A hydrogen-powered accelerating ducted fan for aircraft hybrid power system

Abstract

The present application belongs to the technical field of aircraft hybrid power system design, and specifically relates to a hydrogen energy acceleration ducted fan of an aircraft hybrid power system, comprising an outer casing, a nozzle, an air intake cone, an inner casing, a tail cone, an electric fan, an electric motor, a rectifying support plate, a hydrogen injection rod, and an ignition nozzle; the nozzle is connected to the rear end of the outer casing, and the air intake cone, the inner casing, and the tail cone are sequentially arranged in the outer casing; there is an annular gap between the rear end of the air intake cone and the front end of the inner casing; the electric fan is arranged in the outer casing and is located at the position of the annular gap; the electric motor is arranged in the inner casing, and its rotor is connected to the electric fan; there are multiple rectifying support plates, which are supported circumferentially between the outer casing and the inner casing; there are multiple hydrogen injection rods, which are arranged through the outer casing and extend into each rectifying support plate, and each nozzle thereon is aligned with each hydrogen injection hole on the side walls on both sides of the rectifying support plate; the ignition nozzle is arranged through the outer casing and extends between the rear edges of two adjacent rectifying support plates.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft hybrid power system design, and specifically relates to a hydrogen energy accelerating ducted fan of an aircraft hybrid power system. Background Art

[0002] The aircraft's hybrid power system uses the main engine and ducted fan to work together, which increases the equivalent bypass ratio of the power system and significantly reduces the fuel consumption of the power system, which can well meet the aircraft's long-term flight needs.

[0003] However, installing a ducted fan in an aircraft hybrid power system will increase the windward area of ​​the power system and increase the windward resistance of the power system, making it difficult to generate sufficient thrust to allow the aircraft to fly at high speed.

[0004] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0005] The purpose of the present application is to provide a hydrogen-powered accelerating ducted fan for an aircraft hybrid power system to overcome or alleviate at least one of the known technical deficiencies.

[0006] The technical solution of this application is:

[0007] A hydrogen energy accelerating ducted fan of an aircraft hybrid power system, comprising an outer casing, a nozzle, an air intake cone, an inner casing, a tail cone, an electric fan, an electric motor, a rectifying support plate, a hydrogen injection rod, and an ignition nozzle;

[0008] The nozzle is connected to the rear end of the outer casing, and the air intake cone, the inner casing, and the tail cone are sequentially arranged in the outer casing, wherein the air intake cone and the outer casing are supported by a plurality of air intake cone support rods along the circumferential direction, and an annular gap exists between the rear end and the front end of the inner casing; the rear end of the inner casing is connected to the front end of the tail cone, and the inner casing has a plurality of front end cooling air intake holes distributed along the circumferential direction; the tail cone extends into the nozzle, and has a plurality of rear end cooling exhaust holes distributed along the circumferential direction;

[0009] The electric fan is arranged in the outer casing at the position of the annular gap;

[0010] The motor is arranged in the inner casing, wherein the motor stator and the inner casing are supported along the circumferential direction by a plurality of stator support rods; the motor housing and the rotor are connected by a bearing, and the housing extends into the air intake cone and is supported along the circumferential direction by a plurality of housing support rods; the motor rotor is connected to the electric fan;

[0011] There are multiple rectifying support plates, which are supported between the outer casing and the inner casing along the circumferential direction and are located behind the front cooling air inlet hole; the leading edge of the rectifying support plate has multiple leading edge cooling air inlet holes, the trailing edge has multiple trailing edge cooling exhaust holes, the side walls on both sides have multiple side wall cooling holes, and have multiple hydrogen injection holes, and the hydrogen injection holes are close to the trailing edge of the rectifying support plate;

[0012] There are multiple hydrogen injection rods, which are arranged through the outer casing and extend into each rectifying support plate, and each nozzle on the rod is aligned with each hydrogen injection hole on the side walls of both sides of the rectifying support plate;

[0013] The ignition nozzle is arranged through the outer casing and extends between the rear edges of two adjacent rectifier support plates.

[0014] Optionally, in the hydrogen-powered acceleration duct fan of the above-mentioned aircraft hybrid power system, the motor rotor is connected to the electric fan via a mortise and tenon structure.

