Firewall system

Abstract

A firewall system isolating a fire zone of an engine (2) from a hanger (1) located in a non-fire zone, comprising: a vertical firewall (3) arranged at a front end of a frame of the hanger, on which a support structure (13) is arranged for mounting the hanger and a fairing of the engine; and a bottom firewall (7) which is provided so as to extend rearward from the vertical firewall, is provided so as to cover the suspended frame from below, has a bottom plate (71), a left side plate (72), and a right side plate (73), and has an isolated space formed by the vertical firewall, the bottom firewall, and the suspended frame. Fireproof sealing isolation of an aircraft engine can be achieved, meanwhile, arrangement of multiple systems such as fuel oil, hydraulic pressure, an air source, fire prevention, power and EWIS is achieved, influences between the systems are avoided, and structural weight reduction can be achieved.

Description

Technical Field

[0001] This invention relates to a firewall system for isolating the engine fire zone and the aircraft non-fire zone. Background Technology

[0002] The firewall between aircraft engines is a crucial structure for isolating the engine's fire zone from the aircraft's non-fire zone. Furthermore, the firewall contains pre-installed openings for systems such as fire protection, fuel supply, hydraulics, air supply, and EWIS (Electronic Warfare Information System), making it an important part of the overall aircraft design. Its airworthiness, safety, and maintainability significantly impact the overall aircraft performance. The matching design of the aircraft engine firewall involves weighing the engine, nacelle, and aircraft pylons together through analysis, design optimization, and iterative iterations to ultimately arrive at the optimal system layout and firewall structure from a holistic aircraft perspective. Its technical level directly affects the aircraft's overall performance indicators, airline operations and maintenance, and airworthiness certification.

[0003] In reality, the passive implementation of system layout, maintainability simulation, aerodynamic efficiency optimization, and separation surface design for aircraft engine firewalls results in firewall designs with relatively low aerodynamic efficiency, large structural strength margins, poor maintainability, and poor fire protection, which affect the aircraft's economy, safety, and maintainability.

[0004] A fireproof sealing assembly for an aircraft engine is known, comprising a first L-shaped cover having a first leg and a second leg extending outward from the first leg, and a second L-shaped cover having a third leg and a fourth leg extending outward from the third leg. This prior art primarily designs the fireproof sealing assembly, without addressing specific schemes for aircraft engine firewalls or methods for separating the systems on both sides of the engine. Aircraft engine firewall design requires repeated consideration from a holistic, overall perspective, necessitating simultaneous overall spatial planning for both the aircraft and engine firewalls, as well as detailed digital prototype design for subsystems. However, current aircraft engine firewall layout design methods generally passively accept engine and system design inputs, failing to conduct active system layout spatial planning and fireproof isolation for the aircraft engine firewall, and failing to consider the frequent maintenance requirements and aerodynamic drag reduction needs throughout the aircraft's life cycle.

[0005] Furthermore, a known technology achieves multi-system layout and fire protection through a combination of fire-resistant frames and vertical firewalls. In the cold-side air supply design of some aircraft models, the entire system, including the fan inlet device, compensation device, fan air valve, and precooler, is arranged in the suspended non-fire zone. While this arrangement eliminates the need for fire protection considerations in the cold-side bleed air duct and precooler system design, resulting in weight reduction advantages in the bleed air system, the numerous bends in the firewall complicate the structure of the corresponding fire-resistant seals. Additionally, in some aircraft engine firewall designs, the bottom firewall uses a fire-resistant frame, which increases design weight and maintenance difficulty. Moreover, a systematic design methodology and flexible integration of vertical firewalls with multi-system design devices have not been established. Summary of the Invention

[0006] The purpose of this invention is to provide a firewall system for aircraft engines that can achieve fireproof sealing and isolation of aircraft engines, while accommodating the arrangement of multiple systems such as fuel, hydraulic, air source, fire protection, power, and EWIS and avoiding interference between systems, reducing the width of the mounting, reducing aerodynamic drag, and achieving structural weight reduction.

