Aero-engine assembly

Abstract

The invention relates to an aero-engine assembly which comprises a starting motor, a gear box, an air inlet cover and a turbine engine, the starting motor, the gear box, the air inlet cover and the turbine engine are sequentially arranged from front to back, the gear box is provided with an output shaft, the output shaft penetrates through the air inlet cover, and the turbine engine is arranged on the gear box. The turbine generator is connected to the turbine engine; a plurality of air suction ports are formed in a connecting interface of the starting motor and the gear box; the end, away from the multiple air suction ports, of the starting motor is connected with an air flow pipeline, and the air flow pipeline communicates with the air inlet cover. According to the aero-engine assembly, only the airflow pipeline extending from the starting motor to the air inlet cover needs to be configured, other pipeline layout or parts do not need to be configured, and therefore the structure of the aero-engine assembly is simplified, and the design cost, the manufacturing cost and even the maintenance cost of an aircraft are saved.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft engines and gas turbines, and in particular to an aircraft engine assembly. Background Art

[0002] In the scope of modern aircraft engine systems, the cooling of the starter motor is achieved by cooling gas provided by the aircraft. The specific arrangement is to open a cooling duct in the aircraft, and during the high-speed flight of the aircraft, introduce low-temperature gas from the high-altitude atmosphere or the aircraft intake fan, and enter the starter motor through the cooling duct, thereby dissipating heat for the coil of the starter motor. However, in order to apply such a cooling solution, it is necessary to add additional airflow ducts to the aircraft casing, or to configure corresponding airflow ducts near the intake fan of the aircraft engine. No matter which configuration scheme is adopted, it will inevitably increase the complexity and total weight of the aircraft structure, thereby leading to an increase in the maintenance cost of the aircraft.

[0003] Some other aircraft engine manufacturers adopt such a cooling solution, that is, a cooling duct is opened in the aircraft, and a fan is arranged at the tail end of the starter motor. When the starter motor is running, the fan rotates together, so that low-temperature gas enters the starter motor through the cooling duct, thereby dissipating heat for the coil of the starter motor. However, similarly, such a solution inevitably increases the complexity and total weight of the aircraft structure, thereby increasing the maintenance cost of the aircraft.

[0004] Russian invention patent RU2358120C1 discloses a turbopropeller gas turbine engine, wherein the winding of the electric generator is enclosed in the electric generator sleeve, connected with its air cooling system, and the electronic controller is installed on the power cable; the air cooling system includes a valve and an air exhaust duct. It can be seen that in this scheme, it is necessary to configure a relatively complex air cooling system specifically for the electric generator. In addition, US invention patent US2827760A discloses a combined anti-icing and generator cooling device for a gas turbine engine, wherein a bullet-shaped fairing (44) includes an inner wall (45) and an outer wall (46), between which a plurality of circumferentially spaced baffles (47) are respectively installed; at the front end of the fairing there is an opening (48) for allowing cooling air to enter the generator (42). It should be noted that, although in this solution, it is not necessary to configure a special air cooling system for the generator (42), such as valves and airflow ducts and other components, this solution is obviously only applicable to the structure in which the generator (42) is arranged in the front section of the bullet-shaped fairing (44), and therefore lacks universality. Summary of the invention

[0005] In order to overcome at least one of the defects described in the above-mentioned prior art, the purpose of the present application is to provide an aircraft engine assembly, including a starter motor, a gear box, an air intake cover and a turbine engine, wherein the starter motor, the gear box, the air intake cover and the turbine engine are arranged in sequence from front to back, wherein the gear box has an output shaft, and the output shaft passes through the air intake cover so as to be connected to the turbine engine; a plurality of air intake ports are provided at the connection interface between the starter motor and the gear box; an end of the starter motor away from the plurality of air intake ports is connected to an airflow pipeline, and the airflow pipeline is connected to the air intake cover.