[0015] Optionally, the above-mentioned aircraft hybrid power system hydrogen energy acceleration duct fan has a normal state and an acceleration state;

[0016] When the aircraft hybrid power system hydrogen energy acceleration ducted fan is in a normal state, the electric motor drives the electric fan to operate, so that the aircraft hybrid power system hydrogen energy acceleration ducted fan inhales air and ejects it through the nozzle at an accelerated speed to generate thrust;

[0017] When the aircraft hybrid power system hydrogen energy acceleration ducted fan is in the acceleration state, the electric motor drives the electric fan to operate, so that the aircraft hybrid power system hydrogen energy acceleration ducted fan inhales air, and gaseous hydrogen is sprayed into the aircraft hybrid power system hydrogen energy acceleration ducted fan through each hydrogen injection rod to be mixed with the air, and ignited by the ignition nozzle in the reflow zone generated by the trailing edge of each rectifier support plate to organize combustion and generate high-temperature combustion gas, which is accelerated and ejected through the nozzle to generate thrust.

[0018] Optionally, in the above-mentioned aircraft hybrid power system hydrogen energy acceleration ducted fan, the sum of the trailing edge areas of each rectifying support plate is 30% to 50% of the cross-sectional flow area where the trailing edge of the rectifying support plate is located.

[0019] Optionally, in the above-mentioned aircraft hybrid power system hydrogen energy acceleration ducted fan, the hydrogen injection holes on the side walls of both sides of each rectifying support plate are centrally arranged in the range of 1 / 2 to 2 / 3 of the length of the rectifying support plate.

[0020] Optionally, in the above-mentioned aircraft hybrid power system hydrogen energy acceleration duct fan, the electric motor is connected to an external power supply through a line, and the line is routed through a rectifier support plate.

[0021] This application has at least the following beneficial technical effects:

[0022] A hydrogen-powered accelerated ducted fan for an aircraft hybrid power system is provided. The thrust of the ducted fan is greatly increased by utilizing the characteristics of rapid and efficient combustion of hydrogen and rapid flame propagation speed and high temperature. The windward area and length of the ducted fan are not changed, so that the thrust of the entire hybrid power system meets the requirements of rapid flight of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 is a schematic diagram of a hydrogen energy accelerating ducted fan of an aircraft hybrid power system provided by an embodiment of the present application;

[0024] Figure 2 is a schematic diagram of a rectifier support plate provided in an embodiment of the present application;

[0025] Figure 3 It is a schematic diagram of the coordination of the rectifying support plate, the hydrogen injection rod, and the ignition nozzle provided in the embodiment of the present application;

[0026] in:

[0027] 1-outer casing; 2-nozzle; 3-intake cone; 4-inner casing; 5-tail cone; 6-electric fan; 7-electric motor; 8-rectifier support plate; 9-hydrogen injection rod; 10-ignition nozzle; 11-intake cone support rod; 12-stator support rod; 13-bearing; 14-casing support rod; 15-line; 16-front end cooling air inlet hole; 17-rear end cooling exhaust hole; 18-leading edge cooling air inlet hole; 19-trailing edge cooling exhaust hole; 20-side wall cooling hole; 21-hydrogen injection hole.

[0028] In order to better illustrate the present embodiment, some contents of the drawings may be omitted, enlarged or reduced, which is only used for illustrative purposes and should not be construed as limiting the present application. DETAILED DESCRIPTION

[0029] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0030] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should be the common meanings understood by those skilled in the art in the field to which this application belongs. The term "include" used in the description of this application means that the concepts appearing before the term include the concepts listed after the term and their equivalents, without excluding other related concepts.

[0031] In addition, the words indicating orientation used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and other similar words used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0032] Without increasing the frontal area of ​​the aircraft hybrid power system, a combustion chamber can be set up behind the ducted fan to burn a large amount of fresh air to further generate thrust, thereby increasing the thrust of the hybrid power system and enabling the aircraft to fly at high speed. Due to the low temperature and pressure of the airflow after the ducted fan, the use of aviation kerosene as fuel has poor atomization and evaporation effects, low combustion efficiency, and a long combustion section, making it difficult to design and achieve good technical effects. Hydrogen has the characteristics of rapid combustion, fast flame propagation speed, and high temperature. Using hydrogen as fuel, it can be directly mixed with air in a gaseous state, can burn quickly in a short distance, has a high combustion efficiency, and can greatly increase the thrust of the ducted fan without increasing the frontal area and length of the ducted fan, meeting the aircraft hybrid power system's demand for high thrust.

