A multi-electric aeroengine accessory layout

Abstract

This invention provides a multi-electric aero-engine accessory layout structure, belonging to the field of aero-engine technology. It includes: at least one electric fuel pump, an electric oil pump, an electric pump controller, at least one radiator, an adjustable variable actuator, and an electronic controller. The electric pump controller connects the electric fuel pump and the electric oil pump via a high-voltage cable, and is used to send fuel supply control command signals to the electric fuel pump and the electric oil pump. The electric fuel pump is connected to the radiator via a thick pipe. The electronic controller is connected to the adjustable variable actuator via a low-voltage cable, and is used to drive the stable operation of the adjustment mechanism and change the physical position of the adjustable variable. The accessory housing is divided into a high-voltage area and a low-voltage area. The multi-electric aero-engine-specific accessories, including the electric fuel pump, electric oil pump, and electric pump controller, are located in the high-voltage area, while the conventional multi-electric aero-engine accessories, including the radiator, adjustable variable actuator, and electronic controller, are located in the low-voltage area.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine technology, and specifically relates to an accessory layout structure for a multi-electric aero-engine. Background Technology

[0002] Traditional aero engines drive various fuel pumps, oil pumps, and other accessories through engine accessory housings. The layout of these accessories revolves around the front and rear areas of the engine accessory housing. The main control unit—the electronic controller—drives the corresponding accessories, including various adjustable variable actuators, through low-voltage cables. The cable connection scheme has a high degree of freedom and does not need to be considered separately in the early stages of the design. The main limiting factor for the accessory layout is the connection scheme of the thick pipes.

[0003] Each type of electric pump in an aero-engine requires a separate motor controller, and the two are connected by a high-voltage cable, which is prone to electromagnetic interference with the engine's conventional cables (low-voltage cables). If the engine is equipped with multiple types of electric pumps, multiple electric pumps and their motor controllers need to be arranged, occupying a significant amount of engine installation space. Therefore, the arrangement of electric pumps and their motor controllers seriously affects the external layout of multi-electric aero-engines. Traditional solutions do not plan a separate high-voltage area for them, resulting in high-voltage and low-voltage cables intertwined. Furthermore, the supply and return oil pipelines for cooling oil to the electric pumps in the aero-engine are complex and long, resulting in low thermal management efficiency at the accessory level, significant oil loss along the pipeline, and numerous and long pipelines, which is detrimental to engine weight control. Summary of the Invention

[0004] The purpose of this invention is to provide a multi-electric aero-engine accessory layout structure to solve or mitigate at least one of the problems in the prior art.

[0005] The technical solution of the present invention is: a multi-electric aero-engine accessory layout structure, including: at least one electric fuel pump, an electric oil pump, an electric pump controller, at least one radiator, an adjustable variable actuator, and an electronic controller. The electric pump controller is connected to the electric fuel pump and the electric oil pump via a high-voltage cable and is used to send fuel supply control command signals to the electric fuel pump and the electric oil pump. The electric fuel pump is connected to the radiator via a thick pipe. The electronic controller is connected to the adjustable variable actuator via a low-voltage cable and is used to drive the stable operation of the adjustment mechanism and change the physical position of the adjustable variable.

[0006] The accessory housing of the aero-engine is divided into a high-voltage area and a low-voltage area. Multi-electric aero-engine-specific accessories, including electric fuel pumps, electric oil pumps and electric pump controllers, are located in the high-voltage area, while multi-electric conventional accessories, including radiators, adjustable variable actuators and electronic controllers, are located in the low-voltage area.

[0007] In one embodiment of the present invention, different types of aircraft engines have different accessory types and quantities.

[0008] In one embodiment of the present invention, the electric pump controller is an inherited controller, which can simultaneously control the electric fuel pump and the electric lubricating oil pump.

[0009] In one embodiment of the present invention, the limiting factor for the accessory layout of the multi-electric aero-engine is the connection scheme of the thick pipeline and the connection scheme of the high-voltage cable.

