A method of replacing a helicopter engine

Abstract

The application discloses a method for replacing a helicopter engine, which comprises the following steps: S1, determining the performance parameters and structural features of a replacement engine and performing analysis; S2, determining the mounting interface between the replacement engine and the helicopter and performing analysis; S3, when the mounting interface between the replacement engine and the helicopter is not matched, analyzing the influence of the mounting interface change of the replacement engine and / or the helicopter on the helicopter; and S4, obtaining an overall technical scheme for replacing the helicopter engine based on the analysis results of S1-S3, and carrying out the replacement work of the helicopter engine according to the overall technical scheme. The application can comprehensively consider the matching and applicability between the replacement engine and the helicopter, ensure that the replacement engine can normally and reliably work after being mounted, improve work efficiency and reduce technical risks.

Description

Technical Field

[0001] This application relates to the field of helicopter overall design technology, and in particular to a method for replacing a helicopter engine. Background Technology

[0002] Modern helicopters, characterized by low-altitude, low-speed, and vertical takeoff and landing capabilities, play a vital role in human production and daily life, primarily in transportation, patrol, tourism, and rescue operations. Modern helicopters typically use turboshaft engines as their power plant. These engines are installed in the helicopter's engine bay and mechanically connected to the main gearbox via a power output shaft, thereby driving the rotor and tail rotor to rotate at a predetermined speed. This demonstrates the crucial role of the engine in the normal operation of a helicopter; therefore, the engine is often referred to as the "heart of the helicopter."

[0003] The turboshaft engine is the heart of a helicopter, directly determining its overall performance. Replacing the engine is an effective way to improve a helicopter's mission capability, expand its operational scope, and optimize maintenance costs. However, there is no universally applicable method for replacing helicopter engines in the current technology, resulting in a lack of theoretical guidance during the actual replacement process, technical risks, and impacts on work progress and efficiency. Summary of the Invention

[0004] In view of this, this application provides a method for replacing a helicopter engine, which can quickly and comprehensively consider the compatibility and applicability between the replacement engine and the helicopter, ensuring that the replacement engine works normally and reliably after installation, while improving work efficiency and reducing technical risks.

[0005] According to one aspect of this application, a method for replacing a helicopter engine is provided, comprising:

[0006] S1. Determine and analyze the performance parameters and structural characteristics of the replacement engine;

[0007] S2, determine and analyze the installation interface between the replacement engine and the helicopter;

[0008] S3, When the installation interface between the replacement engine and the helicopter is not compatible, analyze the impact of the change in the installation interface of the replacement engine and / or the helicopter on the helicopter;

[0009] S4. Based on the analysis results of S1 to S3, a general technical solution for replacing the helicopter engine is obtained, and the replacement of the helicopter engine is carried out in accordance with the general technical solution.

[0010] By employing the above technical solution, this application provides a method for replacing a helicopter engine. First, the performance parameters and structural characteristics of the replacement engine can be determined, and it can be analyzed whether these parameters and characteristics meet the requirements of the helicopter to be replaced. Further, the installation interface of the replacement engine can be determined, and it can be analyzed whether the installation interface matches the helicopter's installation interface. If the installation interfaces between the replacement engine and the helicopter do not match, further analysis can be conducted on what adaptive adjustments need to be made to the replacement engine and / or the helicopter, and necessary calculations, simulations, and experiments can be performed to provide a basis for the engine replacement plan. Finally, based on the above analysis results, the overall technical solution for replacing the helicopter engine can be obtained. This application's embodiments, by quickly and comprehensively considering the compatibility and applicability between the replacement engine and the helicopter, ensure the normal and reliable operation of the replacement engine after installation, while improving work efficiency and reducing technical risks.