[0033] Based on the above, the embodiment of the present application provides a hydrogen energy acceleration ducted fan of an aircraft hybrid power system, such as Figure 1 As shown, it includes an outer casing 1, a nozzle 2, an air intake cone 3, an inner casing 4, a tail cone 5, an electric fan 6, an electric motor 7, a rectifier support plate 8, a hydrogen injection rod 9, and an ignition nozzle 10.

[0034] The nozzle 2 is connected to the rear end of the outer casing 1 and is a non-adjustable retractable structure.

[0035] The intake cone 3, the inner casing 4 and the tail cone 5 are sequentially arranged in the outer casing 1, wherein the intake cone 3 and the outer casing 1 are supported circumferentially by a plurality of intake cone support rods 11, and an annular gap exists between the rear end and the front end of the inner casing 4; the rear end of the inner casing 4 is connected to the front end of the tail cone 5, and the inner casing 4 has a plurality of front end cooling intake holes 16 distributed along the circumferential direction; the tail cone 5 extends into the nozzle 2, and has a plurality of rear end cooling exhaust holes 17 distributed along the circumferential direction.

[0036] The electric fan 6 is arranged in the outer casing 1 at the position of the annular gap.

[0037] The electric motor 7 is arranged in the inner casing 4, wherein the stator of the electric motor 7 and the inner casing 4 are supported circumferentially by a plurality of stator support rods 12; the outer casing of the electric motor 7 and the rotor are connected by a bearing 13, and the outer casing extends into the air intake cone 3, and is supported circumferentially by a plurality of outer casing support rods 14 between the outer casing and the air intake cone 3; the rotor of the electric motor 7 is connected to the electric fan 6, and specifically can be connected to the electric fan 6 by a mortise and tenon structure.

[0038] There are multiple straightening support plates 8, which are supported between the outer casing 1 and the inner casing 4 along the circumferential direction and are located behind the front cooling air intake hole 16. The front edge of the straightening support plate 8 has multiple front edge cooling air intake holes 18, the rear edge has multiple rear edge cooling exhaust holes 19, the side walls on both sides have multiple side wall cooling holes 20, and have multiple hydrogen injection holes 21. The hydrogen injection holes 21 are close to the rear edge of the straightening support plate 8, such as Figure 2 shown.

[0039] There are multiple hydrogen injection rods 9, which are arranged through the outer casing 1 and extend into each rectifying support plate 8, and each nozzle thereon is aligned with each hydrogen injection hole 21 on the side walls of both sides of the rectifying support plate 8.

[0040] The ignition nozzle 10 is disposed through the outer casing 1 and extends between the rear edges of two adjacent rectifying support plates 8 .

[0041] The hydrogen-powered accelerating ducted fan of the aircraft hybrid power system disclosed in the above-mentioned embodiment has a normal state and an accelerating state.

[0042] When the aircraft hybrid power system hydrogen energy acceleration ducted fan is in a normal state, the electric motor 7 drives the electric fan 6 to operate, so that the aircraft hybrid power system hydrogen energy acceleration ducted fan inhales air and accelerates to eject it through the nozzle 2 to generate thrust. This working state is suitable for normal take-off and cruising flight of the aircraft.

[0043] When the aircraft hybrid power system hydrogen energy acceleration ducted fan is in the acceleration state, the electric motor 7 drives the electric fan 6 to operate, so that the aircraft hybrid power system hydrogen energy acceleration ducted fan inhales air, and gaseous hydrogen is sprayed into the aircraft hybrid power system hydrogen energy acceleration ducted fan through each hydrogen injection rod 9 to mix with the air, and is ignited by the ignition nozzle 10 in the reflow zone generated at the trailing edge of each rectifier support plate 8 to organize combustion and generate high-temperature combustion gas, which is accelerated and ejected through the nozzle 2 to generate greater thrust. This working state is suitable for situations where the aircraft needs to increase the thrust, such as taking off in harsh environments such as plateaus, and situations where the aircraft needs to accelerate and fly at high speed.

