CN119551182B - Hydrogen energy accelerating duct fan of aircraft hybrid power system - Google Patents
Hydrogen energy accelerating duct fan of aircraft hybrid power system Download PDFInfo
- Publication number
- CN119551182B CN119551182B CN202510126234.9A CN202510126234A CN119551182B CN 119551182 B CN119551182 B CN 119551182B CN 202510126234 A CN202510126234 A CN 202510126234A CN 119551182 B CN119551182 B CN 119551182B
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- outer casing
- power system
- hybrid power
- support plate
- rectifying support
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C15/00—Attitude, flight direction, or altitude control by jet reaction
- B64C15/02—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/16—Aircraft characterised by the type or position of power plants of jet type
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The application belongs to the technical field of design of aircraft hybrid power systems, and particularly relates to a hydrogen energy acceleration ducted fan of an aircraft hybrid power system, which comprises an outer casing, a spray pipe, an air inlet cone, an inner casing, a tail cone, an electric fan, a motor, a rectifying support plate, a hydrogen injection rod and an ignition electric nozzle; the jet pipe is connected to the rear end of the outer casing, the air inlet cone, the inner casing and the tail cone are sequentially arranged in the outer casing, annular gaps are formed between the rear end of the air inlet cone and the front end of the inner casing, the electric fan is arranged in the outer casing and is positioned at the annular gaps, the electric motor is arranged in the inner casing, the rotor of the electric motor is connected with the electric fan, the plurality of rectifying support plates are circumferentially supported between the outer casing and the inner casing, the plurality of hydrogen injection rods penetrate through the outer casing and extend into the rectifying support plates, the nozzles on the hydrogen injection rods are aligned with the hydrogen injection holes on the side walls of the two sides of the rectifying support plates, and the ignition nozzle penetrates through the outer casing and extends into the space between the rear edges of the two adjacent rectifying support plates.
Description
Technical Field
The application belongs to the technical field of design of aircraft hybrid power systems, and particularly relates to a hydrogen energy acceleration duct fan of an aircraft hybrid power system.
Background
The aircraft hybrid power system adopts the combined work of the main engine and the duct fan, so that the equivalent duct ratio of the power system is increased, the fuel consumption rate of the power system is greatly reduced, and the long-term aviation requirement of the aircraft can be well met.
However, the bypass fan is arranged in the hybrid power system of the aircraft, so that the windward area of the power system is increased, the windward resistance of the power system is increased, and enough thrust is difficult to generate, so that the aircraft flies at a high speed.
The present application has been made in view of the above-described technical drawbacks.
Disclosure of Invention
It is an object of the present application to provide an aircraft hybrid system hydrogen energy accelerating ducted fan that overcomes or mitigates at least one of the known technical drawbacks.
The technical scheme of the application is as follows:
a hydrogen energy acceleration ducted fan of an aircraft hybrid power system comprises an outer casing, a spray pipe, an air inlet cone, an inner casing, a tail cone, an electric fan, a motor, a rectifying support plate, a hydrogen spray rod and an ignition electric nozzle;
the spray pipe is connected to the rear end of the outer casing, and the air inlet cone, the inner casing and the tail cone are sequentially arranged in the outer casing, wherein a plurality of air inlet cone supporting rods are supported between the air inlet cone and the outer casing along the circumferential direction, and annular gaps exist between the rear end and the front end of the inner casing;
the electric fan is arranged in the outer casing and positioned at the annular gap position;
the motor is arranged in the inner casing, wherein a plurality of stator support rods are used for supporting between a motor stator and the inner casing along the circumferential direction; the motor shell is connected with the rotor through a bearing, and the shell extends into the air inlet cone and is supported with the air inlet cone along the circumferential direction through a plurality of shell supporting rods;
The front edge of the rectifying support plate is provided with a plurality of front edge cooling air inlets, the rear edge is provided with a plurality of rear edge cooling air outlets, the side walls of the two sides are provided with a plurality of side wall cooling holes, and a plurality of hydrogen injection holes are arranged, and are close to the rear edge of the rectifying support plate;
The plurality of hydrogen injection rods penetrate through the outer casing and extend into each rectifying support plate, and each nozzle on the hydrogen injection rods is aligned to each hydrogen injection hole on the side walls of the two sides of each rectifying support plate;
the ignition nozzle penetrates through the outer casing and extends into the space between the rear edges of two adjacent rectifying support plates.