[0006] In one embodiment, the aircraft engine assembly further comprises an air compressor, which is arranged in the air intake cowling and is configured to supply compressed air to the turbine engine.

[0007] In another embodiment, the air intake hood includes a filter screen covering the air intake hood, or the air intake hood is a filter screen.

[0008] In yet another embodiment, the starter motor can be reversed to act as a generator when the turbine engine is in normal operation.

[0009] In yet another embodiment, the gearbox is filled with lubricating oil.

[0010] In yet another embodiment, the connection between the starter motor and the air flow pipeline is in the form of a clamp connection.

[0011] In yet another embodiment, the connection between the air intake hood and the airflow pipeline is in the form of a clamp connection.

[0012] In yet another embodiment, the plurality of air intakes between the starter motor and the gear box are provided with filtering devices.

[0013] In yet another embodiment, the air flow conduit is a hose.

[0014] The aircraft engine assembly of the present application only needs to be configured with an airflow pipeline extending from one end of the starter motor to the air intake cover, and does not need to be configured with a relatively complex pipeline layout or corresponding valves and other components, thereby simplifying the structure of the aircraft engine assembly, which in turn saves the cost of designing, manufacturing and even maintaining the aircraft; at the same time, omitting the relatively complex pipeline layout or the existence of corresponding valves and other components will reduce the total weight of the aircraft engine assembly, which means that the aviation cost of the aircraft can also be effectively saved, or alternatively, the aviation capacity optimized by lightweight design can be invested in people / cargo, that is, the aircraft capacity is optimized. In addition, the space saved in this way can be further used to optimize the aerodynamic surface design of the aircraft or to accommodate other equipment / components of the aircraft, providing a basis for the functional optimization of other aspects of the aircraft. Moreover, the aircraft engine assembly of the present application is not only suitable for the scene where the generator / motor is arranged just in the front section of the engine fairing, but, relatively speaking, even if the generator / motor is arranged in other parts of the engine fairing, the configuration structure of the present application is also applicable. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0016] Figure 1 A perspective view of an aircraft engine assembly according to an embodiment of the present application is shown.

[0017] List of reference numerals:

[0018] 1-aircraft engine assembly; 2-starter motor; 3-gear box; 4-air intake cover; 5-turbine engine; 6-air flow pipeline; 7-filter device; 8-first clamp; 9-second clamp. DETAILED DESCRIPTION

[0019] In order to make the purpose, technical solutions and advantages of this application clearer, the technical solutions in the embodiments of this application will be clearly and completely described below in conjunction with the drawings in the embodiments of this application. Obviously, the described embodiments are only part of the embodiments of this application, not all of them. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0020] In the description of the present application, it should be understood that the terms "X-axis", "Y-axis", "Z-axis", "vertical", "parallel", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, which are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present application. In addition, the terms "first" and "second" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present application, unless otherwise specified, "multiple" means two or more.

[0021] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0022] like Figure 1 , which shows a perspective view of an aircraft engine assembly 1 according to an embodiment of the present application. The aircraft engine assembly 1 includes a starter motor 2, a gearbox 3, an air intake hood 4 and a turbine engine 5. As in a conventional aircraft engine assembly, the air intake hood 4 is always arranged in front of the turbine engine 5; in this embodiment, the starter motor 2, the gearbox 3, the air intake hood 4 and the turbine engine 5 are arranged in sequence from front to back; however, in other embodiments, the starter motor 2, the gearbox 3, the air intake hood 4 and the turbine engine 5 do not have to be arranged in sequence, for example, the starter motor 2 and the gearbox 3 can be arranged beside the outer peripheral edge of the air intake hood 4 or the air compressor along its radial direction, and the input / output shaft direction of the starter motor 2 and the gearbox 3 can be parallel or orthogonal to the length direction of the turbine engine 5.