[0007] This invention relates to a firewall system that isolates the engine's fire zone from a suspension located in the non-fire zone. The system includes: a vertical firewall disposed at the front end of the suspension frame, with a support structure on the vertical firewall for mounting the suspension and the engine cowling; and a bottom firewall extending rearward from the vertical firewall and covering the suspension frame from below. The bottom firewall has a bottom plate, a left side plate, and a right side plate. An isolation space is formed by the vertical firewall, the bottom firewall, and the suspension frame.

[0008] The firewall system described above uses a vertical firewall, a bottom firewall, and a suspended frame to create an isolation space, achieving separation between the fire zone and the non-fire zone. Compared to previous fireproof frames or side firewalls, this design achieves structural weight reduction, a smaller aerodynamic profile, and lower aerodynamic drag.

[0009] Ideally, a fireproof seal is installed on the support structure, which is arranged along the outer periphery of the support structure, and the outer contour of the support structure corresponds to the outer contour of the hanging device.

[0010] This further achieves fireproof sealing, and since the outer contour of the support structure corresponds to the outer contour of the suspension, it further reduces aerodynamic resistance.

[0011] In addition, a front mounting section is provided on the vertical firewall, and a rear mounting section is provided on the bottom firewall. The engine fan compartment is fixed to the vertical firewall and the bottom firewall via the front mounting section and the rear mounting section, respectively.

[0012] This structure simplifies the structure and installation process while ensuring a stable installation.

[0013] In addition, the front mounting section is provided with an EWIS reserved through-frame hole for the EWIS system cables to pass through.

[0014] In this way, the front mounting section not only serves to isolate the fire zone, but also provides space for the EWIS system to be arranged and pass through the frame.

[0015] Ideally, the vertical firewall is also provided with at least one of the following: a fireproof wall opening for liquid pipelines, a fireproof wall opening for gas source start-up pipelines, a fireproof wall opening for fan compartment fire extinguishing pipelines, and a fireproof wall opening for EWIS.

[0016] By setting these through-frame holes, the fire zone and non-fire zone can be isolated while allowing for the through-frame connection of fuel hydraulic lines, EWIS cables, high-temperature gas supply lines, and other pipelines.

[0017] In addition, the bottom firewall is provided with at least one of the following: a firewall frame opening for the gas source system, a firewall frame opening for the fire protection system, and a firewall frame opening for the EWIS system. The firewall frame opening for the gas source system allows the fan exhaust pipe to pass through, the firewall frame opening for the fire protection system allows the core compartment fire extinguishing pipe to pass through, and the firewall frame opening for the EWIS system allows the pressure sensing pipe of the gas source and the EWIS cable to pass through.

[0018] Based on this structure, it is also possible to achieve frame-to-frame connection of gas supply systems, fire protection systems, and EWIS systems while isolating fire zones from non-fire zones.

[0019] In addition, an inter-system isolation structure is provided on the suspended frame. The inter-system isolation structure includes at least two partitions, which divide the fuel hydraulic pipeline layout compartment, the gas source equipment and pipeline layout compartment, and the EWIS cable layout compartment.

[0020] By setting up isolation structures between systems, the systems can be arranged in separate compartments. For example, fuel and hydraulic lines can be arranged in one compartment, starting lines (high temperature) in another, and the EWIS wiring harness in a separate compartment. Through this compartmentalized arrangement, the isolation distance between each system can be minimized, thereby reducing the width of the sling, aerodynamic drag, and weight.

[0021] Ideally, a left maintenance port is provided on the left side panel of the bottom firewall, and a right maintenance port is provided on the right side panel of the bottom firewall.

[0022] This allows for the operation and maintenance of the system and structure. Attached Figure Description

[0023] Figure 1 This is a schematic diagram showing the general structure of the engine system of an aircraft according to an embodiment of the present invention.

[0024] Figure 2 This is a perspective view showing the structure of the firewall of the engine according to an embodiment of the present invention.

[0025] Figure 3 This is a partial perspective view showing the vertical firewall and its surrounding structure according to an embodiment of the present invention.

