Fireproof and heat-insulating part product

Abstract

The present invention relates to a fireproof and heat-insulating part product (1), a composite part, a rear end portion of an aircraft, a pipeline, a battery housing, and a helicopter. The fireproof and heat-insulating part product comprises a combination of the following: - an alkaline earth silicate (AES) material (2), and - at least one of the following: a liquid barrier film (5), a FRP (fiber reinforced plastic) layer (4), cork (3), - wherein the liquid barrier film (5) and the FRP layer (4) are stacked on the AES material (2), - and wherein the cork (3) material is also stacked on the AES material (2) or embedded in the AES material (2), and the cork (3) is configured as a plurality of strips to form a grid structure filled with the AES material (2).

Description

Technical Field

[0001] The present invention relates to a product that provides a structure and related systems for protection against the consequences of a fire event, particularly flame penetration, and also provides heat insulation capabilities. The present invention is particularly applicable to different parts of aircraft and helicopters. Background Art

[0002] Many components of an aircraft are affected by fire events, and in order to ensure the normal operation of the aircraft, the structure and related systems must be protected against the consequences of fire events.

[0003] For these purposes, several materials and solutions have been tested and implemented to prevent the consequences of fire events. Depending on the application, two main effects need to be addressed: flame penetration and heat insulation.

[0004] The problem of flame penetration needs to be solved in order to keep the fire confined to a designated area. On the other hand, heat insulation capabilities can allow a wide range of materials to be used for structural applications with lower decoupling temperature requirements.

[0005] The most widely used solution in the prior art is a heat insulation cladding mainly made of ceramic or silicone laminates together with aluminum sheets. These heat insulation claddings are effective solutions for flame penetration and heat insulation, but they are also expensive and heavy.

[0006] The heat insulation cladding may have some problems in structural applications due to its lack of rigidity. Therefore, these heat insulation claddings may collapse during the manufacturing or assembly process, resulting in the loss of their effectiveness.

[0007] Another solution in the prior art is a material that resists fire events by forming a porous material char layer to prevent flame penetration and provide heat insulation. This option is relevant to many applications due to its performance, but due to the loss of protection under operating strip conditions, structures subject to vibration cannot implement this solution.

[0008] In another solution of the prior art, materials such as titanium, steel, or Inconel alloys that exhibit higher fire resistance / fireproof capabilities are added or used instead of conventional materials commonly used for structural parts, such as aluminum, composite materials (CFRP, GFRP, etc.), to overcome the problem of fire penetration. As an example, this can be understood in the APU of an aircraft, which can be surrounded by a titanium fire wall to prevent damage to aluminum (as a structural material), so that in the event of a fire, the fire can come out from the tail cone. Summary of the Invention

[0009] The object of the present invention is to provide a product that is fireproof and also has good heat insulation capabilities, so as to avoid the high temperature at the structure around the fire source from damaging the structure.

[0010] The present invention provides a fireproof and heat-insulating component product, which comprises a material combination of the following items:

[0011] - An alkaline earth silicate (AES) material, and

[0012] - At least one of the following: a liquid barrier film, an FRP (fiber reinforced plastic) layer, cork,

[0013] Wherein, the liquid barrier film and the FRP layer are stacked on the AES material, and wherein, the cork material is also stacked on the AES material or embedded in the AES material, and in the last case, where the cork is embedded in the AES material, the cork is configured as a plurality of strips, thereby forming a grid structure filled with the AES material.

[0014] The present invention provides the following advantages:

[0015] -- The cost is lower than the prior art solutions.

[0016] - Using low-density materials, thus reducing the weight and providing a lighter solution than the prior art.

[0017] - The fireproof and heat-insulating capabilities are ensured through testing.

[0018] - Environmentally friendly.

[0019] - Integrated in the structural panel, thus reducing potential costs while avoiding the problem of the insulating material collapsing during manufacturing and / or assembly.