[0011] The above description is only an overview of the technical solution of this application. In order to better understand the technical means of this application and to implement it in accordance with the contents of the specification, and to make the above and other objects, features and advantages of this application more obvious and understandable, the following are specific embodiments of this application. Attached Figure Description

[0012] The accompanying drawings, which are included to provide a further understanding of this application and form part of this application, illustrate exemplary embodiments and are used to explain this application, but do not constitute an undue limitation of this application. In the drawings:

[0013] Figure 1 A schematic flowchart of a helicopter engine replacement method provided in an embodiment of this application is shown;

[0014] Figure 2 This diagram illustrates the impact of an interface change on various parts of a helicopter, as provided in an embodiment of this application. Detailed Implementation

[0015] The present application will be described in detail below with reference to the accompanying drawings and embodiments. It should be noted that, unless otherwise specified, the embodiments and features described in the embodiments of the present application can be combined with each other.

[0016] This embodiment provides a method for replacing a helicopter engine, such as... Figure 1 As shown, the method includes:

[0017] Step S1: Determine and analyze the performance parameters and structural characteristics of the replacement engine;

[0018] Step S2: Determine and analyze the installation interface between the replacement engine and the helicopter;

[0019] Step S3: When the installation interface between the replacement engine and the helicopter is mismatched, analyze the impact of the change in the installation interface of the replacement engine and / or the helicopter on the helicopter.

[0020] Step S4: Based on the analysis results of S1 to S3, a general technical solution for replacing the helicopter engine is obtained, and the replacement of the helicopter engine is carried out according to the general technical solution.

[0021] The helicopter engine replacement method provided in this application can be applied to scenarios where helicopter engines are being replaced. In helicopter applications, it is often necessary to replace the engine to improve the overall performance or safety of the helicopter. The helicopter engine replacement method provided in this application can quickly and comprehensively consider the compatibility and applicability between the replacement engine and the helicopter, ensuring normal and reliable operation after the replacement engine is installed, while improving work efficiency and reducing technical risks.

[0022] Optionally, the analysis priority of the performance parameters and structural features is determined based on the target requirements. Step S1, "determining and analyzing the performance parameters of the replacement engine," includes: determining the power and fuel consumption rate of the replacement engine in each major operating state, and analyzing whether the power and fuel consumption rate in each major operating state meet the power requirements of the helicopter; determining the lifespan of the replacement engine, and analyzing whether the lifespan matches the overhaul interval of the helicopter; "determining and analyzing the structural features of the replacement engine," includes: determining the structural form, intake and exhaust methods, weight, and external dimensions of the replacement engine, and analyzing whether the structural features meet the installation requirements of the helicopter.

[0023] Furthermore, the performance parameters and structural characteristics of the replacement engine are determined, and its compliance with helicopter requirements is analyzed. Different priorities can be determined based on the user's target needs. If the user has specific performance requirements for the replacement engine, then engine power, fuel consumption rate, and lifespan are key concerns and have priority. The power and fuel consumption rate of the replacement engine in each major operating state are determined, and it is analyzed whether the power and fuel consumption rate in each major operating state meet the helicopter's power requirements, with a focus on analyzing the degree of satisfaction with the helicopter's power requirements in conjunction with the mission scenario. Here, the power of each major operating state can include maximum power, intermediate power, maximum continuous power, and idle power. The lifespan of the replacement engine is determined, generally calculated using operating hours. Based on the above analysis, the power of the replacement engine in each major operating state is not less than the helicopter's required power, the fuel consumption rate of the replacement engine in each major operating state is not greater than the helicopter's fuel consumption rate requirement, and the lifespan of the replacement engine is further improved compared to the original engine, and is an integer multiple of the helicopter's overhaul interval, indicating that the performance parameters of the replacement engine meet the helicopter's power requirements.

[0024] If the user has specific requirements regarding the installation method of the replacement engine, then the engine's structural characteristics are a key focus and have priority. The structural form, intake and exhaust methods, weight, and overall dimensions of the replacement engine must be determined to ensure they meet the helicopter's installation requirements. Based on the above analysis, if the installation method of the replacement engine remains consistent with the original engine, and the helicopter requires no adaptation modifications or the modification workload is within the user's acceptable range, then the structural characteristics of the replacement engine meet the helicopter's installation requirements.

