(19)
(11)EP 3 401 222 B1

(12)EUROPEAN PATENT SPECIFICATION

(45)Mention of the grant of the patent:
11.09.2019 Bulletin 2019/37

(21)Application number: 17204248.3

(22)Date of filing:  28.11.2017
(51)International Patent Classification (IPC): 
B64D 33/04(2006.01)
B64D 41/00(2006.01)

(54)

ENGINE EXHAUST DUCT MOUNTING ASSEMBLY

MOTORABGASKANALMONTAGEANORDNUNG

ENSEMBLE DE MONTAGE DE CONDUIT D'ÉCHAPPEMENT DE MOTEUR


(84)Designated Contracting States:
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

(30)Priority: 12.05.2017 US 201715593956

(43)Date of publication of application:
14.11.2018 Bulletin 2018/46

(73)Proprietor: Bell Helicopter Textron Inc.
Fort Worth, TX 76101 (US)

(72)Inventor:
  • ROSADO, Angel David
    Fort Worth, TX 76126 (US)

(74)Representative: Barker Brettell LLP 
100 Hagley Road Edgbaston
Birmingham B16 8QQ
Birmingham B16 8QQ (GB)


(56)References cited: : 
EP-A2- 1 045 185
DE-A1- 4 016 052
US-A1- 2010 269 328
EP-A2- 2 385 228
US-A1- 2005 258 642
US-A1- 2011 074 150
  
      
    Note: Within nine months from the publication of the mention of the grant of the European patent, any person may give notice to the European Patent Office of opposition to the European patent granted. Notice of opposition shall be filed in a written reasoned statement. It shall not be deemed to have been filed until the opposition fee has been paid. (Art. 99(1) European Patent Convention).


    Description

    BACKGROUND


    Technical Field:



    [0001] The present disclosure relates to an aircraft, and more particularly, to an aircraft having a mounting assembly for mounting a portion of an engine exhaust duct in an opening in an airframe panel.

    Description of Related Art:



    [0002] Certain aircraft have main power units in or on a wing. Oftentimes the main power units, such as a gas turbine engine, are exhausted directly from the aft end of the wing. In some aircraft, an auxiliary power unit, which is typically a smaller gas turbine engine, is exhausted using a metal exhaust duct that is mounted internally cantilevered from a metal firewall in the fuselage. The exhaust duct extends from the firewall through an opening provided in an outer airframe surface panel where hot (e.g. 1200°F) turbine exhaust gases (e.g. 1200°F exhaust gases) are discharged to atmosphere.

    [0003] In order to thermally protect the airframe panel from the hot exhaust duct, the opening in the airframe surface panel currently is over-sized to provide a clearance space between the hot exhaust duct and the airframe surface panel. However, the over-sized opening in the airframe surface panel can weaken the airframe panel and create drag that adversely affects aerodynamics of the outer airframe panel during aircraft operation.

    [0004] There is a need for an improved mounting for the exhaust duct on the airframe panel of such tiltrotor and other aircraft.

    [0005] US 2010/0269328 A1 discloses a device for mechanically decoupled retention of components perfused by hot gas in an aircraft, with a coupling member for coupling to a component emitting hot gas and to a component accepting hot gas, with a holder, with a flange. and with a bellows, the holder being fittable to a housing or frame connected to the component emitting hot gas, the bellows being fastened by one end to the flange and by the other end to the holder, and the coupling member being fastened to the flange. By virtue of the device, both an angular misalignment and radial and axial positional misalignment can be equalised.

    [0006] US 2005/0258642 A1 discloses compressed wire filament(s) that form a seal that seals the joint between first and second pipes of an automotive exhaust system secured by bolted together first and second flanges. The seal is initially attached to the first pipe and first flange in an intermediate assembly by an interface connection that prevents the seal from axially moving off of the first pipe prior to final assembly to the second pipe and second flange. A male projection is at the end region of the first pipe outer surface to which the seal is attached. The first flange abuts the seal at a planar seal interface. The seal has a bore with a longitudinal channel portion for initially axially engaging the projection and a transverse channel portion medially the seal bore for receiving the projection by rotation of the seal after the projection is axially displaced within the seal bore. The transverse channel portion may be tapered to wedge the projection in place to preclude accidental disengagement of the seal prior to final assembly to the mating second flange and second pipe. The joint in one embodiment articulates and in a second embodiment the joint is fixed and does not articulate. Various embodiments are disclosed.

