are angeord¬net, which deformation layers have lower strength than the reinforcing layer. The inventive design of the fan casing is characterized in that at least three layers, namely the inner layer, the reinforcing layer and the outer layer, are provided, for which special materials are used to achieve the objects according to the invention, namely the protection of the aircraft engine in the event of damage on the one hand, and the preservation of a certain residual rigidity of the aircraft engine for a safe landing, on the other hand. In the snake house according to the invention, the two tasks are divided into two different components, whereby the materials of these components can be optimally adapted to the respective tasks. The medium reinforcing layer made of glass-fiber reinforced plastic serves to protect a separated fan blade from passing through the housing and to overcome the impact. Accordingly, glass fiber reinforced plastic is used, which has the best properties in terms of impact of a fan part. Due to the location of the reinforcing layer with the surrounding deformation layers inside the snake shell, it is also protected from damage, such as rockfalls, and the weight advantage can thereby be achieved. The residual rigidity necessary for a safe landing in case of damage, on the other hand, is largely ensured by the outer layer of the fan casing. The present invention is particularly preferred for aircraft engines of very high speed (> 10000 revolutions per minute) in which the kinetic energy of a severed part of the fan is particularly high. Depending on the design, the weight of the fan casing can be reduced by between 30% and 50% compared to steel constructions and up to 10% in titanium constructions.
    At least one deformation layer may be formed by a honeycomb structure. Such a honeycomb structure is characterized by particularly low weight. In the event of damage, the deformation layer is correspondingly deformed and at least the outer layer of the fan casing is protected against impermissibly large deformation.
    At least one deformation layer can also be formed by Schaummateri¬al. By choosing appropriate foam materials and at most a combination with the honeycomb deformation layer, the weight or the deformability can be further improved. As foam materials, for example, plastics such as acrylonitrile-butadiene-styrene copolymer (ABS), polymethacrylimide (PMI) and the like are used.
    Preferably, the reinforcing layer of the fan housing consists of at least 20 layers of glass fiber reinforced plastic. By arranging layers of glass fiber reinforced plastic, the usually necessary strengths are achieved. In particularly high-speed aircraft engines or for smaller Busi¬ness jets and more layers, for example, 35 layers, may be required to meet the safety requirements.
    Advantageously, at least one fastening flange is integrated in the outer layer. By integrating at least one attachment flange, in particular two attachment flanges (front and rear), on the one hand the strength of the entire barrel housing is increased, since no joints between the fastening flange and the outer layer are required, and on the other hand simplifies the assembly process.
    An abrasive layer of deformable material may be disposed on the inner layer of the fan casing in the region of the fan. Such an abrasive layer of deformable material can further reduce the air gap between the fan of the aircraft engine and the inner layer of the fan casing, since the fan blade with the largest outer diameter ent¬ milling the speaking shape into the grinding layer.
    The abrasive layer can be formed from glass fiber reinforced resin or filled honeycomb cores. Such materials have proven particularly useful and are sufficiently soft compared to the fan blades usually made of titanium or titanium alloys.
    If between the inner layer and the reinforcing layer in the area of the fan a deflection ring made of a material with higher strength than the deformation layers is arranged, the safety in the case of breakage of a fan blade can be increased or material in the inner layer and / or reinforcing layer be saved with the same security. The deflecting ring serves to laterally divert the radially occurring quasi punktförmi¬gen forces and thus to counteract a destruction of the catchment housing or engine housing.
    The deflection ring is preferably made of metal, in particular steel. Due to the small size of the deflection ring with respect to the entire fan housing, the resulting weight disadvantage is negligible.
    Alternatively, the deflector ring may be made of aramid fiber reinforced plastic, e.g. Kevlar®, be formed. Such fiber-reinforced plastics have lower weight than metals but are correspondingly more expensive.
    If the deflecting ring has a wedge-shaped cross-section with an oblique surface pointing towards the fan, the radially auftre¬tende force, which emanates from a broken off part of a Fanschau¬fel, laterally deflected and distributed and consequently the risk of destruction of the fan casing or Trieb¬ factory housing and the endangerment of the aircraft and passengers are reduced.
    The outer layer and the inner layer of the fan casing are vor¬zugsweise preferably made of carbon fiber reinforced plastic. In particular, the outer layer of the fan casing is formed from correspondingly many layers of carbon fiber reinforced plastic, to give the aircraft engine in case of damage sufficient stability and safe landing of the aircraft guarantee.
    The invention will be explained in more detail below with reference to an embodiment. Show:
    1 shows an aircraft engine in a partially sectioned arrangement with a fan cowl arranged in the region of the fan; and
    Fig. 2 shows a part of a inventively designed Fangehäu¬ses in a sectional view.
    1 shows an aircraft engine 2 in a partially cutaway arrangement with a fan cowl 1 arranged in the region of the fan 3. Typically, a fan casing 1 consists of a cylindrical casing with integral or attached mounting flanges and any stiffening ribs or the like. The fan housing 1 is connected to the rest of the engine housing, which in turn is arranged on corresponding Befestigungsele¬menten, usually wings.