[0025] Optionally, in step S2, "determine and analyze the installation interface between the replacement engine and the helicopter," the installation interface includes a mechanical installation interface and a system installation interface. The mechanical installation interface includes at least one of the following: engine body mounting section, connection between the engine air intake and the helicopter air intake, engine exhaust pipe, interface between the engine power output shaft and the main reducer, and engine control system installation interface. The system installation interface includes at least one of the following: engine fuel system interface, lubricating oil system interface, anti-icing bleed air system interface, starting electrical system interface, and CNC system electrical interface.

[0026] Furthermore, the installation interfaces between the replacement engine and the helicopter were determined, and the compatibility between the replacement engine's installation interface and the helicopter's installation interface was analyzed, with a focus on identifying any mismatches. The installation interfaces include mechanical installation interfaces and system installation interfaces. Mechanical installation interfaces include the engine body mounting section, the connection between the engine air intake and the helicopter air intake, the engine exhaust pipe, the interface between the engine power output shaft and the helicopter main gearbox, and the engine control system installation interface. System installation interfaces include the fuel system interface, lubrication system interface, anti-icing bleed air system interface, starting electrical system interface, and CNC system interface.

[0027] Optionally, step S3 includes: when the installation interface between the replacement engine and the helicopter is not compatible, analyzing the impact of the change in the installation interface of the replacement engine and / or the helicopter on the airframe structure of the helicopter and various systems of the helicopter, the systems including at least the power system, fuel system, avionics system, electrical system, electromechanical management system and fire suppression system.

[0028] Optionally, the "analysis of the impact of the replacement engine and / or the change of the helicopter's mounting interface on the helicopter's airframe structure" includes: analyzing the impact of the replacement engine on the helicopter's main power transmission path and structural integrity after the installation interface of the replacement engine and / or the helicopter is changed; analyzing the static strength and fatigue life of the helicopter's overall structure when the helicopter's airframe structure undergoes significant changes; analyzing the impact of the replacement engine on the helicopter's power compartment and power platform; analyzing whether there is interference between the replacement engine and the helicopter's power compartment, and when interference exists, making adaptive adjustments to the local structure of the helicopter's power compartment, ensuring that the adjusted power compartment's fairing aerodynamic shape, internal structural components, ventilation and cooling capacity, fire suppression capacity, and internal maintenance and inspection meet the helicopter's preset power compartment requirements.

[0029] Optionally, the "analysis of the impact of the replacement engine and / or the change of the helicopter's mounting interface on the helicopter's power system" includes: when the replacement engine and / or the helicopter's mounting interface is changed, analyzing the impact of the replacement engine on the engine mounting system, engine intake and exhaust system, and engine control system; comparing the differences between the replacement engine's center of gravity, mounting position, and connection form and the original engine of the helicopter, and making adaptive adjustments; comparing the differences between the replacement engine's control method and the original engine of the helicopter, and redesigning the engine control-related system when the control method changes.

[0030] Optionally, the "analysis of the impact of the change of the installation interface of the replaced engine and / or the helicopter on the fuel system of the helicopter" includes: analyzing whether the fuel system meets the fuel inlet requirements of the replaced engine after the change of the installation interface of the replaced engine and / or the helicopter. The fuel inlet requirements include the mechanical interface requirements of the fuel supply line, fuel flow requirements, fuel pressure requirements, fuel temperature requirements, and fuel purity requirements.

[0031] Optionally, the "analysis of the impact of the replacement engine and / or the change of the helicopter's installation interface on the helicopter's avionics system" includes: analyzing whether the display of the replacement engine's operating parameters and the fault alarm indication are normal after the change of the replacement engine and / or the helicopter's installation interface, and when abnormal, making adaptive changes to the control display unit software, multi-function display software, and monitoring software.