[0020] - Due to the decoupling of thermal and structural requirements, it is possible to use structural materials in designated areas of a fire zone with limited high-temperature strength capabilities.

[0021] Other features and advantages of the present invention will become apparent from the following detailed description of several embodiments for explaining the purpose in connection with the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 A schematic diagram showing a fireproof and heat-insulating component product according to a first preferred embodiment of the present invention.

[0023] Figure 2 A schematic diagram showing the thermal performance of cork.

[0024] Figure 3 A schematic diagram showing a fireproof and heat-insulating component product according to a second preferred embodiment of the present invention.

[0025] Figures 4a to 4c A schematic diagram showing fireproof and heat-insulating component products according to different preferred embodiments of the present invention.Figure 4a A top view is shown. Figure 4b A cross-sectional view of a fireproof and heat-insulating component product according to a third preferred embodiment of the present invention is shown. Figure 4c A cross-sectional view of a fireproof and heat-insulating component product according to a fourth preferred embodiment of the present invention is shown.

[0026] Figure 5a An aircraft having an APU compartment at its rear end is shown, wherein at least one fireproof wall includes the fireproof and heat-insulating component product of the present invention. Figure 5b A detailed view of the APU compartment is shown.

[0027] Figure 6a and Figure 6b respectively show the front fireproof wall of the APU compartment.

[0028] Figure 7a An exploded view of a battery and its housing is shown. Figure 7b A perspective view of the main elements of the housing is shown.

[0029] Figure 8 An engine mount of a helicopter including the fireproof and heat-insulating component product of the present invention is shown.

[0030] Figure 9 A helicopter engine compartment having a central wall including the fireproof and heat-insulating component product of the present invention is shown. Detailed Description

[0031] It is important to consider the concept of "fireproof" as defined by aviation regulations such as the following:

[0032] - FAR / JAR 25.1191: Fireproof Wall - Definition.

[0033] - FAR / JAR 25.865: Fireproof Protection for Flight Controls, Engine Mounts, and Other Flight Structures.

[0034] Figure 1 A first preferred configuration of the fireproof and heat-insulating component product 1 of the present invention is shown. The fireproof and heat-insulating component product includes a stack of layers. The stack of layers includes a cork layer 3 and an alkaline earth silicate material (AES) layer 2. The alkaline earth silicate material layer is on the side of the product 1 intended to face the fire. The AES layer 2 mainly acts as a fireproof barrier and acts as a heat insulator at a second level, while the cork layer 3 acts as a heat insulator.

[0035] For most possible applications, the AES layer 2 and the cork layer 3 need to be combined with protection against erosive fluids, mainly for AES 2. To this end, a pair of liquid barrier films 5 and a pair of FRP (fiber-reinforced plastic) layers 4 are placed on both sides of the product 1. The pair of FRP 4 layers is intended to be bonded to the AES and the cork.

[0036] Preferably, the liquid barrier film 5 is a PVF (polyvinyl fluoride) film or a similar material (PEEK, PDVF, PET, etc.). And preferably, the FRP layer 4 is a GFRP layer.

[0037] Figure 1 The illustrated embodiment is a good solution for non-structural protection and can be placed as an add-on on structures in many areas to protect the structure from fire and temperature.

[0038] In addition to heat insulation through the low thermal conductivity of the cork material itself, this material also exhibits the following important characteristics for this specific application. As Figure 2 shown, the closed-cell (micro) structure acts as an effective barrier against hot fire gases, and the degradation of this structure under severe thermal shock produces a further heat-insulating char layer on the surface facing the fire / heat source. The pyrolysis gases are also considered to provide some insulation.

[0039] Figure 3 A second preferred configuration of the fireproof and heat-insulating member product 1 of the present invention is shown. The fireproof and heat-insulating member product includes a stack of layers, and the stack of layers includes an alkaline earth silicate material (AES) layer 2, a pair of FRP (fiber reinforced plastic) layers 4 on both sides of the AES layer 2, and a pair of liquid barrier films 5 on both sides of the FRP layer 4. In this second preferred configuration, the (one or more) AES layers act as a fire barrier and a heat-insulating solution.