    [0007] EP 2 385 228 A2 discloses first and second exhaust system pipes in one of several embodiments that are joined in a fixed fluid tight joint comprising a first flared flange on a first pipe and a flared flange portion on a second pipe. The flange portion is part of a second flange on the second pipe spaced from the second pipe end edge forming a pipe segment forming a corner with the second flange. A seal is between the two flanges abutting the second pipe segment. The first flange has a convex spherical outer surface and a concave inner spherical surface engaged with a first outer convex spherical surface portion of the seal, the radius of the flange inner surface is larger than the radius of the seal first outer surface portion forming a first tangential engaged contact point. A band clamp has two depending legs which respectively engage the first flared flange of the first pipe and the second pipe flared flange portion for forcing the flanges and pipes together and against the seal. A first clamp leg engages the first flange outer convex spherical surface at a second tangential contact point. The other conical leg of the clamp engages the second pipe flared flange portion. The two tangential contact points define a plane normal to the corresponding engaged surfaces providing enhanced stress concentration from the clamp to the pipes via the first flange and seal.

    SUMMARY OF THE INVENTION



    [0008] In a first aspect, there is provided a mounting assembly for mounting a portion of an engine exhaust duct in an opening of an airframe panel of an aircraft, including an airframe panel for an aircraft including an opening, an engine exhaust duct disposed at least partially in the opening of the airframe panel, a peripheral flange disposed on the portion of the engine exhaust duct, and at least one mounting member including a first mounting plate for connection to the airframe panel, a second mounting plate connected to the first mounting plate, a first compliant isolator ring connected to the first mounting plate, a second compliant isolator ring connected to the second mounting plate; wherein the first compliant isolator ring and the second compliant isolator ring define a slot therebetween to receive the peripheral flange of the engine exhaust duct in a manner that suspends the engine exhaust duct in the opening away from the airframe panel and accommodates thermal expansion and contraction of the engine exhaust duct relative to the airframe panel.

    [0009] In an exemplary embodiment, the slot comprises a peripheral slot into which at least an outermost portion of the peripheral flange of the engine exhaust duct is received.

    [0010] In yet another embodiment, the slot includes an inner portion for receiving the peripheral flange and an outer portion opposite from the inner portion.

    [0011] In an embodiment, the slot further includes a clearance space in the outer portion.

    [0012] In an embodiment, the first mounting plate and the second mounting plate each includes a respective first outer peripheral flange portion and a second outer peripheral flange portion for connection to a contoured surface of the airframe panel.

    [0013] In yet another embodiment, the first mounting plate and the second mounting plate each includes a respective first planar surface and a second planar surface between which the first compliant isolator ring and the second compliant isolator ring are disposed.

    [0014] In yet another embodiment, the first compliant isolator ring and the second compliant isolator ring comprises a metallic encapsulated insulation material.

    [0015] In an exemplary embodiment, the first mounting plate and the second mounting plate comprises an aluminum alloy.

    [0016] In an embodiment, there is a combination of an airframe panel and the mounting assembly including the airframe panel comprising an outer composite airframe panel.

    [0017] In one embodiment, the airframe panel includes a carbon-carbon composite.

    [0018] In a second aspect, there is provided a method of mounting an engine exhaust duct in an opening of an airframe panel of an aircraft, including connecting a peripheral flange to the outer periphery of the engine exhaust duct, connecting a mounting member to the airframe panel, the mounting member including a first mounting plate, a second mounting plate connected to the first mounting plate, a first compliant isolator ring connected to the first mounting plate and a second compliant isolator ring connected to the second mounting plate, the first compliant isolator ring and the second compliant isolator ring defining a slot therebetween; and suspending a portion of the peripheral flange in the slot to accommodate thermal expansion and contraction of the engine exhaust duct in an opening of the airframe panel.

    [0019] In an exemplary embodiment, the slot includes an inner portion for receiving the peripheral flange and an outer portion opposite from the inner portion.

    [0020] In another embodiment, the slot further includes a clearance space in the outer portion.

    [0021] In an exemplary embodiment, the first compliant isolator ring and the second compliant isolator ring can be a metallic encapsulated insulation material.

    [0022] Other aspects, features, and advantages will become apparent from the following detailed description when taken in conjunction with the accompanying drawings, which are a part of this disclosure and which illustrate, by way of example, principles of the inventions disclosed.