    Fig. 2 shows a part of a inventively designed fan housing 1 in a sectional view. The fan housing 1 includes an inner layer 4, which is designed in accordance with the aerodynamic requirements of the aircraft engine 2, and an outer layer 5 and a reinforcing layer 6 arranged between the inner layer 4 and the outer layer 5 and deformation layers 7 arranged on both sides of the reinforcing layer 6. The reinforcing layer 6 is formed of fiberglass-reinforced plastic and is used primarily to survive a collision ei¬nes part of the fan 3 in case of damage. Deformation layers 7, which may be formed by a honeycomb structure or suitable foam materials or combinations thereof, serve to accommodate the kinetic energy emanating from a severed portion of fan 3. The inner layer 4 may be formed of carbon fiber reinforced plastic. The outer layer 5, which significantly serves to ensure the residual strength of the catcher 1 in the event of damage and to enable secure landing with the damaged aircraft engine 2, is preferably also formed of carbon fiber reinforced plastic.
    The reinforcing layer 6 made of fiberglass-reinforced plastic is produced as a function of the aircraft engine 2 from a plurality of layers, for example at least 20 layers, of fiberglass-reinforced plastic.
    To facilitate the production and assembly costs, the fastening flanges 8, 9 necessary for the attachment of the catcher housing 1 can be integrated in the outer layer 5 and produced in a production process with the outer layer 5. Due to the functional separation of the reinforcing layer 6 and the outer layer 5, a tearing of the outer layer 5, in particular in the region of the fastening flanges 8, 9, in the event of a damage can be prevented or at least the risk of damage can be reduced.
    In order to reduce the air gap between fan 3 and inner layer 4, a grinding layer 10 of deformable material may be arranged in the area of the fan 3, into which grinding layer 10 the fan blade with the largest outer diameter mills, thus leaving a vanishing air gap between fan 3 and inner layer 4b. Abrasive layer 10 results.
    The abrasive layer 10 may be formed of glass fiber reinforced resin or honeycomb honeycomb cores.
    In the region of the fan 3, between the inner layer 4 and the reinforcing layer 6, a deflecting ring 11 made of a material having a higher strength than the deformation layers 7 can be arranged, via which deflecting ring 11 the radial forces occurring in the event of damage are laterally deflected. The deflecting ring 11 may be formed of metal, in particular steel, or else aramide fiber-reinforced plastic, for example Kevlar®. For optimal deflection of the radially acting forces, the deflecting ring 11 can have a wedge-shaped cross section with an oblique surface 12 facing the fan 3, as shown.
    At the rear end of the fan casing 1, an attachment element 13 can be arranged and preferably adhesively bonded to the inner layer 4.
    权利要求:
    Claims (12)
    [1]
    1. A fan housing (1) for an aircraft engine (2) in the region des¬sen fan (3), with a plurality of substantially cylindrically angeord¬neten and interconnected layers (3) made of fiber-reinforced plastic, characterized in that zwi¬schen an inner layer (4) and an outer layer (5) a reinforcing layer (6) made of glass fiber reinforced plastic is arranged, and that on both sides of the reinforcing layer (6) Defor¬mationsschichten (7) are arranged, which deformation layers (7) lower strength than the reinforcing layer (6).
    [2]
    A fan case (1) according to claim 1, characterized in that at least one deformation layer (7) is formed by a honeycomb structure.
    [3]
    3. fan housing (1) according to claim 1 or 2, characterized gekennzeich¬net that at least one deformation layer (7) is formed by Schaumma-material.
    [4]
    4. fan housing (1) according to one of claims 1 to 3, characterized ge indicates that the reinforcing layer (6) consists of at least 20 La¬gen of glass fiber reinforced plastic.
    [5]
    5. fan housing (1) according to one of claims 1 to 4, characterized ge indicates that in the outer layer (5) at least one Befes¬tigungsflansch (8, 9) is integrated.
    [6]
    6. fan housing (1) according to one of claims 1 to 5, characterized ge indicates that on the inner layer (4) in the region of the fan (3) an abrasive layer (10) of deformable material is angeord¬net
    [7]
    A fan case (1) according to claim 6, characterized in that the abrasive layer (10) is formed of glass fiber reinforced resin.
    [8]
    8. fan housing (1) according to one of claims 1 to 7, characterized in that between the inner layer (4) and the Verdickkungslage (6) in the region of the fan (3) a deflection ring (11) made of a material with higher strength than the Deformations¬schichten (7) is arranged.
    [9]
    A fan housing (1) according to claim 8, characterized in that the deflector ring (11) is formed of metal, in particular steel.
    [10]
    10. fan housing (1) according to claim 8, characterized in that the deflection ring (11) is gebil¬det of aramid fiber reinforced plastic.
    [11]
    11. fan housing (1) according to one of claims 8 to 10, characterized in that the deflecting ring (11) has a wedge-shaped cross-section with a fan (3) facing oblique surface (12).