[0040] Similar to Figure 1 the embodiment, this second preferred configuration is a good solution for non-structural protection and can be placed as an add-on on structures in many areas to protect the structure from fire and temperature.

[0041] Figures 4a to 4c Another preferred embodiment of the fireproof and heat-insulating member product 1 is shown. In this embodiment, the product 1 includes a stack of layers, and the stack of layers includes a layer formed by AES 2 and cork 3. The cork 3 is configured as a plurality of strips that form a grid structure (lattice) filled with the AES material 2. Figure 4a This product is schematically depicted.

[0042] This option is introduced as a more robust protection. The product can be placed on a structure or included inside a structural laminate used as a sandwich panel core. Additionally, in this case, the cork acts as a rigid structure that prevents the insulation material from collapsing due to the high pressure applied during the curing process in an autoclave.

[0043] Figure 4bShows a third preferred embodiment, wherein the layer formed by the cork lattice 3 filled with AES 2 further includes an additional AES layer 2 deposited on the layer composed of AES + cork, a pair of FRP (fiber reinforced plastic) layers 4 on both sides of the AES + cork layer and the additional AES layer 2, and a pair of liquid barrier membranes 5 on both sides of the FRP layer 4. In this third preferred configuration, one or more AES layers act as a fire barrier and a heat insulation solution. Preferably, the FRP layer 4 is a GFRP layer.

[0044] Figure 4c Shows a fourth preferred embodiment, wherein the layer formed by the cork lattice 3 filled with AES 2 further includes a pair of FRP (fiber reinforced plastic) layers 4 on both sides of the layer composed of AES + cork, and a pair of liquid barrier membranes 5 on both sides of the FRP layer 4. In this fourth preferred configuration, the FRP layer acts as a fire barrier and a heat insulation solution. This fourth embodiment is very promising for direct integration as part of a composite structure. Preferably, the FRP layer 4 is a CFRP layer.

[0045] The first preferred embodiment ( Figure 1 ) has been tested by the Bunsen test. The test sample has a 2 mm AES layer 2 and an 8 mm cork layer 3, and the following conditions are applied:

[0046] - Direct flame impingement for 15 min.

[0047] - Calibrated flame at 1100 °C.

[0048] - No load or vibration applied.

[0049] - Protect the GFRP and PVF covering the two layers from the influence of fluids.

[0050] The result after 15 minutes of the required 1100 °C flame is that not only did no flame pass through, but the temperature measured at the rear of the specimen was 220 °C.

[0051] The third preferred embodiment that has been tested ( Figure 4b ) meets the FAR / JAR 25 regulations regarding firewalls FAR / JAR25.1191 and FAR / JAR25.865, namely:

[0052] - Direct flame impingement for 15 min.

[0053] - Calibrated flame at 1100 °C at a distance of 100 mm from the specimen.

[0054] - Calibrated heat flux.

[0055] - The specimen is under vibration at 50 Hz (reduced to 16.6 Hz after 5 min).

[0056] - No load is applied.

[0057] - The protective covering shields the core GFRP and PVF from the fluid.

[0058] The result after 15 minutes in the required 1100 °C flame is that not only does no flame pass through, but the temperature measured at the rear of the specimen is 240 °C, with a peak of approximately 300 °C at the fastener hot spot.

[0059] According to another aspect, the invention also relates to a composite part (non-structural part) that includes a fireproof and heat-insulating part product as shown in the first or second preferred embodiment. In these cases, the product is attached to the part by means of fasteners, by bonding or Velcro-type connection. In the case of attachment by means of fasteners, washers will preferably be used and installed so as to form an air chamber between the part and the product.