    DESCRIPTION OF THE DRAWINGS



    [0023] The features believed characteristic of the embodiments of the present disclosure are set forth in the appended claims. However, the embodiments themselves, as well as a preferred mode of use, and further objectives and advantages thereof, will best be understood by reference to the following detailed description when read in conjunction with the accompanying drawings, wherein:

    FIG. 1A is a perspective view of a tiltrotor aircraft, according to one example embodiment;

    FIG. 1B is a side view of the tiltrotor aircraft in FIG. 1A with an aft portion broken away to illustrate an exhaust duct mounting assembly, according to one example embodiment;

    FIG. 1C is a partial, enlarged view of the aft portion broken away showing the exhaust duct mounting assembly in FIG. 1B;

    FIG. 2 is a partial perspective view of an exhaust duct mounting assembly fixedly mounted on an internal firewall in the fuselage and extending inside the fuselage to an aft upper airframe panel or skin (only partially shown) of the aircraft, according to one example embodiment;

    FIG. 3 is a partial side view of an exhaust duct mounting assembly, according to one example embodiment; and

    FIG. 4 is an exploded view of the exhaust duct mounting assembly according to one example embodiment.


    DESCRIPTION OF THE PREFERRED EMBODIMENT



    [0024] Illustrative embodiments of the mounting assembly and method are described below. In the interest of clarity, all features of an actual implementation may not be described in this specification. It will of course be appreciated that in the development of any such actual embodiment, numerous implementation-specific decisions must be made to achieve the developer's specific goals, such as compliance with system-related and business-related constraints, which will vary from one implementation to another. Moreover, it will be appreciated that such a development effort might be complex and time-consuming but would nevertheless be a routine undertaking for those of ordinary skill in the art having the benefit of this disclosure.

    [0025] In the specification, reference may be made to the spatial relationships between various components and to the spatial orientation of various aspects of components as the devices are depicted in the attached drawings. However, as will be recognized by those skilled in the art after a complete reading of the present application, the devices, members, apparatuses, etc. described herein may be positioned in any desired orientation. Thus, the use of terms such as "above," "below," "upper," "lower," or other like terms to describe a spatial relationship between various components or to describe the spatial orientation of aspects of such components should be understood to describe a relative relationship between the components or a spatial orientation of aspects of such components, respectively, as the device described herein may be oriented in any desired direction.

    [0026] The embodiments of the engine exhaust duct mounting assembly 220 will be described with refence to a tiltrotor aircraft 101, it will be appreciated that the mounting assembly 220 may be used on any type of aircraft or device having an exhaust duct; for example, and not limitation, the mounting assembly 220 can be used with any helicopters, tilt wing aircrafts, unmanned aerial vehicles (UAVs), hovercrafts, other vertical lift or VTOL aircrafts, or can further be used with any vehicle or device having an exhaust duct.

    [0027] Referring to FIG. 1A in the drawings, a tiltrotor aircraft 101 is illustrated. Tiltrotor aircraft 101 can include a fuselage 103, landing gear 105, a tail member 107, and a wing member 109 having a propulsion system 111, and a propulsion system 113. Each propulsion system 111 and 113 is housed within a nacelle 111a and 113a that can include a fixed portion with an engine and a rotatable proprotor gear box proprotor (PRGB) system 115 and 117, respectively. Each rotatable proprotor gearbox system 115 and 117 has a plurality of rotor blades 119 and 121, respectively. The position of the rotatable proprotor gearbox systems 115 and 117 as well as the pitch of the rotor blades 119 and 121, can be selectively controlled in order to selectively control direction, thrust, and lift of the tiltrotor aircraft. The rotor blades 119 and 121 are each driven by an output shaft of the PRGB which is powered by engine 123 in fixed nacelle 130, all as described in aforementioned U.S. Patent 9,174,731.

    [0028] FIG. 1A illustrates tiltrotor aircraft 101 in the vertical flight mode (helicopter mode) in which the rotatable proprotor gearbox systems 115 and 117 are positioned substantially vertical to provide a lifting thrust. Tiltrotor aircraft 101 can be operated in a forward flight mode (airplane mode), as shown in FIG. 1B, in which the rotatable proprotor gearbox systems 115 and 117 are positioned substantially horizontal to provide a forward thrust in which a lifting force is supplied by the wing member 109. It will be appreciated that tiltrotor aircraft 101 can be operated such rotatable gearbox systems 115 and 117 are selectively positioned between the airplane mode and the helicopter mode, which can be referred to as a conversion mode.

