Electric turbofan engine, aircraft and control method

Abstract

The invention relates to the technical field of aviation, particularly provides an electric turbofan engine, an aircraft and a control method, and aims to solve the problem that the electric energy cannot be matched with the electric energy required by the engine in the prior art, which is one of the important problems to be solved urgently in the field. The electric turbofan engine is applied to the aircraft and comprises a supercharging assembly, a shell, a first flow channel, a second flow channel, a flow channel switching mechanism, a plurality of turbine generators and a plurality of flow guide pipes, the supercharging assembly is arranged in the shell and located in the first flow channel, the second flow channel is formed between the outer side wall of the supercharging assembly and the inner side wall of the shell, and the flow channel switching mechanism is arranged between the first flow channel and the second flow channel. Each flow guide pipe is annularly arranged on the outer side wall of the shell, each flow guide pipe is communicated with the second flow channel, the flow channel switching mechanism is arranged at an inlet of each flow guide pipe, and each turbine generator is arranged at an outlet of each flow guide pipe. The electric turbofan engine, the aircraft and the control method are used for increasing the power of the electric turbofan engine.

Description

Technical Field

[0001] The present disclosure relates to the field of aviation technology, and in particular to an electric turbofan engine, an aircraft, and a control method. Background Art

[0002] The combination of laser weapons and intelligent electrified drones is an inevitable trend for future combat platforms. The realization of their comprehensive combat effectiveness is inseparable from efficient and high-performance propulsion systems. At the same time, it is accompanied by a large power extraction from the power propulsion system. Based on the existing mature turbofan engines, the development of high-power extraction multi-electric engines that replace conventional mechanical systems is the most feasible technical approach.

[0003] As a key technology for improving the performance of next-generation aircraft and engines, multi-electric technology has attracted keen attention from countries around the world. Among them, some countries have carried out verification of the dual-axis power extraction scheme of embedded starter generators, and the output power has reached the megawatt level. With the development of multi-electric technology, the output power of multi-electric technology cannot meet the huge demand for new sensors and directed energy weapons on future fighters. Therefore, some countries have carried out research and verification on the integration of embedded generators and engine components / systems through the Power Optimized Aircraft (POA) technology verification program. However, the demand for electricity of advanced airborne systems and weapon systems has reached more than megawatts.

[0004] Therefore, how to solve the problem that the existing technology cannot match the electrical energy required by the engine is one of the important issues that need to be solved urgently in this field. Summary of the invention

[0005] In view of this, the embodiments of the present disclosure provide an electric turbofan engine, an aircraft and a control method to solve the problem in the prior art that the electric energy required by the engine cannot be matched.

[0006] According to one aspect of the present disclosure, an electric turbofan engine is provided, which is applied to an aircraft. The electric turbofan engine comprises: a supercharging assembly, a casing, a first flow channel, a second flow channel, a flow channel switching mechanism, a plurality of turbine generators and a plurality of flow guide pipes. The supercharging assembly is arranged in the casing, the supercharging assembly is located in the first flow channel, a second flow channel is formed between an outer side wall of the supercharging assembly and an inner side wall of the casing, each flow guide pipe is annularly arranged on the outer side wall of the casing, each flow guide pipe is communicated with the second flow channel, the flow channel switching mechanism is arranged at the inlet of each flow guide pipe, and each turbine generator is arranged at the outlet of each flow guide pipe;

[0007] When the aircraft is in the first state, the flow channel switching mechanism is used to close the inlet of each flow guide pipe;

[0008] When the aircraft is in the second state, the flow channel switching mechanism is used to open the inlet of each flow guide tube.

[0009] In addition, according to an electric turbofan engine of one aspect of the present disclosure, the boost assembly includes: a fan, a compressor, a combustion chamber and a turbine, the fan is fixedly connected to one end of the compressor, the other end of the compressor is connected to the combustion chamber, the combustion chamber is connected to the turbine, and each guide duct is arranged near the compressor.