[0026] Figure 4 This is a top view showing the internal structure of the suspension according to an embodiment of the present invention.

[0027] Figure 5 This is a perspective view showing the structure of the firewall of the engine according to an embodiment of the present invention, as viewed from below.

[0028] Figure 6 This is a perspective view showing the structure of the fire zone of the engine according to an embodiment of the present invention.

[0029] Figure 7 This is a perspective view showing the internal structure of the hanging device according to an embodiment of the present invention.

[0030] Figure 8 This is a perspective view showing the piping layout of the fire zone of the engine according to an embodiment of the present invention.

[0031] (Symbol Explanation)

[0032] 1 hanging

[0033] 2 engines

[0034] 3 Vertical Firewalls

[0035] 4 front installation section

[0036] 5EWIS pre-drilled frame holes

[0037] 6. Inter-system isolation structure

[0038] 7 Bottom Firewall

[0039] 8 Gas source system firewall through frame hole

[0040] 9 Fire protection system firewall through-frame hole

[0041] 10EWIS system firewall through-frame hole

[0042] 11. Left Maintenance Port (To the Left of the Course)

[0043] 12 Rear Installation Section Installation Part

[0044] 13 Supporting Structure

[0045] 14 Fireproof seals

[0046] 15 Fuel and Hydraulic Piping Arrangement Compartment

[0047] 16 Gas source equipment and pipeline layout compartment

[0048] 17EWIS Cable Laying Cabin

[0049] 18 partitions

[0050] 19 Right Maintenance Port

[0051] 20 fan compartments

[0052] 21 core modules

[0053] 22 Liquid Piping Firewall Through-Frame Hole

[0054] 23 Gas source start-up pipeline firewall through frame hole

[0055] 24. Fire extinguishing pipes in the fan compartment pass through the frame opening.

[0056] 25EWIS Firewall Through-Frame Hole

[0057] 26 Core Module Fire Extinguishing Piping

[0058] 27 Fan exhaust pipe

[0059] 28EWIS cable Detailed Implementation

[0060] The following describes specific embodiments of the present invention. It should be noted that, in order to provide a concise description, this specification cannot exhaustively describe all features of the actual embodiments. It should be understood that, in the actual implementation of any embodiment, just as in any engineering or design project, various specific decisions are often made to achieve the developer's specific goals and to meet system-related or business-related constraints, and this can change from one embodiment to another. Furthermore, it is understood that although the efforts made in this development process may be complex and lengthy, for those skilled in the art related to the content disclosed in this invention, some design, manufacturing, or production modifications based on the technical content disclosed herein are merely conventional technical means and should not be construed as insufficient content of this disclosure.

[0061] Unless otherwise defined, the technical or scientific terms used in the claims and description shall have the ordinary meaning understood by one of ordinary skill in the art to which this invention pertains. The terms "first," "second," and similar terms used in the patent application description and claims of this invention do not indicate any order, quantity, or importance, but are merely used to distinguish different components. The terms "an" or "a" and similar terms do not indicate a quantity limitation, but rather indicate the presence of at least one. The terms "comprising" or "including" and similar terms mean that the element or object preceding "comprising" or "including" encompasses the element or object listed following "comprising" or "including" and its equivalents, and do not exclude other elements or objects. The terms "connected" or "linked" and similar terms are not limited to physical or mechanical connections, nor are they limited to direct or indirect connections.

[0062] In the following description, numerous directional terms will be used to clearly illustrate the structure and operation of the present invention. However, terms such as "front," "rear," "left," "right," "outer," "inner," "outward," "inward," "upward," and "downward" should be understood as convenient terms and not as limiting terms. It is particularly important to note that "front" and "rear" are determined based on the air intake direction. "Left" and "right" refer to left and right when viewed from the front of the engine.

[0063] Figure 1 This is a schematic diagram showing the general structure of the engine system of an aircraft according to an embodiment of the present invention. For example... Figure 1 As shown, the aircraft engine system of the present invention mainly includes a pylon 1 and an engine 2. The pylon 1 has a frame, and the engine 2 has a fan zone as the fire zone and a non-fire zone.