[0044] When the hydrogen energy acceleration duct fan of the aircraft hybrid power system disclosed in the above embodiment is working, part of the air behind the electric fan 6 can enter the inner casing 4 through the front cooling air inlet 16 to cool the electric motor 7, and then be discharged through the rear cooling exhaust hole 17, thereby cooling the inner casing 4 and the tail cone 5 along the way and protecting the inner casing 4 and the tail cone 5 from being ablated by high-temperature combustion gas.

[0045] When the hydrogen energy accelerated ducted fan of the aircraft hybrid power system disclosed in the above embodiment is working, part of the air behind the electric fan 6 can enter the rectifying support plate 8 through each leading edge cooling air inlet hole 18 to cool the rectifying support plate 8 and protect the rectifying support plate 8 from being burned by the high-temperature combustion gas, and then be discharged through each side wall cooling hole 20 and the trailing edge cooling exhaust hole 19. The air flowing out through each side wall cooling hole 20 can increase the turbulence of the air behind the electric fan 6, which is conducive to mixing with hydrogen. The air discharged through each trailing edge cooling exhaust hole 19 can blow the flame away from the trailing edge of the rectifying support plate 8 to prevent surface combustion, thereby further protecting the rectifying support plate 8 from being burned by the high-temperature combustion gas.

[0046] In the hydrogen energy acceleration ducted fan of the aircraft hybrid power system disclosed in the above-mentioned embodiment, the force applied to the air intake cone 3 can be transmitted to the outer casing 1 through each air intake cone support rod 11, the force generated by the rotor of the electric motor 7 can be transmitted to the outer casing through the bearing 13, and then transmitted to the air intake cone 3 through each outer casing support rod 14, and the force generated by the stator of the electric motor 7 can be transmitted to the inner casing 4 through each stator support rod 12, and then transmitted to the outer casing 1 through each rectifier support plate 8.

[0047] Each rectifying support plate 8 is supported between the outer casing 1 and the inner casing 4 along the circumferential direction, and can transmit force between the inner casing 4 and the outer casing 1, and rectify the airflow, so that the airflow is close to axial flow, and the ability of the aircraft hybrid power system hydrogen energy acceleration duct fan to generate axial thrust is increased, and the trailing edge of each rectifying support plate 8 can form a reflow zone, providing good conditions for the combustion of hydrogen. In addition, due to the fast propagation speed of hydrogen flame, the sum of the trailing edge areas of each rectifying support plate 8 can be designed to be 30% to 50% of the cross-sectional flow area where the trailing edge of the rectifying support plate 8 is located. Under this area ratio, the flame can be directly transmitted between each rectifying support plate 8, and there is no need to set up an additional circumferential flame connection device.

[0048] In the case where the aircraft does not need to fly at supersonic speed, the temperature of the outlet of the hydrogen energy acceleration duct fan of the aircraft hybrid power system can be designed to be within 1000K, and the hydrogen injection holes 21 on the side walls of the rectifier support plate 8 are designed to be centrally set in the range of 1 / 2 to 2 / 3 of the length of the rectifier support plate 8, such as Figure 3As shown, X / Y=1 / 2~2 / 3, wherein X is the height of the distribution range of the hydrogen injection holes 21 on the side walls of the rectifying support plate 8, and Y is the height of the rectifying support plate 8. The temperature of the outlet of the hydrogen energy acceleration duct fan of the aircraft hybrid power system can be limited to within 1000K, and no ablation will be caused to the outer casing 1.

[0049] The motor 7 is connected to an external power source via a line 15 , and the line 15 is designed to be routed through the rectifier support plate 8 to avoid being scour by high-speed airflow.