    [0029] Referring now to FIGS. 1A-1C and 2-3, tiltrotor aircraft 101 is provided with an auxiliary power unit 200, such as a small gas turbine engine shown schematically, that is housed in the main fuselage 103 for providing electrical power to aircraft components. The auxiliary power unit 200 is provided with a metallic exhaust duct 202 that is mounted internally cantilevered from a metallic (e.g. titanium alloy) firewall 204 in the fuselage 103. Exhaust duct 202 extends from the firewall 204 through an opening 206 provided in an airframe panel 210 where hot (e.g. 1200°F) turbine exhaust gases (e.g. 1200°F exhaust gases) are discharged to atmosphere, as shown in FIG. 1C.

    [0030] In certain illustrative embodiments, exhaust duct 202 includes an outer peripheral flange 203 that is welded or otherwise attached to the peripheral wall of the exhaust duct 202. Exhaust duct flange 203 extends transversely relative to the long axis of the exhaust duct 202. If the exhaust duct 202 has a circular cross-section, flange 203 may extend in a substantially radial direction relative to the long axis.

    [0031] In certain illustrative embodiments, the airframe panel 210 is an aft upper airframe panel or skin 210a, comprising a composite panel that can be damaged by heat and thermal expansion/contraction of the exhaust duct 202 relative to the airframe panel 210 during aircraft operation. In an embodiment, the airframe panel 210 is a composite panel comprised of a plurality of plies of composite fibers with resin (i.e. pre-preg). In an embodiment, the airframe panel 210 can be at least one of the following: a carbon-carbon composite panel, a reinforced carbon-carbon composite panel, a carbon fiber sandwich panel, carbon fiber and honeycomb sandwich panel, and a carbon fiber and foam sandwich panel.

    [0032] It will be appreciated that the contemplated embodiments of the mounting assembly 220 are configured for an airframe panel 210 located generally in the fuselage 103 of the aircraft 101. This disclosure contemplates that the mounting assembly 220 can be configured for use with at least one panel located on the wing member 109; nacelles 111a, 113a; tail member 107; and/or other areas suitable for mounting the end portion 202a of the exhaust duct 202 therethrough. The airframe panel 210 can be a skin, interior, or exterior surface of the aircraft 101.

    [0033] Certain illustrative embodiments of the present invention provide a mounting assembly 220 to compliantly mount the end portion 202a of the exhaust duct 202 in the opening 206 in the airframe panel 210 in a manner to protect the airframe panel 210 from exhaust duct heat and damage caused by repeated thermal expansion/contraction of the exhaust duct 202. Use of the mounting assembly 220 is further advantageous to dampen and isolate any exhaust duct-induced vibrations during engine operation and to facilitate installation of the exhaust duct 202 by reducing tolerance build-ups with respect to the opening 206.

    [0034] Referring to FIGS. 2 and 3, certain illustrative embodiments provide a mounting assembly 220 including at least one mounting member 221 shown as including a first mounting plate 222 and a second mounting plate 224. First mounting plate 222 is the upper mounting plate and second mounting plate 224 is the lower mounting plate, which can be connected by intermediate sidewall 225 as a one-piece component. The mounting plates 222, 224 can have flat (planar) or contoured surfaces to match the surface of the airframe panel 210. The first (upper) mounting plate 222 includes radially spaced apart holes 222a to receive fasteners for attaching the mounting assembly 220 to the exterior surface of the airframe panel 210.

    [0035] The mounting assembly 220 can be made as a one-piece component by, for example, machining, casting, and other manufacturing processes in certain illustrative embodiments. In other embodiments, the mounting assembly 220 can be comprised of distinct and separate parts (e.g., the first mounting plate 222 and the second mounting plates are separate parts that can be fastened together using conventional fasteners and/or adhesives). In certain illustrative embodiments, mounting assembly 220 can be comprised of an aluminum alloy or other suitable material.

    [0036] Referring to FIGS. 2 and 3, at least one compliant isolator member 230 is positioned between the first and second mounting plates 222, 224. In certain illustrative embodiments, the compliant isolator member 230 can comprise an upper, flat-sided compliant isolator ring 230a and a lower, flat-sided compliant isolator ring 230b, which can be adhesively or otherwise attached to the facing surface of the respective first and second mounting plates 222, 224. In certain embodiments, the upper and lower compliant isolator rings 230a, 230b can comprise to two half-rings that mate together to form a single ring structure. In other embodiments, at least one of the isolator rings 230a, 230b can be made as a one-piece ring structure.

    [0037] When the mounting assembly 220 is assembled on the airframe panel 210, the isolator rings 230a, 230b are spaced apart and form a transversely-extending slot SL to compliantly receive and compliantly suspend the exhaust duct flange 203 in the opening 206 spaced away from the airframe panel 210 to provide a peripheral air insulating space between the exhaust duct and the mounting assembly. The mounting assembly 220 and the exhaust duct flange 203 cooperate in a manner that closes off the opening 206 in the airframe panel 210.