[0064] like Figure 2 As shown, a system isolation structure 6 is installed on the frame of the suspension 1. This system isolation structure 6 enables the compartmentalized arrangement of systems. For example, it allows for the isolation of fuel and hydraulic lines in one compartment, the isolation of starting lines (high temperature) in another compartment, and the EWIS wiring harness in a separate compartment. This compartmentalized arrangement minimizes the isolation distance between systems, thereby reducing the width of the suspension, aerodynamic drag, and weight. The specific structure and compartmentalized arrangement of the system isolation structure 6 will be described in detail later.

[0065] Figure 2 This is a perspective view showing the structure of the firewall of the engine according to an embodiment of the present invention. Figure 2 As shown, the engine is equipped with a vertical firewall 3 and a bottom firewall 7. By installing the vertical firewall 3 and the bottom firewall 7, the engine's fire zone is isolated from the suspension located in the non-fire zone.

[0066] Figure 3 This is a partial perspective view showing the vertical firewall and its surrounding structure according to an embodiment of the present invention. The vertical firewall 3 is used to isolate the non-fire zone of the suspension and the fan compartment of the engine, i.e., the fire zone. In addition, the vertical firewall 3 is used to realize the frame connection and sealing of the systems on both sides of the engine. The vertical firewall 3 is disposed at the front end of the frame of the suspension 1. To achieve these functions, such as Figure 3 As shown, a support structure 13 is provided on the vertical firewall 3, which is used to install the pylon 1 and the engine cowling. Furthermore, a fireproof seal 14 is installed on the support structure 13, which is positioned along its outer perimeter. Fuel, hydraulic, air supply, and EWIS systems are generally arranged on the rearward side of the vertical firewall 3, and the outer contour of the vertical firewall 3 corresponds to the outer contour of the pylon 1. In addition, the vertical firewall 3 is provided with interfaces for hydraulic lines, fuel lines, air supply lines, and fire extinguishing pipes for the aircraft engine system, as well as through-wall seals for power and signal wiring harnesses (not shown).

[0067] A front mounting section 4 is also provided on the vertical firewall 3. The front mounting section 4 not only isolates the fire zone, but also provides space for the EWIS system to be arranged and pass through the frame. The front mounting section 4 is provided with EWIS reserved frame holes 5 for the EWIS system cables to pass through.

[0068] In addition, such as Figure 7 As shown, the vertical firewall 3 is also equipped with a firewall frame through-hole 22 for liquid pipelines, a firewall frame through-hole 23 for gas source start-up pipelines, a firewall frame through-hole 24 for fan compartment fire extinguishing pipelines, and a firewall frame through-hole 25 for EWIS. By setting these through-holes, the fire zone and non-fire zone are isolated while allowing the fuel pipelines, hydraulic pipelines, high-temperature gas source pipelines, EWIS cables, and other pipelines to pass through the frame.

[0069] Regarding inter-system isolation structure 6, such as Figure 4 As shown, the system isolation structure 6 of the present invention isolates the high-temperature gas source pipeline, fuel hydraulic pipeline (if any), EWIS cable, and other pipelines respectively, meeting the overall design requirements such as environmental drainage and clearance. As an example, the system isolation structure 6 includes two partitions 18, which divide the fuel hydraulic pipeline arrangement compartment 15, the gas source equipment and pipeline arrangement compartment 16, and the EWIS cable arrangement compartment 17.

[0070] Next, we will provide a detailed explanation of the bottom firewall 7.

[0071] like Figure 6 As shown, the bottom firewall 7 is used to isolate the non-fire zone of the aircraft and the fire zone 21 of the engine core compartment. Furthermore, the bottom firewall 7 can facilitate the cross-frame connection of the aircraft engine interconnection system. Figure 2 As shown, the bottom firewall 7 extends rearward from the vertical firewall 3 to cover the frame of the hanging 1 from below, and has a bottom plate 71, a left side plate 72, and a right side plate 73. The vertical firewall 3, the bottom firewall 7, and the frame of the hanging 1 form a generally enclosed isolation space.