    [12]
    12. fan housing (1) according to one of claims 1 to 11, characterized in that the outer layer (5) and the inner layer (4) is formed of carbon fiber reinforced plastic.
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    同族专利:
    公开号 | 公开日
    EP3204619A1|2017-08-16|
    CN107109962A|2017-08-29|
    US20170305117A1|2017-10-26|
    ES2668933T3|2018-05-23|
    US10035330B2|2018-07-31|
    AT516322B1|2017-04-15|
    EP3204619B1|2018-02-28|
    CA2959433A1|2016-04-14|
    RU2017115814A3|2019-04-19|
    RU2698581C2|2019-08-28|
    WO2016054669A1|2016-04-14|
    CN107109962B|2019-06-14|
    BR112017005088A2|2017-12-05|
    RU2017115814A|2018-11-13|
    引用文献:
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    EP1344895A2|2002-03-15|2003-09-17|ROLLS-ROYCE plc|Turbomachine casing made from cellular material|
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    EP2096269A2|2008-02-27|2009-09-02|Rolls-Royce plc|Fan track liner assembly for a gas turbine engine|
    GB2471465A|2009-06-30|2011-01-05|Rolls Royce Plc|Fan casing for a turbofan gas turbine engine|
    US20120224958A1|2011-03-04|2012-09-06|Rolls-Royce Plc|Turbomachine casing assembly|
    GB2498194A|2012-01-05|2013-07-10|Rolls Royce Plc|Ice impact panel for a gas turbine engine|
    GB2288639B|1994-04-20|1998-10-21|Rolls Royce Plc|Ducted fan gas turbine engine nacelle assembly|
    US6053696A|1998-05-29|2000-04-25|Pratt & Whitney Canada Inc.|Impact resistant composite shell for gas turbine engine fan case|
    GB0008193D0|2000-04-05|2000-05-24|Rolls Royce Plc|A gas turbine engine blade containment assembly|
    FR2859002A1|2003-08-18|2005-02-25|Snecma Moteurs|Abradable surface for gas turbine engine housing surrounding fan, is made from a resin with glass balls over a layer of thermoformable foam|
    US7246990B2|2004-12-23|2007-07-24|General Electric Company|Composite fan containment case for turbine engines|
    CA2602319A1|2006-09-25|2008-03-25|General Electric Company|Blade containment system for a gas turbine engine|
    US8021102B2|2006-11-30|2011-09-20|General Electric Company|Composite fan containment case and methods of fabricating the same|
    US8403624B2|2007-12-12|2013-03-26|General Electric Company|Composite containment casings having an integral fragment catcher|
    FR2925118B1|2007-12-14|2009-12-25|Snecma|ABRADABLE SUPPORT PANEL IN A TURBOMACHINE|
    RU2371589C1|2008-01-16|2009-10-27|Федеральное Государственное Унитарное предприятие "Уральский научно-исследовательский институт композиционных материалов"|Blade device|
    GB2459646B|2008-04-28|2011-03-30|Rolls Royce Plc|A fan assembly|
    US8672609B2|2009-08-31|2014-03-18|United Technologies Corporation|Composite fan containment case assembly|
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    US9140135B2|2010-09-28|2015-09-22|United Technologies Corporation|Metallic radius block for composite flange|US10669894B2|2018-01-26|2020-06-02|Raytheon Technologies Corporation|Annular retention strap|
    US20200011203A1|2018-07-06|2020-01-09|General Electric Company|Blade containment structure|
    GB201811547D0|2018-07-13|2018-08-29|Rolls Royce Plc|Fan blade containment|
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    法律状态:
    2020-08-15| MM01| Lapse because of not paying annual fees|Effective date: 20191010 |
    优先权:
    申请号 | 申请日 | 专利标题
    ATA50723/2014A|AT516322B1|2014-10-10|2014-10-10|Flight case for an aircraft engine|ATA50723/2014A| AT516322B1|2014-10-10|2014-10-10|Flight case for an aircraft engine|
    BR112017005088A| BR112017005088A2|2014-10-10|2015-10-09|fan box for an aircraft propulsion mechanism|
    CA2959433A| CA2959433A1|2014-10-10|2015-10-09|Fan case for an aircraft engine|
    US15/517,932| US10035330B2|2014-10-10|2015-10-09|Fan case for an aircraft engine|
    RU2017115814A| RU2698581C2|2014-10-10|2015-10-09|Aircraft engine fan housing|
    EP15793680.8A| EP3204619B1|2014-10-10|2015-10-09|Fan case for an aircraft engine|
    ES15793680.8T| ES2668933T3|2014-10-10|2015-10-09|Fan housing for an airplane engine|
    CN201580054176.8A| CN107109962B|2014-10-10|2015-10-09|Blower-casting for aircraft engine|
    PCT/AT2015/050251| WO2016054669A1|2014-10-10|2015-10-09|Fan case for an aircraft engine|
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