    [0038] The outer end portion of the exhaust duct flange 203 is received in an inner portion of the slot SL. The slot SL includes a clearance space at the outer portion of the slot SL as illustrated in FIG. 3 that allows the exhaust duct flange 203 to move transversely (e.g. radially) in the slot SL to accommodate transverse (e.g. radial) thermal expansion/contraction of the exhaust duct 202.

    [0039] In certain illustrative embodiments, the isolator rings 230a, 230b are made of metallic encapsulated, semi rigid insulating core material such that the isolator rings are capable of reversible deflection in the axial direction perpendicular to the slot SL in order to accommodate axial thermal expansion/contraction of the exhaust duct 202 and isolate the thermal expansion/contraction within the mounting assembly 220.

    [0040] In certain embodiments, the isolator rings 230a, 230b can be made of a thermal insulating material to contain and isolate heat from the exhaust duct flange 203 within the mounting assembly 220.

    [0041] Although FIGS. 2-3 illustrate the compliant isolator member 230 as comprising first and second isolator rings, the isolator member 230 can comprise a one-piece component, such as C-shaped component, with slot SL machined, molded, or otherwise provided to receive the exhaust duct flange 203. Such a one-piece isolator member 230 can be attached on a one-piece mounting member in certain illustrative embodiments.

    [0042] FIG. 4 illustrates an embodiment of an exhaust duct mounting assembly 220'. Certain components of the mounting assembly 220' are as described above. Those components bear similar reference characters to the components of the mounting assembly 220, but are primed. The mounting assembly 220' includes first and second mounting plates 222', 224' that are made as separate plates from one another, rather than as a one-piece component as in FIGS. 2-3.

    [0043] The first and second mounting plates 222', 224' each includes respective holes 222a', 224a' to receive fasteners for attaching the mounting assembly 220' to the respective outer and inner surface of the airframe panel 210. Moreover, in FIG. 4, the upper and lower compliant rings 230a', 230b' are shown for purposes of illustration and not limitation as each including two half-rings that mate together to form a single isolator ring structure.

    [0044] The illustrative embodiment shown in FIG. 4 otherwise functions in a similar manner as described for the FIGS. 2-3. For example, when the mounting assembly 220' is assembled on the airframe panel 210, the isolator rings 230' are spaced apart to define a transversely-extending slot that compliantly receives and suspends the exhaust duct flange 203 in the opening 206 spaced away from the airframe panel 210 in the manner described above and shown in FIGS. 2-3 to provide a peripheral air insulating space between the exhaust duct and the mounting assembly. The mounting assembly 220' and the exhaust duct flange 203 cooperate in a manner that closes off the opening 206 in the airframe panel 210 as described above for FIGS. 2-3. The outer end portion of the exhaust duct flange 203 is received in a slot (SL in FIGS. 2-3) provided between isolator members 230a', 230b' with a clearance space at the outer portion of the slot SL (as illustrated in FIG. 3) that allows the exhaust duct flange 203 to move transversely (e.g. radially) in the slot to accommodate transverse (e.g. radial) thermal expansion/contraction of the exhaust duct 202.

    [0045] An embodiment provides a method of mounting the engine exhaust duct 202 in an opening 206 of an airframe panel 210 of an aircraft 101 including connecting a flange 203 that is welded to the outer periphery of the exhaust duct 202, connecting an outer peripheral portion of the at least one mounting member 221 to the airframe panel 210, and suspending the flange 203 of the exhaust duct 202 on at least one compliant isolator member 230 disposed on an inner peripheral portion of the at least one mounting member 221 to space the exhaust duct in the opening 206 away from the airframe panel and to accommodate thermal expansion and contraction of the exhaust duct 202 relative to the airframe panel 210.

    [0046]  Use of broader terms such as comprises, includes, and having should be understood to provide support for narrow terms such as consisting of, consisting essentially of, and comprised substantially of. Accordingly, the scope of protection is not limited by the description set out above but is defined by the claims.