[0032] Optionally, the "analysis of the impact of the replacement engine and / or the change of the installation interface of the helicopter on the electrical system of the helicopter" includes: after the replacement engine and / or the installation interface of the helicopter is changed, when the engine starter generator or the matching auxiliary power unit participates in the power supply of the helicopter's power system, calculating the power capacity and electrical load, and analyzing whether the calculation results meet the power system requirements of the helicopter.

[0033] Optionally, the "analysis of the impact of the replacement engine and / or the change of the installation interface of the helicopter on the electromechanical management system of the helicopter" includes: analyzing the interface compatibility between the electromechanical management system and other electromechanical systems, avionics systems and flight parameter recording systems of the helicopter after the replacement engine and / or the change of the installation interface of the helicopter.

[0034] Optionally, the "analysis of the impact of the change in the installation interface of the replaced engine and / or the helicopter on the fire suppression system of the helicopter" includes: after the installation interface of the replaced engine and / or the helicopter is changed, analyzing the impact of the engine compartment cooling ventilation on the fire suppression system, focusing on whether the flow field inside the engine compartment meets the requirements for the diffusion rate and concentration distribution of the fire extinguishing agent; determining the high-risk fire area of ​​the engine compartment based on the factory documents of the replaced engine, and optimizing the placement of fire detectors based on the high-risk fire area and the internal structure of the compartment.

[0035] Furthermore, based on the compatibility analysis results of the installation interface between the replaced engine and the helicopter, the impact of the engine replacement and the change in the helicopter's installation interface on various parts of the helicopter is analyzed. For example... Figure 2As shown, the components here include the airframe structure, power system, fuel system, avionics system, electrical system, electromechanical management system, and fire suppression system.

[0036] (a) Analyze the impact of engine replacement and changes to the helicopter mounting interface on the helicopter airframe structure, including: the impact on the helicopter's main power transmission path and structural integrity, and the impact on the power compartment and power platform. If the helicopter airframe structure does not undergo significant changes after replacing the original engine, then it is not necessary to conduct static strength and fatigue life calculations for the entire airframe structure; otherwise, static strength and fatigue life analysis of the entire airframe structure is required. If the replacement engine interferes with the power compartment and power platform, adaptive adjustments to the local structure of the power compartment are required, but it is essential to ensure that the aerodynamic shape of the power compartment fairing, the internal structural components of the power compartment, the ventilation and cooling capacity of the power compartment, the fire suppression capacity, and the maintenance and inspection capabilities of the power compartment meet the requirements of the helicopter.

[0037] (b) Analyze the impact of the engine replacement and changes to the helicopter's mounting interface on the power system, including: comparing the differences between the replacement engine's center of gravity, mounting location, and connection method and the helicopter's original engine, making adaptive adjustments, and redesigning the engine mounting section if necessary. Furthermore, analyze whether the replacement engine's control method is consistent with the helicopter's original engine. If not, the engine control system needs to be redesigned; otherwise, no adjustments to the relevant systems are required. For example, if the replacement engine uses digital electronic control, consistent with the original engine, then no adjustments to the relevant systems are needed.

[0038] (c) Analyze the impact of engine replacement and helicopter mounting interface changes on the fuel system, including whether the fuel system meets the fuel inlet requirements of the replacement engine. Here, fuel inlet requirements include fuel supply line mechanical interface requirements, fuel flow requirements, fuel pressure requirements, fuel temperature requirements, and fuel purity requirements.

[0039] (d) Analyze the impact of engine replacement and helicopter mounting interface changes on the avionics system, including whether the engine's operating parameters and fault alarm indications are displayed correctly. If the communication protocol between the engine's CNC system and the helicopter changes, and the engine's operating parameter limits and fault codes change, then the helicopter's control display unit software, multifunction display software, and monitoring software need to be adaptively modified to ensure that the avionics system can correctly receive and display the engine's operating parameters and fault alarm information.