[0010] According to an electric turbofan engine of one aspect of the present disclosure, the flow channel switching mechanism includes a first baffle and a second baffle, the first baffle having a first hinged side and a first extended side opposite to the first hinged side, the second baffle having a second hinged side and a second extended side opposite to the second hinged side, the thickness of the first hinged side being greater than the thickness of the first extended side;

[0011] The first hinged side is hinged on the outer side wall of the compressor, the second hinged side is hinged on the inlet of each guide tube, and the thickness of the second hinged side is greater than the thickness of the second extended side.

[0012] According to an electric turbofan engine of one aspect of the present disclosure, the thickness of the first baffle decreases along the distribution direction from the first hinged side to the first extended side, and the thickness of the second baffle decreases along the distribution direction from the second hinged side to the second extended side.

[0013] According to an electric turbofan engine of one aspect of the present disclosure, the first baffle and the second baffle are both wedge-shaped baffles, the wedge-shaped tip of the first baffle is the extended end of the first baffle, and the wedge-shaped tip of the second baffle is the extended end of the second baffle; and / or,

[0014] The flow channel switching mechanism also includes a connecting rod, which is hinged on the same side of the first baffle plate and the second baffle plate, and the connecting rod is arranged on the outer side wall of the compressor.

[0015] In an electric turbofan engine according to one aspect of the present disclosure, the guide surface of the first baffle and the guide surface of the second baffle are planes or curved surfaces.

[0016] In an electric turbofan engine according to one aspect of the present disclosure, a fan, a compressor, a combustion chamber, and a turbine rotate coaxially.

[0017] According to another aspect of the present disclosure, an aircraft is provided, comprising the above-mentioned electric turbofan engine.

[0018] According to another aspect of the present disclosure, a flight mode control method is provided. For the above-mentioned aircraft, the method comprises:

[0019] In response to the first state flight instruction, controlling the electric turbofan engine to operate;

[0020] The flow channel switching mechanism is controlled to close the inlet of each guide pipe, and the first state flight instruction is used to indicate that each turbine generator is in a non-operating state;

[0021] In response to the second state flight instruction, controlling the electric turbofan engine to operate;

[0022] The flow channel switching mechanism is controlled to open the inlet of each guide pipe, and the first state flight instruction is used to indicate that each turbine generator is in a working state.

[0023] According to an aspect of the present disclosure, the flight mode control method further includes:

[0024] Determine the target physical parameters of the electric turbofan engine when the electric turbofan engine is operating normally;

[0025] Determine the actual physical parameters of the turbine generator based on the normal operation of the electric turbofan engine;

[0026] The geometric parameters of the turbine generator are determined based on the target physical parameters and the actual physical parameters.

[0027] At least one of the above-mentioned technical solutions adopted in the embodiments of the present disclosure can achieve the following beneficial effects: an electric turbofan engine is applied to an aircraft, a boost component is arranged in a shell, the boost component is located in a first flow channel, a second flow channel is formed between the outer wall of the boost component and the inner wall of the shell, each guide pipe is arranged on the outer wall of the shell, each guide pipe is connected to the second flow channel, a flow channel switching mechanism is arranged at the inlet of each guide pipe, and each turbine generator is arranged at the outlet of each guide pipe. When air flows into the boost component, a part of the fluid flows into the first flow channel, and another part of the fluid flows into the second flow channel. When the aircraft is in a first state, the flow channel switching mechanism is used to close the inlet of each guide pipe. At this time, each turbine generator arranged at the outlet of each guide pipe is in a non-working state. When the aircraft is in a second state, the flow channel switching mechanism is used to open the inlet of each guide pipe, and part of the fluid flows into each guide pipe, driving each turbine generator located at the outlet of each guide pipe to work, and each turbine generator works to generate electricity to provide electrical energy for the electric turbofan engine, which effectively solves the problem that the prior art cannot match the electrical energy required by the engine. At the same time, each turbine generator is arranged in each guide duct, which has little impact on the structural layout of the original power system and has a flexible installation method and a compact structure, and can be modularly installed according to the required power size of the electric turbofan engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the technical solutions in the embodiments of the present disclosure, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present disclosure. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0029] Figure 1A schematic diagram of the structure of an electric turbofan engine according to an embodiment of the present disclosure is shown;

[0030] Figure 2 The figure shows a schematic diagram of the structure of a flow channel switching mechanism according to an embodiment of the present disclosure.