[0072] The bottom plate of the bottom firewall 7 is equipped with firewall frame access holes 8 for the air supply system, 9 for the fire protection system, and 10 for the EWIS system. The fan bleed air duct 27, which is typically required for certain aircraft models, can be connected to the bottom firewall 7 via the firewall frame access hole 8 for fire and non-fire zones. The core compartment fire suppression piping is located according to the fire suppression requirements provided by the engine environmental specialists, and the core compartment fire suppression piping 26 is connected to the firewall frame access hole 9 for fire and non-fire zones. The pressure sensing piping of the air supply and the EWIS cable 28 are connected to the bottom firewall 7 at the rearward direction via the EWIS system firewall frame access hole 10. Furthermore, a thrust rod hole is pre-drilled on the rearward side of the bottom firewall 7 for engine thrust rod installation.

[0073] like Figure 2 and Figure 5 As shown, the left maintenance port 11 and the right maintenance port 19 are designed on the left and right side panels of the bottom firewall 7, respectively, which can realize the installation and maintenance of the system and structure in the hanging box section.

[0074] In addition, a rear mounting section 12 is provided on the bottom plate of the bottom firewall 7, which is used to fix the rear mounting section. The aircraft's engine fan nacelle 20 is fixed to the aircraft's firewall via the forward mounting section 4 and the rear mounting section respectively.

[0075] The fuel system typically includes a fuel supply line on the firewall of an aircraft engine. Since aviation fuel is a significant factor affecting aircraft safety, the design of this fuel line must fully consider various maintenance and leak-proof requirements during the manufacturing and operational phases. Specific methods are as follows:

[0076] 1) Determine the fuel design requirements based on the specific engine model selected and the overall aircraft requirements;

[0077] 2) Determine whether to use double-layer sleeves for fuel supply lines to reduce the risk of leakage, based on airworthiness regulations and specific top-level design requirements of the aircraft;

[0078] 3) If double-layer sleeve is selected, determine the lowest point of the pipeline relative to the horizontal ground according to the pipeline laying situation, and comprehensively weigh the impact of the fuel pipeline passing through the frame at the firewall based on the lowest point of the drain.

[0079] 4) Determine the diameter D1 of the fuel line and the maximum diameter D2 at the drain connector based on the above inputs;

[0080] 5) Determine whether to use quick-release couplings based on the frequency of aircraft engine production testing and delivery operation maintenance;

[0081] 6) If it is determined that a quick-release coupling is to be used, the corresponding quick-release coupling can be selected according to the fuel line diameter D1, and the maximum diameter D3 of the quick-release coupling can be determined. If a quick-release coupling is not used, a flange connection is generally used, and the diameter of the connecting flange is recorded as D4.

[0082] 7) Based on the previous process, the quick-release connector scheme is selected. Generally, the firewall layout scheme is designed based on the D3 dimension. The flange connector scheme is selected. Generally, the maximum value of D3 and D4 is used for the firewall fuel pipeline passing through the frame scheme design.

[0083] Furthermore, depending on the engine's thrust reverser configuration, the hydraulic system typically has three or more hydraulic lines on the engine firewall. These hydraulic lines generally have the same lifespan as the aircraft. However, since hydraulic oil is a potential hazard, the design of these multiple hydraulic lines must fully consider manufacturing costs, pressure loss, and the possibility of line disconnections at the engine firewall. The specific process is as follows:

[0084] 1) Determine the overall hydraulic system architecture based on the aircraft pressure system, flight conditions, hydraulic users, engine speed, etc.

[0085] 2) Based on the hydraulic system architecture, information such as the diameter of the three pipes connected to the engine drive pump (EDP) can be preliminarily determined;

[0086] 3) Determine the thrust reverser configuration of the engine based on the overall machine design requirements and the product racks;

[0087] 4) If hydraulic thrust reversers are used, determine the number and size of the additional piping required for hydraulic thrust reversers based on information such as the thrust reverser architecture provided by the engine or nacelle supplier.