[0023] In this embodiment, the starter motor 2, the gearbox 3, the air intake cover 4 and the turbine engine 5 are closely connected to each other in pairs according to the above order, wherein the connection interface between the starter motor 2 and the gearbox 3 is provided with a plurality of air intake ports (not shown); the gearbox 3 has an output shaft (not shown), which passes through the air intake cover 4 so as to be connected to the turbine engine 5. An airflow pipeline 6 is connected to the end of the starter motor 2 away from the plurality of air intake ports, and the airflow pipeline 6 is connected to the air intake cover 4.

[0024] In other embodiments, the starter motor 2 and the gear box 3 do not need to be closely connected to each other. Instead, it is only necessary to ensure that the output shaft of the starter motor 2 is connected to the input end of the gear box 3. On the other hand, the output shaft of the gear box 3 is directly connected to the turbine engine 5. A plurality of air intake ports (not shown) are provided at either end of the starter motor 2, and an airflow pipeline 6 is connected to the other end thereof, and the airflow pipeline is connected to the air intake cover 4.

[0025] Regardless of whether the starter motor 2 and the gear box 3 are arranged close to each other, or whether the starter motor 2, the gear box 3, the air intake cover 4 and the turbine engine 5 are arranged in sequence from front to back, as long as the output shaft of the starter motor 2 is connected to the input end of the gear box 3, and as long as the end of the starter motor 2 away from the air intake ports is connected to the air flow duct 6 leading to the air intake cover 4, it can be ensured that the aircraft engine assembly 1 has an air cooling system with a simple layout and relatively few components.

[0026] Preferably, the aircraft engine assembly 1 further comprises an air compressor (not shown), which is arranged in the air intake hood 4, and the configuration is to supply compressed air to the turbine engine 5. More preferably, the aircraft engine assembly 1 may include a multi-stage air compressor, wherein the first-stage air compressor is arranged in the air intake hood 4, and the air compressors of the subsequent stages are arranged in sequence in front of the turbine engine 5. During the normal operation of the aircraft engine assembly 1, the negative pressure generated by the air compressor serves as the source of suction force for the low-temperature gas near the air intake hood 4, including the gas in the air flow duct 6 connected to the air intake hood 4, whereby the negative pressure acts on the gas near the air flow duct 6, the starter motor 2 and even several air intake ports in sequence. This means that the air compressor not only supplies compressed air to the turbine engine 5 as conventional means, but also acts as a fan in the prior art to provide power / negative pressure for the air cooling system of the starter motor 2.

[0027] In such a configuration, considering that the low-temperature air flowing through the starter motor 2 to provide air cooling for it is then sucked into the air compressor in the air intake hood 4 and finally sucked into the turbine engine 5 to participate in combustion, it is necessary to ensure that the sucked air is free of large-sized particles. It is conceivable that in the case where the air intake hood 4 is a grid-like frame with a large grid size, the surface of the air intake hood 4 can be covered with several layers of filter screens, and the filter size and air permeability of the filter screen can be selected according to the air intake rate of the air compressor and the turbine engine 5. Or, alternatively, the air intake hood 4 itself is composed of several layers of filter screens. On the other hand, similarly, considering that the low-temperature air flows through the starter motor 2, in order for the starter motor 2 to be able to operate for a long time, a filter device 7, such as the aforementioned several layers of filter screens, is provided at several air intake ports, thereby preventing particles in the atmosphere from adhering to its components, such as the stator, rotor and winding, during the flow through the starter motor 2.

[0028] In a preferred embodiment, the starter motor 2 is capable of reverse operation, that is, when the aircraft engine assembly 1 is started, the starter motor 2 functions as a motor to activate the operation of the turbine engine 5; when the aircraft engine assembly 1 is operating normally, the starter motor 2 acts as a generator, and the turbine engine 5 drives the rotor of the starter motor 2 to rotate to generate electrical energy, and the generated electrical energy is consumed by other electrical appliances of the aircraft.