[0031] Reference numerals:

[0032] 1 - boost assembly, 11 - fan, 12 - compressor, 13 - combustion chamber, 14 - turbine, 2 - guide duct, 3 - turbine generator, 4 - first flow channel, 5 - second flow channel, 6 - flow channel switching mechanism, 61 - first baffle, 62 - connecting rod, 63 - second baffle. DETAILED DESCRIPTION

[0033] Embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although certain embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be construed as being limited to the embodiments described herein, which are instead provided for a more thorough and complete understanding of the present disclosure. It should be understood that the drawings and embodiments of the present disclosure are only for exemplary purposes and are not intended to limit the scope of protection of the present disclosure.

[0034] It should be understood that the various steps described in the method embodiments of the present disclosure may be performed in different orders and / or in parallel. In addition, the method embodiments may include additional steps and / or omit the steps shown. The scope of the present disclosure is not limited in this respect.

[0035] The term "including" and its variations used in this document are open inclusions, that is, "including but not limited to". The term "based on" means "based at least in part on". The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one other embodiment"; the term "some embodiments" means "at least some embodiments". Relevant definitions of other terms will be given in the description below. It should be noted that the concepts of "first", "second", etc. mentioned in this disclosure are only used to distinguish different devices, modules or units, and are not used to limit the order or interdependence of the functions performed by these devices, modules or units.

[0036] It should be noted that the modifications of "one" and "plurality" mentioned in the present disclosure are illustrative rather than restrictive, and those skilled in the art should understand that unless otherwise clearly indicated in the context, it should be understood as "one or more".

[0037] The names of the messages or information exchanged between multiple devices in the embodiments of the present disclosure are only used for illustrative purposes and are not used to limit the scope of these messages or information.

[0038] The combination of laser weapons and intelligent electrified drones is an inevitable trend for future combat platforms. The realization of their comprehensive combat effectiveness is inseparable from efficient and high-performance propulsion systems. At the same time, it is accompanied by a large power extraction from the power propulsion system. Based on the existing mature turbofan engines, the development of high-power extraction multi-electric engines that replace conventional mechanical systems is the most feasible technical approach.

[0039] As a key technology for improving the performance of next-generation aircraft and engines, multi-electric technology has attracted keen attention from countries around the world. Among them, some countries have carried out verification of the dual-axis power extraction scheme of embedded starter generators, and the output power has reached the megawatt level. With the development of multi-electric technology, the output power of multi-electric technology cannot meet the huge demand for new sensors and directed energy weapons on future fighters. Therefore, some countries have carried out research and verification on the integration of embedded generators and engine components / systems through the Power Optimized Aircraft (POA) technology verification program. However, the demand for electricity of advanced airborne systems and weapon systems has reached more than megawatts.

[0040] In view of the above problems, the exemplary embodiments of the present disclosure provide an electric turbofan combined cycle engine, an aircraft and a control method to solve the problem in the prior art that the electric energy required by the engine cannot be matched.

[0041] An electric turbofan combined cycle engine according to an embodiment of the present disclosure will be described in detail below with reference to the accompanying drawings.

[0042] Figure 1 The figure shows a schematic diagram of the structure of an electric turbofan engine according to an embodiment of the present disclosure. Figure 1 As shown, an electric turbofan engine is applied to an aircraft, and the electric turbofan engine comprises: a supercharging component 1, a shell, a first flow channel 4, a second flow channel 5, a flow channel switching mechanism 6, a plurality of turbine generators 3 and a plurality of flow ducts 2, the supercharging component 1 is arranged in the shell, the supercharging component 1 is located in the first flow channel 4, a second flow channel 5 is formed between the outer wall of the supercharging component 1 and the inner wall of the shell, each flow duct 2 is arranged on the outer wall of the shell, each flow duct 2 is connected with the second flow channel 5, the flow channel switching mechanism 6 is arranged at the inlet of each flow duct 2, and each turbine generator 3 is arranged at the outlet of each flow duct 2; when the aircraft is in the first state, the flow channel switching mechanism 6 is used to close the inlet of each flow duct 2; when the aircraft is in the second state, the flow channel switching mechanism 6 is used to open the inlet of each flow duct 2.