[0040] (e) Analyze the impact of engine replacement and helicopter installation interface changes on the electrical system, including: the auxiliary power unit (APU) associated with the engine replacement participates in the power supply of the helicopter power system, and it is necessary to carry out power capacity and electrical load calculations to analyze whether the power supply requirements of the helicopter power system are met.

[0041] (f) Analyze the impact of engine replacement and helicopter installation interface changes on the electromechanical management system, including the compatibility of interfaces between the electromechanical management system and other electromechanical systems, avionics systems and flight parameter recording systems.

[0042] (g) Analyze the impact of engine replacement and changes to helicopter mounting interfaces on the fire suppression system, including: analyzing the impact of engine compartment cooling and ventilation on the fire suppression system after engine replacement, and whether the airflow field within the engine compartment meets the requirements for extinguishing agent diffusion rate and concentration. Simultaneously, optimize the placement of fire detectors based on the locations prone to fires within the compartment and the internal structure. The locations prone to fires within the compartment can be determined through the engine's factory documentation.

[0043] Finally, based on the above analysis results, a general technical solution for replacing the helicopter engine was formulated. The general technical solution includes design analysis, theoretical calculation, simulation analysis, and engineering technical solutions. The replacement of the helicopter engine was then carried out in accordance with the general technical solution.

[0044] Those skilled in the art will understand that the accompanying drawings are merely schematic diagrams of a preferred embodiment, and the processes depicted in the drawings are not necessarily essential for implementing this application.

[0045] The serial numbers in this application are for descriptive purposes only and do not represent the superiority or inferiority of any particular implementation scenario. The above disclosures are merely a few specific implementation scenarios of this application; however, this application is not limited thereto, and any variations conceived by those skilled in the art should fall within the protection scope of this application.

Claims

1. A method for replacing a helicopter engine, characterized in that, include: S1. Determine and analyze the performance parameters and structural characteristics of the replacement engine; S2, determine and analyze the installation interface between the replacement engine and the helicopter; S3, When the installation interface between the replacement engine and the helicopter is not compatible, analyze the impact of the change in the installation interface of the replacement engine and / or the helicopter on the helicopter; S4. Based on the analysis results of S1~S3, the overall technical solution for replacing the helicopter engine is obtained, and the replacement work of the helicopter engine is carried out according to the overall technical solution. The effects on the helicopter include the effects on the helicopter's airframe structure; The analysis includes the impact of the engine replacement and / or changes to the helicopter's mounting interfaces on the helicopter's airframe structure, including: When the replacement engine and / or the installation interface of the helicopter are changed, analyze the impact of the replacement engine on the main force transmission path and structural integrity of the helicopter. The impact on the helicopter also includes the impact on the helicopter's fire suppression system; the analysis of the impact of the engine replacement and / or the change in the helicopter's mounting interface on the helicopter's fire suppression system includes: When the installation interface of the engine and / or the helicopter is changed, the impact of the engine compartment cooling ventilation on the fire extinguishing system is analyzed, with a focus on whether the flow field inside the engine compartment meets the requirements for the diffusion rate and concentration distribution of the fire extinguishing agent. Based on the factory documents of the replaced engine, the high-risk fire areas of the power compartment are identified, and the placement of fire detectors is optimized according to the high-risk fire areas and the internal structure of the compartment.

2. The method according to claim 1, characterized in that, The analysis priority of the performance parameters and structural features is determined based on the target requirements; the determination and analysis of the performance parameters of the replacement engine includes: Determine the power and fuel consumption rate of the engine under each major operating condition, and analyze whether the power and fuel consumption rate under each major operating condition meet the power requirements of the helicopter. Determine the lifespan of the replaced engine and analyze whether the lifespan matches the overhaul interval of the helicopter; The process of determining and analyzing the structural characteristics of the replacement engine includes: The structural form, intake and exhaust method, weight, and external dimensions of the replacement engine are determined, and it is analyzed whether the structural features meet the installation requirements of the helicopter.