[0010] Compared with existing technologies, the multi-electric aero-engine accessory layout structure of the present invention has the following advantages:

[0011] 1) The layout of the accessories is divided into high-voltage and low-voltage areas, and the high-voltage and low-voltage cables are physically isolated to avoid electromagnetic interference;

[0012] 2) The controllers of various types of electric pumps are integrated into one type of accessory, including the electric fuel pump of the control system and the electric lubricating oil pump of the mechanical system. This breaks the traditional concept of system and realizes a high degree of integration of accessories, that is, one type of controller can control multiple electric pumps at the same time.

[0013] 3) The main limiting factor for the layout of accessories was changed from the large-diameter pipeline connection scheme to the large-diameter pipeline and high-voltage cable connection scheme.

[0014] 4) All types of electric pumps and controllers require fuel cooling. Centralizing their arrangement facilitates the supply and return of cooling oil pipelines for various accessories, improves the thermal management efficiency of accessories, and reduces the loss of cooling oil along the pipeline. Attached Figure Description

[0015] To more clearly illustrate the technical solution provided by the present invention, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of the present invention.

[0016] Figure 1 This is a schematic diagram of the accessory layout structure of the multi-electric aero-engine of the present invention. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions in the embodiments of this invention will be described in more detail below with reference to the accompanying drawings.

[0018] This invention proposes a multi-electric aero-engine accessory layout structure, which includes at least one electric fuel pump, an electric oil pump, an electric pump controller, at least one radiator, an adjustable variable actuator, and an electronic controller. The electric fuel pump, electric oil pump, and electric pump controller constitute unique accessories for the multi-electric aero-engine, while the radiator, adjustable variable actuator, and electronic controller constitute conventional accessories. The engine accessory housing is divided into a high-voltage area and a low-voltage area. The unique accessories for the multi-electric aero-engine are located in the high-voltage area, and the conventional accessories are located in the low-voltage area, thereby physically isolating the unique accessories from the conventional accessories. Figure 1 The dotted line is the physical isolation boundary, which facilitates the physical isolation of high-voltage cables and low-voltage cables.

[0019] In this invention, the types and quantities of accessories for different types of aero engines vary. For example, in this invention... Figure 1 In this embodiment, the accessory layout structure comprises three electric fuel pumps, one electric lubricating oil pump, one electric pump controller, two radiators, an adjustable variable actuator, and an electronic controller. The three electric fuel pumps are of different types (e.g., an electric main fuel pump, an electric afterburner fuel pump, etc.), and the two radiators are of different types. It should be noted that the accessories listed in this invention are commonly used accessories for multi-electric aircraft engines. The types and quantities of accessories listed are for illustrative purposes only. The accessories described only relate to the accessory layout behind the accessory housing of the multi-electric aircraft engine (the core area of ​​the accessory layout). Accessories in other areas are still multi-electric aircraft engine accessories, but are not described in this invention.

[0020] In the unique accessory for multi-electric aircraft engines of the present invention, the connection between the electric pump controller and the electric lubricating oil pump and the three types of electric fuel pump is made of high-voltage cable. Figure 1 (As indicated by the thick black arrow), while the conventional components of multi-electric aircraft engines are connected by low-voltage cables. Figure 1 (As indicated by the thin black arrow). Figure 1 The solid black arrows in the middle show the fuel supply command signals sent by the electric pump controller to various types of electric fuel pumps and electric lubricating oil pumps, including fuel supply timing, fuel supply quantity, fuel supply rate, etc. Figure 1 The black dashed arrow in the middle indicates the adjustment signal sent by the electronic controller to the adjustable variable actuator, which drives the stable operation of the adjustment mechanism and changes the physical position of the adjustable variable (e.g., the opening and closing angle of the adjustable guide vane). Physical isolation between high-voltage and low-voltage cables avoids electromagnetic interference and reduces the impact on the transmission of various electrical signals. It should be noted that... Figure 1Only the driving electrical signals indicated by the arrows are listed. The actual physical process also includes various feedback electrical signals, etc., which will not be described in detail here.

[0021] Existing electric pumps (including electric fuel pumps and electric lubricating oil pumps) are bound one-to-one with their controllers. The electric pump controller in this invention can be bound to multiple types of electric pumps simultaneously, sending drive signals to multiple types of electric pumps and receiving corresponding feedback signals. This enables high integration of the components, saves physical space, and improves the space utilization of the pump installation.