    Claims

    1. A mounting assembly (220) for mounting a portion of an engine exhaust duct (202) in an opening (206) of an airframe panel (210) of an aircraft (101), comprising:

    an airframe panel (210) for an aircraft (101) including an opening;

    an engine exhaust duct disposed at least partially in the opening of the airframe panel (210), the engine exhaust duct including a peripheral flange (203); and

    at least one mounting member (221) including a first mounting plate (222) for connection to the airframe panel, a second mounting plate (224) connected to the first mounting plate, a first compliant isolator ring (230a) connected to the first mounting plate, and a second compliant isolator ring (230b) connected to the second mounting plate;

    wherein the first compliant isolator ring and the second compliant isolator ring define a slot therebetween to receive a portion of the peripheral flange (203) in a manner that suspends the engine exhaust duct in the opening (206) away from the airframe panel and accommodates thermal expansion and contraction of the engine exhaust duct (202) relative to the airframe panel (210).


     
    2. The assembly (220) of claim 1, wherein the slot comprises a peripheral slot into which at least an outermost portion of the peripheral flange (203) of the engine exhaust duct is received.
     
    3. The assembly (220) of claim 1, wherein the first mounting plate (222) and the second mounting plate (224) each includes a respective first outer peripheral flange portion and a second outer peripheral flange portion for connection to a contoured surface of the airframe panel (210).
     
    4. The assembly (220) of claim 1, wherein the first mounting plate (222) and the second mounting plate (224) each includes a respective first planar surface and a second planar surface between which the first compliant isolator ring (230a) and the second compliant isolator ring (230b) are disposed.
     
    5. The assembly (220) of claim 1 or any of preceding claim depending directly or indirectly from claim 1, wherein the slot comprises an inner portion for receiving the peripheral flange (203) and an outer portion opposite from the inner portion.
     
    6. The assembly (220) of claim 5, wherein the slot further comprises a clearance space in the outer portion.
     
    7. The assembly (220) of claim 1 or of any preceding assembly claim , wherein the first compliant isolator ring (230a) and the second compliant isolator ring (230b) comprises a metallic encapsulated insulation material.
     
    8. The assembly (220) of claim 1 or of any preceding claim, wherein the first mounting plate (222) and the second mounting plate (224) comprises an aluminum alloy.
     
    9. A combination of the airframe panel (210) and the mounting assembly (220) of claim 1 including the airframe panel comprising a composite outer airframe panel.
     
    10. The combination of claim 9, wherein the airframe panel (210) comprises a carbon-carbon composite.
     
    11. A method of mounting an engine exhaust duct (202) in an opening (206) of an airframe panel (210) of an aircraft (101), comprising:

    connecting a peripheral flange (203) to the outer periphery of an exhaust duct;

    connecting a mounting member to an airframe panel; the mounting member including a first mounting plate (222), a second mounting plate (224) connected to the first mounting plate, a first compliant isolator ring (230a) connected to the first mounting plate; and a second compliant isolator ring (230b) connected to the second mounting plate, the first compliant isolator ring and the second compliant isolator ring defining a slot therebetween; and

    suspending a portion of the peripheral flange in the slot to accommodate thermal expansion and contraction of the engine exhaust duct (202) in an opening (206) of the airframe panel.


     
    12. The method of claim 11, wherein the slot comprises an inner portion for receiving the peripheral flange (203) and an outer portion opposite from the inner portion.
     
    13. The method of claim 11, wherein the slot further comprises a clearance space in the outer portion.
     
    14. The method of any preceding method claim, wherein the first compliant isolator ring (230a) and the second compliant isolator ring (230b) comprises a metallic encapsulated insulation material.
     


    Revendications

    1. Ensemble de montage (220) pour monter une partie d'un conduit de gaz d'échappement de moteur (202) dans une ouverture (206) d'un panneau de fuselage (210) d'un aéronef (101), comprenant :

    un panneau de fuselage (210) pour un aéronef (101) incluant une ouverture ;

    un conduit de gaz d'échappement de moteur disposé au moins en partie dans l'ouverture du panneau de fuselage (210), le conduit de gaz d'échappement de moteur incluant une bride périphérique (203) ; et

    au moins un élément de montage (221) incluant une première plaque de montage (222) pour une liaison au panneau de fuselage, une seconde plaque de montage (224) reliée à la première plaque de montage, un premier anneau isolant souple (230a) relié à la première plaque de montage et un second anneau isolant souple (230b) relié à la seconde plaque de montage ;

    dans lequel le premier anneau isolant souple et le second anneau isolant souple définissent une fente entre eux pour recevoir une partie de la bride périphérique (203) de manière à suspendre le conduit de gaz d'échappement de moteur dans l'ouverture (206) de manière éloignée du panneau de fuselage et à accueillir une expansion et contraction thermiques du conduit de gaz d'échappement de moteur (202) par rapport au panneau de fuselage (210).