[0060] According to another preferred embodiment, the composite part (structural part) includes a fireproof and heat-insulating part product as shown in the third or fourth preferred embodiment. In these cases, product 1 is bonded or co-cured to the part.

[0061] The following is a list of potential embodiments of the proposed invention:

[0062] · Firewall at the rear end of the aircraft:

[0063] - Size limitation: fire and heat protection

[0064] - Modification: Replace the current titanium fire wall with a new protection based on the proposed solution (preferably the first or second preferred embodiment).

[0065] - Advantage: Improved safety, reduced RC. In the event of a fire, neither the flame nor the heat will affect the structure of the rear end of the aircraft, so there is no need to replace it after a fire incident.

[0066] According to another aspect, the invention also relates to a rear end of an aircraft 6 that includes an APU compartment 7 isolated by at least one fire wall 8, 9, 10, 11 that includes a fireproof and heat-insulating part product 1. Figure 5a An aircraft 6 with an APU compartment 7 at the rear end of the aircraft is shown. Figure 5b A detailed view of the APU compartment 7 and most of the walls of the APU compartment is shown: front fire wall 8, lateral fire walls 9, rear fire wall 10, and upper fire wall 11, where at least one of these walls includes a fireproof and heat-insulating part product 1.

[0067] · Front firewall at the rear end of the aircraft:

[0068] - Size limitation: Fire and heat protection

[0069] - Modification: Based on the proposed solution (preferably the third or fourth preferred embodiment), replace the current titanium fire wall and aluminum girder with a new protection.

[0070] - Advantage: Improved safety, reduced RC. In the event of a fire, neither the flame nor the heat will affect the structure of the fire wall. Therefore, there is no need to replace it after a fire incident.

[0071] According to another aspect, the present invention also relates to a front fire wall 8 including a fire and heat insulation product 1. Figure 6a and Figure 6b shows the front fire wall 8 of the APU compartment. Figure 6b shows the girder 13 that can be replaced with the proposed invention.

[0072] · Battery housing:

[0073] - Size limitation: Heat protection

[0074] - Modification: Based on the proposed solution, replace the current metal shell with a composite metal shell

[0075] - Advantage: Improved safety, reduced RC, reduced weight.

[0076] According to another aspect, the present invention also relates to a battery housing 14 including a fire and heat insulation product 1. Figure 7a shows an exploded view of the battery and its housing. Figure 7b shows a perspective view of the main elements of the housing.

[0077] · Composite fire protection duct:

[0078] - Size limitation: Heat protection

[0079] - Modification: Based on the proposed solution, preferably the third option, replace the current titanium pipe with a composite pipe.

[0080] - Advantage: Improved safety, reduced RC.

[0081] According to another aspect, the present invention also relates to a pipe including a fire and heat insulation product 1.

[0082] · Helicopter engine mount:

[0083] - Size limitation: Main structure, heat protection

[0084] - Modification: Replace the current titanium skin and spars with a composite sandwich with integrated fire and heat protection.

[0085] - Advantage: Weight reduction by implementing a CFRP composite engine mount design, with a mismatch in the coefficient of thermal expansion between the engine mount and the CFRP composite airframe.

[0086] According to another aspect, the present invention also relates to a helicopter engine mount 15 including a fire and heat insulation product 1. Figure 8 An engine mount 15 including a titanium skin, spars, clips, and gussets on an airframe 16 typically made of aluminum is shown.

[0087] · Central firewall in the helicopter engine compartment:

[0088] - Dimension limitations: Reinforcement panels, heat protection

[0089] - Modification: Replace the current reinforced titanium skin with a composite sandwich with integrated fire and heat protection.

[0090] - Advantage: Reduced maintenance and repair, added value for the customer

[0091] According to another aspect, the present invention also relates to a helicopter having an engine compartment including a central fire wall 17, the central fire wall including a fire and heat insulation product 1. Figure 9 A helicopter engine compartment having a central wall 17 including a fire and heat insulation product 1 is shown.