3. The method according to claim 1, characterized in that, The installation interface includes a mechanical installation interface and a system installation interface. The mechanical installation interface includes at least one of the following: engine body mounting section, connection interface between engine air intake and helicopter air intake, engine exhaust pipe interface, engine power output shaft and main reducer interface, and engine control system installation interface. The system installation interface includes at least one of the following: engine fuel system interface, lubricating oil system interface, anti-icing bleed air system interface, starting electrical system interface, and CNC system electrical interface.

4. The method according to claim 1, characterized in that, S3 includes: When the installation interface between the replacement engine and the helicopter is incompatible, analyze the impact of the replacement engine and / or the change in the installation interface of the helicopter on the airframe structure and various systems of the helicopter, including at least the power system, fuel system, avionics system, electrical system, electromechanical management system and fire suppression system.

5. The method according to claim 4, characterized in that, The analysis of the impact of the engine replacement and / or the change of the helicopter's mounting interface on the helicopter's airframe structure also includes: When the helicopter airframe structure undergoes significant changes, analyze the static strength and fatigue life of the entire helicopter structure. The impact of the engine replacement on the helicopter's power compartment and power platform was analyzed. The analysis examines whether there is any interference between the replaced engine and the helicopter's power compartment. If interference exists, adaptive adjustments are made to the local structure of the helicopter's power compartment. The adjusted power compartment's aerodynamic shape of the fairing, internal structural components, ventilation and cooling capacity, fire suppression capability, and internal maintenance and inspection capabilities meet the helicopter's preset power compartment requirements.

6. The method according to claim 4, characterized in that, The analysis of the impact of the engine replacement and / or the change in the helicopter's mounting interface on the helicopter's power system includes: When the replacement engine and / or the installation interface of the helicopter are changed, analyze the impact of the replacement engine on the engine installation system, engine intake and exhaust system and engine control system; Compare the differences between the replacement engine's center of gravity, installation position, and connection method and the original engine of the helicopter, and make adaptive adjustments. The control method of the replaced engine is compared with that of the original engine of the helicopter, and the engine control system is redesigned when the control method changes.

7. The method according to claim 4, characterized in that, The analysis of the impact of the engine replacement and / or the change in the helicopter's mounting interface on the helicopter's fuel system includes: After analyzing the changes to the installation interface of the replaced engine and / or the helicopter, it is determined whether the fuel system meets the fuel inlet requirements of the replaced engine. The fuel inlet requirements include the mechanical interface requirements of the fuel supply line, fuel flow rate requirements, fuel pressure requirements, fuel temperature requirements, and fuel purity requirements.

8. The method according to claim 4, characterized in that, The analysis of the impact of the engine replacement and / or the change in the helicopter's mounting interface on the helicopter's avionics system includes: After analyzing the changes to the installation interface of the replaced engine and / or the helicopter, determine whether the display status of the operating parameters of the replaced engine and the fault alarm indication status are normal, and if abnormal, make adaptive changes to the control display unit software, multi-function display software and monitoring software.

9. The method according to claim 4, characterized in that, The analysis of the impact of the engine replacement and / or the change in the helicopter's mounting interface on the helicopter's electrical system includes: After the replacement engine and / or the installation interface of the helicopter are changed, when the engine starter generator or the matching auxiliary power unit participates in the power supply of the helicopter's power system, the power capacity and electrical load are calculated, and the calculation results are analyzed to see if they meet the power system requirements of the helicopter.

10. The method according to claim 4, characterized in that, The analysis of the impact of the engine replacement and / or the change in the helicopter's mounting interface on the helicopter's electromechanical management system includes: The analysis examines the interface compatibility between the electromechanical management system and other electromechanical systems, avionics systems, and flight parameter recording systems of the helicopter after the engine replacement and / or changes to the helicopter's installation interface.

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