[0050] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. A hydrogen-powered accelerating ducted fan for an aircraft hybrid power system, characterized in that: It comprises an outer casing (1), a nozzle (2), an air intake cone (3), an inner casing (4), a tail cone (5), an electric fan (6), an electric motor (7), a rectifier support plate (8), a hydrogen injection rod (9), and an ignition nozzle (10); The nozzle (2) is connected to the rear end of the outer casing (1), and the air intake cone (3), the inner casing (4), and the tail cone (5) are arranged in sequence in the outer casing (1), wherein the air intake cone (3) and the outer casing (1) are supported in the circumferential direction by a plurality of air intake cone support rods (11), and an annular gap exists between the rear end and the front end of the inner casing (4); the rear end of the inner casing (4) is connected to the front end of the tail cone (5), and the inner casing (4) has a plurality of front end cooling air intake holes (16) distributed in the circumferential direction; the tail cone (5) extends into the nozzle (2), and has a plurality of rear end cooling exhaust holes (17) distributed in the circumferential direction; The electric fan (6) is arranged in the outer casing (1) at the position of the annular gap; The electric motor (7) is arranged in the inner casing (4), wherein the stator of the electric motor (7) and the inner casing (4) are supported in the circumferential direction by a plurality of stator support rods (12); the outer casing of the electric motor (7) and the rotor are connected by a bearing (13), and the outer casing extends into the air intake cone (3) and is supported in the circumferential direction by a plurality of outer casing support rods (14) between the outer casing and the air intake cone (3); the rotor of the electric motor (7) is connected to an electric fan (6); There are a plurality of rectifying support plates (8), which are supported between the outer casing (1) and the inner casing (4) along the circumferential direction and are located behind the front cooling air inlet hole (16); the leading edge of the rectifying support plate (8) has a plurality of leading edge cooling air inlet holes (18), the trailing edge has a plurality of trailing edge cooling exhaust holes (19), the side walls on both sides have a plurality of side wall cooling holes (20), and have a plurality of hydrogen injection holes (21), and the hydrogen injection holes (21) are close to the trailing edge of the rectifying support plate (8); There are a plurality of hydrogen injection rods (9), which are arranged through the outer casing (1) and extend into each rectifying support plate (8), and each nozzle on the hydrogen injection rod is aligned with each hydrogen injection hole (21) on the side walls of both sides of the rectifying support plate (8); The ignition nozzle (10) is arranged through the outer casing (1) and extends between the rear edges of two adjacent rectifying support plates (8).

2. The aircraft hybrid power system hydrogen energy accelerating ducted fan according to claim 1, characterized in that: The rotor of the electric motor (7) is connected to the electric fan (6) via a mortise and tenon structure.

3. The aircraft hybrid power system hydrogen energy accelerating ducted fan according to claim 2, characterized in that: It has a normal state and an accelerated state; When the aircraft hybrid power system hydrogen energy accelerating ducted fan is in a normal state, the electric motor (7) drives the electric fan (6) to operate, so that the aircraft hybrid power system hydrogen energy accelerating ducted fan inhales air and ejects it through the nozzle (2) at an accelerated speed, thereby generating thrust; When the aircraft hybrid power system hydrogen energy acceleration ducted fan is in an accelerating state, the electric motor (7) drives the electric fan (6) to operate, so that the aircraft hybrid power system hydrogen energy acceleration ducted fan inhales air, and gaseous hydrogen is injected into the aircraft hybrid power system hydrogen energy acceleration ducted fan through each hydrogen injection rod (9) to be mixed with air, and ignited by the ignition nozzle (10) in the reflow zone generated by the trailing edge of each rectifying support plate (8), and combustion is organized to generate high-temperature combustion gas, which is accelerated and ejected through the nozzle (2) to generate thrust.

4. The aircraft hybrid power system hydrogen energy accelerating ducted fan according to claim 3, characterized in that: The sum of the rear edge areas of the rectifying support plates (8) is 30% to 50% of the cross-sectional flow area of ​​the rear edge of the rectifying support plate (8).

5. The aircraft hybrid power system hydrogen energy accelerating ducted fan according to claim 4, characterized in that: The hydrogen injection holes (21) on the side walls of each rectifying support plate (8) are centrally arranged in the range of 1 / 2 to 2 / 3 of the length of the rectifying support plate (8).

6. The aircraft hybrid power system hydrogen energy accelerating ducted fan according to claim 5, characterized in that: The motor (7) is connected to an external power source via a line (15), and the line (15) is routed through the rectifier support plate (8).

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