[0043] In practical applications, an electric turbofan engine is applied to an aircraft, a boost component 1 is arranged in a shell, the boost component 1 is located in a first flow channel 4, a second flow channel 5 is formed between the outer wall of the boost component 1 and the inner wall of the shell, each guide pipe 2 is arranged on the outer wall of the shell, each guide pipe 2 is connected to the second flow channel 5, a flow channel switching mechanism 6 is arranged at the inlet of each guide pipe 2, and each turbine generator 3 is arranged at the outlet of each guide pipe 2. When air flows into the boost component 1, part of the fluid flows into the first flow channel 4, and the other part of the fluid flows into the second flow channel 5. When the aircraft When the aircraft is in the first state, the flow channel switching mechanism 6 is used to close the inlet of each guide tube 2. At this time, each turbine generator 3 located at the outlet of each guide tube 2 is in a non-working state. When the aircraft is in the second state, the flow channel switching mechanism 6 is used to open the inlet of each guide tube 2, and part of the fluid flows into each guide tube 2, driving each turbine generator 3 located at the outlet of each guide tube 2 to work. Each turbine generator 3 works to generate electricity to provide electric turbofan engine, effectively solving the problem that the prior art cannot match the electric energy required by the engine. At the same time, each turbine generator 3 is arranged in each guide tube 2, which has little impact on the structural layout of the original power system and has a flexible installation method and a compact structure, and can be modularly installed according to the required power size of the electric turbofan engine.

[0044] For example, Figure 1 As shown, the supercharging assembly 1 includes: a fan 11, a compressor 12, a combustion chamber 13 and a turbine 14. The fan 11 is fixedly connected to one end of the compressor 12, and the other end of the compressor 12 is communicated with the combustion chamber 13. The combustion chamber 13 is connected to the turbine 14, and each guide pipe 2 is arranged at a position close to the compressor 12. It can be understood that the fan 11, the compressor 12, the combustion chamber 13 and the turbine 14 rotate coaxially.

[0045] In another alternative, Figure 2 FIG. 1 is a schematic diagram of a flow channel switching mechanism according to an embodiment of the present disclosure. Figure 2 As shown, the flow channel switching mechanism includes a first baffle 61 and a second baffle 63. The first baffle 61 has a first hinged side and a first extended side opposite to the first hinged side. The second baffle 63 has a second hinged side and a second extended side opposite to the second hinged side. The thickness of the first hinged side is greater than the thickness of the first extended side. The first hinged side is hinged on the outer wall of the compressor, and the second hinged side is hinged at the entrance of each guide tube. The thickness of the second hinged side is greater than the thickness of the second extended side. Since the thickness of the second hinged side is greater than the thickness of the second extended side, the first baffle 61 and the second baffle 63 are easy to control, so that the positions of the first baffle 61 and the second baffle 63 are conveniently controlled, thereby effectively switching the flight state of the aircraft.

[0046] For example, the thickness of the first baffle 61 decreases along the distribution direction from the first hinged side to the first extended side, and the first baffle 61 is easier to control due to the pressure difference caused by different airflows when the airflow passes through the first baffle 61. The thickness of the second baffle 63 decreases along the distribution direction from the second hinged side to the second extended side. Here, the beneficial effects are the same as those of the first baffle 61, and will not be repeated here.

[0047] For example, Figure 2 As shown, the first baffle 61 and the second baffle 63 are both wedge-shaped baffles, the wedge-shaped tip of the first baffle 61 is the protruding end of the first baffle 61, and the wedge-shaped tip of the second baffle 63 is the protruding end of the second baffle 63. The baffles are wedge-shaped structures. Since the wedge-shaped structure itself has the self-locking feature, the flow channel switching mechanism can stably guide the airflow when the aircraft is in different flight states, so that the aircraft can obtain sufficient thrust in different flight modes.