[0022] Figure 1 The controllers for various types of electric pumps are integrated into a single accessory, including the electric main fuel pump and electric afterburner fuel pump of the control system, and the electric lubricating oil pump of the mechanical system. This breaks the traditional system concept and achieves a high degree of integration of accessories. Otherwise, equipping three types of electric pumps with three types of electric pump controllers would greatly increase the engine weight and occupy unnecessary accessory installation space. Installing three types of electric pump controllers on the engine casing simultaneously would pose a huge challenge to the space required for engine installation on the aircraft, making it difficult to control the installation clearance between the aircraft and the engine, and also reducing the maintainability of the accessory in the installed state.

[0023] Traditionally, the main limiting factor in the layout of accessory components is the connection scheme of the thick piping, which determines the installation position, interface orientation, and corresponding accessory adjustment measures for each type of accessory. However, multi-electric aero-engines need to consider the connection scheme of high-voltage cables, and the main limiting factor in the accessory layout of multi-electric aero-engines is the thick piping (… Figure 1 Medium-thick solid line) and high-voltage cable connection scheme ( Figure 1 (Solid black arrowhead)

[0024] Figure 1 The thick pipes listed are only a small part of the thick pipes, and are only for illustrative purposes. Under normal circumstances, a type of aircraft engine can have about 50 thick pipes (pipe outer diameter Φ20mm).

[0025] All types of electric pumps and controllers require fuel cooling. Unifying their placement in the high-voltage area facilitates the supply and return oil piping layout for various accessories, improving thermal management efficiency at the accessory level and reducing cooling oil loss along the pipeline. Compared to the long supply and return oil piping caused by the dispersed arrangement of accessories in multi-electric aircraft engines, this approach reduces pipe connection length and lowers the actual engine weight.

[0026] Compared with existing technologies, the multi-electric aero-engine accessory layout structure of the present invention has the following advantages:

[0027] 1) The layout of the accessories is divided into high-voltage and low-voltage areas, and the high-voltage and low-voltage cables are physically isolated to avoid electromagnetic interference;

[0028] 2) The controllers of various types of electric pumps are integrated into one type of accessory, including the electric fuel pump of the control system and the electric lubricating oil pump of the mechanical system. This breaks the traditional concept of system and realizes a high degree of integration of accessories, that is, one type of controller can control multiple electric pumps at the same time.

[0029] 3) The main limiting factor for the layout of accessories was changed from the large-diameter pipeline connection scheme to the large-diameter pipeline and high-voltage cable connection scheme.

[0030] 4) All types of electric pumps and controllers require fuel cooling. Centralizing their arrangement facilitates the supply and return of cooling oil pipelines for various accessories, improves the thermal management efficiency of accessories, and reduces the loss of cooling oil along the pipeline.

[0031] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A multi-electric aero-engine accessory layout structure, characterized in that, include: The system includes at least one electric fuel pump, an electric oil pump, an electric pump controller, at least one radiator, an adjustable variable actuator, and an electronic controller. The electric pump controller is connected to the electric fuel pump and the electric oil pump via a high-voltage cable and is used to send fuel supply control command signals to the electric fuel pump and the electric oil pump. The electric fuel pump is connected to the radiator via a thick pipe. The electronic controller is connected to the adjustable variable actuator via a low-voltage cable and is used to drive the stable operation of the adjustment mechanism and change the physical position of the adjustable variable. The accessory housing of the aero-engine is divided into a high-voltage area and a low-voltage area. Multi-electric aero-engine-specific accessories, including electric fuel pumps, electric oil pumps and electric pump controllers, are located in the high-voltage area, while multi-electric conventional accessories, including radiators, adjustable variable actuators and electronic controllers, are located in the low-voltage area.

2. The multi-electric aero-engine accessory layout structure as described in claim 1, characterized in that, Different types of aircraft engines have different accessory types and quantities.

3. The multi-electric aero-engine accessory layout structure as described in claim 1, characterized in that, The electric pump controller is an inherited controller, capable of simultaneously controlling the electric fuel pump and the electric lubricating oil pump.

4. The multi-electric aero-engine accessory layout structure as described in claim 1, characterized in that, The limiting factors for the accessory layout of the multi-electric aero-engine are the thick pipeline connection scheme and the high-voltage cable connection scheme.

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