     
    2. Ensemble (220) selon la revendication 1, dans lequel la fente comprend une fente périphérique dans laquelle au moins une partie la plus extérieure de la bride périphérique (203) du conduit de gaz d'échappement de moteur est reçue.
     
    3. Ensemble (220) selon la revendication 1, dans lequel la première plaque de montage (222) et la seconde plaque de montage (224) incluent chacune une première partie extérieure de bride périphérique respective et une seconde partie extérieure de bride périphérique pour une liaison à une surface profilée du panneau de fuselage (210).
     
    4. Ensemble (220) selon la revendication 1, dans lequel la première plaque de montage (222) et la seconde plaque de montage (224) incluent chacune une première surface planaire respective et une seconde surface planaire entre lesquelles le premier anneau isolant souple (230a) et le second anneau isolant souple (230b) sont disposés.
     
    5. Ensemble (220) selon la revendication 1 ou l'une quelconque des revendications précédentes dépendant directement ou indirectement de la revendication 1, dans lequel la fente comprend une partie intérieure pour recevoir la bride périphérique (203) et une partie extérieure opposée à la partie intérieure.
     
    6. Ensemble (220) selon la revendication 5, dans lequel la fente comprend en outre un espace libre dans la partie extérieure.
     
    7. Ensemble (220) selon la revendication 1 ou l'une quelconque des revendications précédentes, dans lequel le premier anneau isolant souple (230a) et le second anneau isolant souple (230b) comprennent un matériau d'isolation encapsulé métallique.
     
    8. Ensemble (220) selon la revendication 1 ou l'une quelconque des revendications précédentes, dans lequel la première plaque de montage (222) et la seconde plaque de montage (224) comprennent un alliage d'aluminium.
     
    9. Combinaison du panneau de fuselage (210) et de l'ensemble de montage (220) selon la revendication 1 incluant le panneau de fuselage comprenant un panneau de fuselage extérieur composite.
     
    10. Combinaison selon la revendication 9, dans laquelle le panneau de fuselage (210) comprend un composite carbone-carbone.
     
    11. Procédé de montage d'un conduit de gaz d'échappement de moteur (202) dans une ouverture (206) d'un panneau de fuselage (210) d'un aéronef (101), comprenant :

    la liaison d'une bride périphérique (203) à la périphérie extérieure d'un conduit de gaz d'échappement;

    la liaison d'un élément de montage à un panneau de fuselage ; l'élément de montage incluant une première plaque de montage (222), une seconde plaque de montage (224) reliée à la première plaque de montage, un premier anneau isolant souple (230a) relié à la première plaque de montage; et un second anneau isolant souple (230b) relié à la seconde plaque de montage, le premier anneau isolant souple et le second anneau isolant souple définissant une fente entre eux ; et

    la suspension d'une partie de la bride périphérique dans la fente pour accueillir une expansion et contraction thermiques du conduit de gaz d'échappement de moteur (202) dans une ouverture (206) du panneau de fuselage.


     
    12. Procédé selon la revendication 11, dans lequel la fente comprend une partie intérieure pour recevoir la bride périphérique (203) et une partie extérieure opposée à la partie intérieure.
     
    13. Procédé selon la revendication 11, dans lequel la fente comprend en outre un espace libre dans la partie extérieure.
     
    14. Procédé selon l'une quelconque des revendications du procédé, dans lequel le premier anneau isolant souple (230a) et le second anneau isolant souple (230b) comprennent un matériau d'isolation encapsulé métallique.
     


    Ansprüche

    1. Montageanordnung (220) zum Montieren eines Abschnitts einer Motorabgasleitung (202) in einer Öffnung (206) eines Flugzeugzellenpanels (210) eines Flugzeugs (101), umfassend:

    ein Flugzeugzellenpanel (210) für ein Flugzeug (101), einschließend eine Öffnung;

    eine Motorabgasleitung, angeordnet teilweise in der Öffnung des Flugzeugzellenpanels (210), wobei die Motorabgasleitung einen peripheren Flansch (203) einschließt; und

    mindestens ein Montageelement (221), einschließend eine erste Montageplatte (222) zur Verbindung mit dem Flugzeugzellenpanel, eine zweite Montageplatte (224), verbunden mit der ersten Montageplatte, einen ersten nachgiebigen Isolatorring (230a), verbunden mit der ersten Montageplatte, und einen zweiten nachgiebigen Isolatorring (230b), verbunden mit der zweiten Montageplatte;

    wobei der erste nachgiebige Isolatorring und der zweite nachgiebige Isolatorring einen Schlitz dazwischen definieren, um einen Abschnitt des peripheren Flansches (203) in einer Weise zu empfangen, die die Motorabgasleitung in der Öffnung (206) weg von dem Flugzeugzellenpanel abhängt und thermische Expansion und Kontraktion der Motorabgasleitung (202) relativ zu dem Flugzeugzellenpanel (210) aufnimmt.