[0092] Although the present invention has been fully described in connection with the preferred embodiments, it is apparent that modifications can be introduced within the scope of the present invention without considering the scope of the present invention to be limited by these embodiments, but rather by the content of the appended claims.

Claims

1. A fireproof and heat-insulating part product (1), the fireproof and heat-insulating part product comprising the following: Alkaline earth silicate material (2), Liquid barrier film (5), Fiber-reinforced plastic layer (4), and Cork (3), Among them, The liquid barrier film (5) and the fiber-reinforced plastic layer (4) are stacked on the alkaline earth silicate material (2), And wherein, the cork (3) material is embedded in the alkaline earth silicate material (2), and the cork (3) is configured as a plurality of strips, thereby forming a grid structure filled with the alkaline earth silicate material (2).

2. The fireproof and heat-insulating part product (1) according to claim 1, wherein, The liquid barrier film (5) is a thermoplastic film.

3. The fireproof and heat-insulating part product (1) according to claim 1, wherein, The liquid barrier film (5) is a polyvinyl fluoride film, a polyether ether ketone film, a polyvinylidene fluoride film or a polyethylene terephthalate film.

4. The fireproof and heat-insulating part product (1) according to claim 1, wherein, The fiber-reinforced plastic layer (4) is a glass fiber-reinforced plastic layer or a carbon fiber-reinforced plastic layer.

5. The fireproof and heat-insulating part product (1) according to claim 1, further comprising an adhesive layer (6) to bond the liquid barrier film (5) to the alkaline earth silicate material (2).

6. The fireproof and heat-insulating part product (1) according to any one of claims 1 to 5, the fireproof and heat-insulating part product comprising a stack of layers, the stack of layers being formed by a cork layer embedded in the alkaline earth silicate material (2), and at least one alkaline earth silicate material layer or fiber-reinforced plastic layer (4) on top of the cork layer embedded in the alkaline earth silicate material (2), to enhance the fireproof property of the product (1).

7. The fireproof and heat-insulating part product (1) according to claim 6, further comprising a liquid barrier film (5) and / or a fiber-reinforced plastic layer (4) at least on the outer side of the product (1).

8. A composite part, said composite part comprising a fireproof and heat-insulating part product (1) according to any one of claims 1 to 5, wherein, The product (1) is attached to the part by means of fasteners, by bonding or by Velcro-type connection.

9. The composite part according to claim 8, wherein, The product (1) is attached to the part by means of fasteners and through a mounting washer, thereby forming an air chamber between the part and the product (1).

10. A composite part, the composite part comprising a fireproof and heat-insulating part product (1) according to any one of claims 6 to 7, wherein, The product (1) is bonded or co-cured to the part.

11. A rear end portion of an aircraft (6), the rear end portion comprising an auxiliary power unit compartment (7) isolated by at least one fireproof wall (8, 9, 10, 11), the at least one fireproof wall comprising the fireproof and heat-insulating part product (1) according to any one of claims 1 to 7.

12. A rear end portion of an aircraft (6), the rear end portion comprising an auxiliary power unit compartment (7) having at least one front fireproof wall (8), the at least one front fireproof wall comprising the fireproof and heat-insulating part product (1) according to any one of claims 6 to 7.

13. A pipeline, the pipeline comprising the fireproof and heat-insulating part product (1) according to any one of claims 6 to 7.

14. A battery housing (14), the battery housing comprising the fireproof and heat-insulating part product (1) according to any one of claims 1 to 7.

15. A helicopter, the helicopter having an engine mount (15), the engine mount comprising the fireproof and heat-insulating part product (1) according to any one of claims 1 to 7.

16. A helicopter, the helicopter having an engine compartment including a central fire wall (17), the central fire wall including a fireproof and heat-insulating product (1) according to any one of claims 1 to 7.

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