[0048] In one example, if Figure 2 As shown, the flow channel switching mechanism of the exemplary embodiment of the present disclosure further includes a connecting rod 62, which is hinged on the same side of the first baffle 61 and the second baffle 63, and is arranged on the outer side wall of the compressor. The first baffle 61 and the second baffle 63 are connected by the connecting rod 62, and the second baffle 63 is driven by the connecting rod 62 to open or close the entrance of each guide tube, and the first baffle 61 and the second baffle 63 can also be synchronously deflected. At the same time, the connecting rod 62 is arranged on the outer side wall of the compressor to reduce air resistance.

[0049] For example, Figure 2 As shown, the guide surface of the first baffle plate 61 and the guide surface of the second baffle plate 63 are flat surfaces or curved surfaces.

[0050] The exemplary embodiments of the present disclosure provide an aircraft, including an electric turbofan engine of the exemplary embodiments of the present disclosure. It should be understood that the aircraft of the exemplary embodiments of the present disclosure may be a drone or a manned aircraft. For example:

[0051] Compared with the prior art, the beneficial effects of the aircraft provided by the embodiments of the present disclosure refer to the beneficial effects of the electric turbofan engine, which will not be elaborated here.

[0052] It should be noted that the aircraft provided in the embodiment of the present disclosure may also include a fuselage, a flight controller, etc. The engine, the flight controller, etc. are arranged in the fuselage, and the flight controller can control the flow channel switching mechanism to open or close the inlet of each guide tube according to the flight status.

[0053] In an optional manner, the flight mode control method is applied to the above-mentioned aircraft, and the flight mode control method includes:

[0054] In response to the first state flight instruction, controlling the electric turbofan engine to operate;

[0055] The flow channel switching mechanism is controlled to close the inlet of each guide pipe, and the first state flight instruction is used to indicate that each turbine generator is in a non-operating state;

[0056] In response to the second state flight instruction, controlling the electric turbofan engine to operate;

[0057] The flow channel switching mechanism is controlled to open the inlet of each guide pipe, and the first state flight instruction is used to indicate that each turbine generator is in a working state.

[0058] Exemplarily, the flight mode control method further includes:

[0059] The target physical parameters of the electric turbofan engine are determined when the electric turbofan engine is operating normally. It can be understood that the above-mentioned target physical parameters are actually the power Pz required for the electric turbofan engine to operate normally.

[0060] According to the actual physical parameters of the turbine generator determined under normal working conditions of the electric turbofan engine, it can be understood that the above actual physical parameters are actually the power generation power Px that can be generated by the gas in the second flow channel passing through the turbine generator per air mass flow rate, wherein the calculation formula of Px is as follows:

[0061]

[0062] Among them, C P is the specific heat capacity of air at constant pressure, η T is the turbine efficiency, ηe is the generator efficiency, T t is the turbine inlet temperature, P t is the turbine inlet pressure, P0 is the standard atmospheric pressure, and k is the air constant entropy index.

[0063] The geometric parameters of the turbine generator are determined based on the target physical parameters and the actual physical parameters. It is also possible to determine the air mass flow rate and quantity required for the turbine generator based on the Pz and Px values.

[0064] For example, taking a medium thrust turbofan engine as an example, the air turbine inlet temperature Tt is 450K, the air turbine inlet pressure Pt is 2.7 atmospheres, the air turbine efficiency ηT is 0.9, and the generator efficiency ηe is 0.88, then Px = 88.05kw / kg, so every kg of air flow in the second flow channel can generate 88.05kw of electrical energy. Two turbine generators are arranged along the outer wall of the boost assembly. Each turbine generator introduces 3kg of air in the second flow channel, which can meet the power requirements of general airborne laser weapons.

[0065] The above descriptions are only some embodiments of the present disclosure and an explanation of the technical principles used. Those skilled in the art should understand that the scope of disclosure involved in the present disclosure is not limited to the technical solutions formed by a specific combination of the above technical features, but should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the above disclosed concept. For example, a technical solution formed by replacing the above features with the technical features with similar functions disclosed in the present disclosure (but not limited to).