[0029] The airflow duct 6 can be in the form of a hose or a rigid duct, which can be selected according to the working environment of the aircraft engine assembly 1. One end of the airflow duct 6 is fluidly connected to the starter motor 2, and the other end is fluidly connected to the air intake hood 4. The connection can be in the form of a clamp connection, wherein the first clamp 8 and the second clamp 9 clamp the corresponding ends of the airflow duct 6 on the corresponding openings of the starter motor 2 and the air intake hood 4, respectively. Or, alternatively, flanges (not shown) are provided at both ends of the airflow duct 6, and flanges (not shown) of complementary shapes are provided on the corresponding openings of the starter motor 2 and the air intake hood 4, thereby achieving fluid connection between the airflow duct 6 and the starter motor 2 and the air intake hood 4. Of course, other connection means are also available, as long as the air tightness of the airflow duct 6 and its connecting parts is ensured.

[0030] The gearbox 3 is used as a transmission between the starter motor 2 and the turbine engine 5, wherein a plurality of mutually meshing gears with different gear ratios are arranged. In order to ensure that the gearbox 3 can run smoothly, a certain amount of lubricating oil can be injected into the gearbox 3.

[0031] When the aircraft engine assembly 1 is started, the starter motor 2 is started first to drive the air compressor in the air intake cover 4 and the turbine engine 5 to operate through the gear box 3. The running air compressor generates negative pressure, and sucks the low-temperature gas in the atmosphere through the airflow pipeline 6, the starter motor 2 and several air intake ports. When the aircraft engine assembly 1 is in a stable operation stage, the starter motor 2 acts as a generator, and it has been running for a period of time and has generated heat. At this time, the low-temperature gas flowing through the starter motor 2 just provides air cooling for it. The air cooling system configured for the starter motor 2 in this way eliminates components such as valves and relatively complex cooling pipe design layouts, saves space and cost of the aircraft, and is universal for the structural construction of various engine assemblies.

[0032] It should be understood that what is described in the above drawings and specific embodiments are merely exemplary embodiments of the present application, and are not exhaustive of the possible implementation methods of the present application. Those skilled in the art may make various changes to the above specific implementation methods within the scope of protection of the present application without departing from the main purpose of the present application.

Claims

1. An aircraft engine assembly, comprising a starter motor, a gear box, an air intake cover and a turbine engine, wherein the starter motor, the gear box, the air intake cover and the turbine engine are arranged in sequence from front to back. It is characterized in that The gearbox has an output shaft, the output shaft passing through the air inlet cowl so as to be connected to the turbine engine; The connection interface between the starter motor and the gear box is provided with a plurality of air intake ports; One end of the starter motor away from the plurality of air intake ports is connected with an air flow pipeline, and the air flow pipeline is connected to the air intake hood.

2. The aircraft engine assembly according to claim 1, It is characterized in that Also included is an air compressor disposed within the air inlet cowl and configured to supply compressed air to the turbine engine.

3. The aircraft engine assembly according to claim 1, It is characterized in that The air intake hood includes a filter screen covering the air intake hood, or the air intake hood is a filter screen.

4. The aircraft engine assembly according to claim 1, It is characterized in that The starter motor can be operated in reverse to act as a generator when the turbine engine is in normal operation.

5. The aircraft engine assembly according to claim 1, It is characterized in that The gearbox is filled with lubricating oil.

6. The aircraft engine assembly according to claim 1, It is characterized in that The connection between the starter motor and the airflow pipeline is in the form of a clamp connection.

7. The aircraft engine assembly according to claim 1, It is characterized in that The connection between the air intake hood and the air flow pipeline is in the form of a clamp connection.

8. The aircraft engine assembly according to claim 1, It is characterized in that The plurality of air intakes between the starter motor and the gear box are provided with filtering devices.

9. The aircraft engine assembly according to claim 1, It is characterized in that The air flow pipeline is a hose.

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