[0088] 5) If electric thrust reverser is used, determine the number and size of the additional EWIS cables, and determine the impact on the EWIS scheme at the aircraft engine firewall based on the installation location of the thrust reverser.

[0089] 6) If quick-release couplings are to be used, the hydraulic line diameter d1-d can be used as a reference. n (n is generally greater than or equal to 3), select the appropriate quick-release coupling, and determine the maximum diameter K1-K of the quick-release coupling. n If quick-release couplings are not used, flange connections are generally used, with the flange diameters denoted as F1-F. n (Flanges are generally round; if they are not round, the diameter of the flange's circumscribed circle shall be used.)

[0090] 7) Based on the previous process, if the quick-release coupling option is selected, it is generally K1-K n When designing the hydraulic layout scheme for a firewall, the flange joint scheme is typically selected, usually F1-F. n The dimensions of the firewall hydraulic pipeline through the frame hole design were carried out.

[0091] The design of firewalls for fuel, hydraulic, and other subsystems, as well as aircraft engines, is an interconnected process and should be carried out in parallel during actual design. Based on the definition of engine fire zones, the engine fan nacelle and core compartment are generally designated fire zones. Aircraft pylons are connected to the engine's fire zones, and firewalls are required at the interfaces with the engine and nacelles to prevent potential fires. This invention designs vertical firewalls and bottom firewalls. The overall layout design method for the firewall system is as follows:

[0092] 1) Identify the systems connected to the aircraft engine, and based on the professional layout and installation requirements of each system, identify the layout design elements at the aircraft engine firewall, such as safety, economy, and maintainability.

[0093] 2) Based on the main design elements, formulate preliminary design requirements for the firewall layout of the aircraft engine;

[0094] 3) Determine and confirm the completeness and correctness of the firewall layout design requirements for aircraft engines, such as whether the design clearances, specific risks (bird strikes, rotor explosions, etc.), maintainability (including manufacturability), ventilation and drainage are comprehensive and accurate.

[0095] 4) Based on airworthiness regulations, aircraft-level requirements, engine requirements, and design requirements of various aircraft subsystems, formulate firewall layout design requirements for aircraft engines.

[0096] 5) Quantify or geometricize the layout design requirements, such as requiring the system to maintain a reasonable gap from the structure, which can be determined as 5mm-25.4mm depending on the specific situation; determine the affected area and geometricize it based on the potential leakage liquid; determine the geometric range of the bird strike area based on the bird strike risk, etc.

[0097] 6) Coordinate all influencing factors (generally including aerodynamics, shape, structure, system, characteristics, process, etc.), check the completeness and correctness of the firewall layout design requirements for the aircraft engine, and after confirmation, form a formal firewall layout design requirements report for the aircraft engine.

[0098] 7) Based on the firewall layout design requirements report for aircraft engines and related MICD documents, determine the fire zone and non-fire zone ranges of aircraft engines, the wall interface and insulation layer thickness, and the overall nacelle design, etc.

[0099] 8) With the design goals of low aerodynamic drag, good maintainability, low manufacturing and installation costs, and maintaining safe design clearances, conduct firewall space allocation for aircraft engines, coordinate the joint design of structures and systems, and form a preliminary firewall layout scheme for aircraft engines.

[0100] 9) Conduct inspections and optimizations of the preliminary firewall layout plan for aircraft engines;

[0101] 10) After the preliminary layout plan is determined, the design of the three-dimensional spatial distribution prototype of the aircraft engine firewall will be carried out. The spatial distribution prototype includes the geometric spatial positions of each system, pipeline joint positions, main maintenance port positions, fire zone and non-fire zone isolation positions, etc.

[0102] 11) After the design of the three-dimensional spatial allocation prototype of the aircraft engine firewall was completed, it was repeatedly evaluated and confirmed, and the spatial allocation prototype was iterated based on feedback.