[0066] Although some specific embodiments of the present disclosure have been described in detail by way of example, it should be understood by those skilled in the art that the above examples are for illustration only and are not intended to limit the scope of the present disclosure. It should be understood by those skilled in the art that the above embodiments may be modified without departing from the scope and spirit of the present disclosure. The scope of the present disclosure is defined by the appended claims.

Claims

1. An electric turbofan engine, characterized in that: Applied to an aircraft, the electric turbofan engine comprises: a supercharging component, a shell, a first flow channel, a second flow channel, a flow channel switching mechanism, a plurality of turbine generators and a plurality of flow guide pipes, the supercharging component is arranged in the shell, the supercharging component is located in the first flow channel, the second flow channel is formed between the outer side wall of the supercharging component and the inner side wall of the shell, each of the flow guide pipes is arranged on the outer side wall of the shell, each of the flow guide pipes is communicated with the second flow channel, the flow channel switching mechanism is arranged at the inlet of each of the flow guide pipes, and each of the turbine generators is arranged at the outlet of each of the flow guide pipes; When the aircraft is in the first state, the flow channel switching mechanism is used to close the inlet of each of the flow guide pipes; When the aircraft is in the second state, the flow channel switching mechanism is used to open the inlet of each of the flow guide tubes.

2. The electric turbofan engine according to claim 1, characterized in that: The boost assembly includes: a fan, a compressor, a combustion chamber and a turbine. The fan is fixedly connected to one end of the compressor, the other end of the compressor is connected to the combustion chamber, the combustion chamber is connected to the turbine, and each of the guide pipes is arranged at a position close to the compressor.

3. The electric turbofan engine according to claim 2, characterized in that: The flow channel switching mechanism includes a first baffle and a second baffle, the first baffle having a first hinged side and a first extended side opposite to the first hinged side, the second baffle having a second hinged side and a second extended side opposite to the second hinged side, the thickness of the first hinged side being greater than the thickness of the first extended side; The first hinged side is hinged on the outer side wall of the compressor, the second hinged side is hinged on the inlet of each of the guide tubes, and the thickness of the second hinged side is greater than the thickness of the second extended side.

4. The electric turbofan engine according to claim 3, characterized in that: The thickness of the first baffle decreases along a distribution direction from the first hinged side to the first extended side, and the thickness of the second baffle decreases along a distribution direction from the second hinged side to the second extended side.

5. The electric turbofan engine according to claim 3, characterized in that: The first baffle plate and the second baffle plate are both wedge-shaped baffle plates, the wedge-shaped tip of the first baffle plate is the protruding end of the first baffle plate, and the wedge-shaped tip of the second baffle plate is the protruding end of the second baffle plate; and / or, The flow channel switching mechanism also includes a connecting rod, which is hinged on the same side of the first baffle plate and the second baffle plate, and the connecting rod is arranged on the outer side wall of the compressor.

6. The electric turbofan engine according to claim 3, characterized in that: The guide surface of the first baffle plate and the guide surface of the second baffle plate are flat surfaces or curved surfaces.

7. The electric turbofan engine according to claim 2, characterized in that: The fan, the compressor, the combustion chamber and the turbine rotate coaxially.

8. An aircraft, characterized in that: It comprises the electric turbofan engine as described in any one of claims 1 to 7.

9. A flight mode control method, characterized in that: For the aircraft of claim 8, the method comprises: In response to the first state flight instruction, controlling the electric turbofan engine to operate; Controlling the flow channel switching mechanism to close the inlet of each of the guide pipes, the first state flight instruction is used to indicate that each turbine generator is in a non-working state; In response to the second state flight instruction, controlling the electric turbofan engine to operate; The flow channel switching mechanism is controlled to open the inlet of each of the guide tubes, and the first state flight instruction is used to indicate that each turbine generator is in a working state.

10. The flight mode control method according to claim 9, characterized in that: The flight mode control method further includes: Determining target physical parameters of the electric turbofan engine when the electric turbofan engine is operating normally; Determine the actual physical parameters of the turbine generator based on the normal operation of the electric turbofan engine; A geometric parameter of the turbine generator is determined based on the target physical parameter and the actual physical parameter.

Images