     
    2. Anordnung (220) nach Anspruch 1, wobei der Schlitz einen peripheren Schlitz umfasst, in dem mindestens ein äußerster Abschnitt des peripheren Flansches (203) der Motorabgasleitung empfangen ist.
     
    3. Anordnung (220) nach Anspruch 1, wobei die erste Montageplatte (222) und die zweite Montageplatte (224) jeweils einen entsprechenden ersten äußeren Flanschabschnitt und einen zweiten äußeren Flanschabschnitt zur Verbindung mit einer konturierten Oberfläche des Flugzeugzellenpanels (210) einschließt.
     
    4. Anordnung (220) nach Anspruch 1, wobei die erste Montageplatte (222) und die zweite Montageplatte (224) jeweils eine entsprechende erste planare Oberfläche und eine zweite planare Oberfläche einschließt, zwischen denen der erste nachgiebige Isolatorring (230a) und der zweite nachgiebige Isolatorring (230b) angeordnet sind.
     
    5. Anordnung (220) nach Anspruch 1 oder einem vorstehenden Anspruch, direkt oder indirekt abhängig von Anspruch 1, wobei der Schlitz einen inneren Abschnitt zum Empfangen des peripheren Flansches (203) und einen äußeren Abschnitt, gegenüberliegend dem inneren Abschnitt, umfasst.
     
    6. Anordnung (220) nach Anspruch 5, wobei der Schlitz weiter einen Durchgangsraum in dem äußeren Abschnitt umfasst.
     
    7. Anordnung (220) nach Anspruch 1 oder einem vorstehenden Anordnungsanspruch, wobei der erste nachgiebige Isolatorring (230a) und der zweite nachgiebige Isolatorring (230b) ein metallisch eingekapseltes Isolationsmaterial umfasst.
     
    8. Anordnung (220) nach Anspruch 1 oder einem vorstehenden Anspruch, wobei die erste Montageplatte (222) und die zweite Montageplatte (224) eine Aluminiumlegierung umfassen.
     
    9. Kombination eines Flugzeugzellenpanels (210) und der Montageanordnung (220) nach Anspruch 1, einschließend das Flugzeugzellenpanel, umfassend ein äußeres Verbundstoffflugzeugzellenpanel.
     
    10. Kombination nach Anspruch 9, wobei das Flugzeugzellenpanel (210) einen Karbon-Karbon-Verbundstoff umfasst.
     
    11. Verfahren zum Montieren einer Motorabgasleitung (202) in einer Öffnung (206) eines Flugzeugzellenpanels (210) eines Flugzeugs (101), umfassend:

    Verbinden eines peripheren Flansches (203) mit der äußeren Peripherie einer Abgasleitung;

    Verbinden eines Montageelements mit einem Flugzeugzellenpanel; wobei das Montageelement eine erste Montageplatte (222), eine zweite Montageplatte (224), verbunden mit der ersten Montageplatte, einen ersten nachgiebigen Isolatorring (230a), verbunden mit der ersten Montageplatte; und einen zweiten nachgiebigen Isolatorring (230b), verbunden mit der zweiten Montageplatte, einschließt, wobei der erste nachgiebige Isolatorring und der zweite nachgiebige Isolatorring einen Schlitz dazwischen definieren; und

    Abhängen eines Abschnitts eines peripheren Flansches in dem Schlitz, um thermische Expansion und Kontraktion der Motorabgasleitung (202) in einer Öffnung (206) des Flugzeugzellenpanels aufzunehmen.


     
    12. Verfahren nach Anspruch 11, wobei der Schlitz einen inneren Abschnitt zum Empfangen des peripheren Flansches (203) und einen äußeren Abschnitt, gegenüberliegend dem inneren Abschnitt, umfasst.
     
    13. Verfahren nach Anspruch 11, wobei der Schlitz weiter einen Durchgangsraum in dem äußeren Abschnitt umfasst.
     
    14. Verfahren nach einem vorstehenden Verfahrensanspruch, wobei der erste nachgiebige Isolatorring (230a) und der zweite nachgiebige Isolatorring (230b) ein metallisch eingekapseltes Isolationsmaterial umfasst.
     




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    Cited references

    REFERENCES CITED IN THE DESCRIPTION



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    Patent documents cited in the description