[0103] 12) After confirming the space allocation prototype, the design of the aircraft-side system digital prototype and the engine (including nacelle)-side system digital prototype will be carried out simultaneously;

[0104] 13) After the digital prototypes for the aircraft side and engine side are designed, assemble the digital prototype of the firewall and confirm the integrity and accuracy of the digital prototype;

[0105] 14) Conduct joint reviews of firewall solutions, including reviews and confirmations on airworthiness, economy, maintainability, security, and manufacturability;

[0106] 15) Form a firewall system layout scheme for the engine.

[0107] The firewall system according to an embodiment of the present invention incorporates both a vertical firewall and a bottom firewall, achieving isolation between fire zones and non-fire zones while increasing the space available for the aircraft engine system and improving overall maintainability. Compared to conventional fireproof frames or side firewalls, it achieves structural weight reduction and aerodynamic surface area reduction, thus lowering aerodynamic drag. Furthermore, the vertical firewall and bottom firewall facilitate the installation of cross-frame joints for multiple systems such as fuel, hydraulics, air supply, fire protection, and EWIS, enabling centralized maintenance and, in particular, improving the maintainability of engine start / stop systems.

[0108] The embodiments and variations of the present invention have been described above. However, it should be understood that this disclosure is not limited to the above embodiments and structures. This disclosure also includes various variations and modifications within the equivalent scope. In addition, various combinations and methods, and further combinations and methods that include only one element or more or less thereof, also fall within the scope and spirit of this disclosure.

Claims

1. A fire wall system separating a fire zone of an engine (2) from a hanger (1) located in a non-fire zone, characterized in that, Comprising: a vertical firewall (3) provided at the front end of the suspended frame, on which a support structure (13) is provided for mounting the suspended frame and the nacelle of the engine; and a bottom firewall (7) extending rearward from the vertical firewall and provided in a manner of covering the suspended frame from below, having a bottom plate (71), a left side plate (72) and a right side plate (73), an isolated space is formed by the vertical firewall, the bottom firewall and the suspended frame.

2. The firewall system according to claim 1, wherein a fireproof seal (14) is mounted on the support structure, which is provided along the outer periphery of the support structure, the outer contour of the support structure corresponds to the outer contour of the suspended frame.

3. The firewall system according to claim 1 or 2, wherein a front mounting section (4) is provided on the vertical firewall, a rear mounting section is provided on the bottom firewall, the fan compartment (20) of the engine is fixed to the vertical firewall and the bottom firewall via the front mounting section and the rear mounting section respectively.

4. The firewall system according to claim 3, wherein an EWIS reserved through-hole (5) is provided on the front mounting section, for the cables of the EWIS system to pass through.

5. The firewall system according to claim 1 or 2, wherein at least one of a liquid pipeline firewall through-hole (22), an air source starting pipeline firewall through-hole (23), a fan compartment fire extinguishing pipeline through-hole (24) and an EWIS firewall through-hole (25) is further provided on the vertical firewall.

6. The firewall system according to claim 1 or 2, wherein at least one of an air source system firewall through-hole (8), a fire protection system firewall through-hole (9) and an EWIS system firewall through-hole (10) is provided on the bottom firewall, the air source system firewall through-hole is for the fan bleed air pipeline (27) to pass through, the fire protection system firewall through-hole is for the core compartment fire extinguishing pipeline (26) to pass through, and the EWIS system firewall through-hole is for the air source pressure sensing pipeline and the EWIS cable (28) to pass through.

7. The firewall system according to claim 1, wherein a system isolation structure (6) is provided on the suspended frame, which includes at least two partitions (18) that divide the fuel hydraulic pipeline arrangement compartment (15), the air source equipment and pipeline arrangement compartment (16) and the EWIS cable arrangement compartment (17).

8. The firewall system according to claim 1 or 2, wherein a left maintenance opening (11) is provided on the left side plate of the bottom firewall.

9. The firewall system according to claim 1 or 2, wherein a right maintenance opening (19) is provided on the right side plate of the bottom firewall.

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