Optionally, in the above-mentioned hydrogen energy acceleration ducted fan of the aircraft hybrid power system, the motor rotor is connected to the electric fan through a joggle structure.
Optionally, the hydrogen energy acceleration ducted fan of the aircraft hybrid power system has a conventional state and an acceleration state;
when the hydrogen energy accelerating ducted fan of the aircraft hybrid power system is in a normal state, the electric fan is driven by the motor to operate, so that the hydrogen energy accelerating ducted fan of the aircraft hybrid power system sucks air, and the air is accelerated and sprayed out through the spray pipe to generate thrust;
When the hydrogen energy accelerating ducted fan of the aircraft hybrid power system is in an accelerating state, the electric fan is driven by the motor to operate, so that the air is sucked into the hydrogen energy accelerating ducted fan of the aircraft hybrid power system, gaseous hydrogen is sprayed into the hydrogen energy accelerating ducted fan of the aircraft hybrid power system through each hydrogen spraying rod to be mixed with the air, a backflow area generated at the tail edge of each rectifying support plate is ignited by the ignition electric nozzle to be organized and combusted, high-temperature fuel gas is generated, and the fuel gas is sprayed out in an accelerating way through the spray pipe to generate thrust.
Optionally, in the hydrogen energy acceleration ducted fan of the aircraft hybrid power system, the sum of the areas of the rear edges of the rectifying support plates is 30% -50% of the cross-section flow area where the rear edges of the rectifying support plates are located.
Optionally, in the above-mentioned hydrogen energy acceleration ducted fan of the aircraft hybrid power system, the hydrogen injection holes on the side walls of two sides of each rectifying support plate are centrally arranged in a range of 1/2-2/3 of the length of the rectifying support plate.
Optionally, in the hydrogen energy acceleration ducted fan of the aircraft hybrid power system, the motor is connected with an external power supply through a circuit, and the circuit runs through a travelling wire in the rectifying support plate.
The application has at least the following beneficial technical effects:
The utility model provides a hydrogen energy acceleration ducted fan of aircraft hybrid system utilizes hydrogen quick, high-efficient burning and flame propagation speed fast, characteristics that the temperature is high, under the prerequisite that does not change the windward area and the length of ducted fan, designs to promote the thrust of ducted fan by a wide margin for whole hybrid system thrust satisfies the demand of aircraft fast flight.
Drawings
FIG. 1 is a schematic diagram of a hydrogen energy accelerating ducted fan of an aircraft hybrid system provided by an embodiment of the present application;
fig. 2 is a schematic diagram of a rectifying support plate according to an embodiment of the present application;
FIG. 3 is a schematic diagram of the cooperation of the rectifying support plate, the hydrogen injection rod and the ignition electrode tip provided by the embodiment of the application;
Wherein:
1-outer casing, 2-spray pipe, 3-air inlet cone, 4-inner casing, 5-tail cone, 6-electric fan, 7-motor, 8-rectifying support plate, 9-hydrogen injection rod, 10-ignition electric nozzle, 11-air inlet cone support rod, 12-stator support rod, 13-bearing, 14-shell support rod, 15-line, 16-front end cooling air inlet hole, 17-rear end cooling air exhaust hole, 18-front edge cooling air inlet hole, 19-rear edge cooling air exhaust hole, 20-side wall cooling hole and 21-hydrogen injection hole.
For the purpose of better illustrating the embodiments, the drawings are certain drawings that are omitted, enlarged or reduced in size, and are not to be construed as limiting the application.
Detailed Description
In order to make the technical solution of the present application and its advantages more clear, the technical solution of the present application will be further and completely described in detail with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application and not for limitation of the present application. It should be noted that, for convenience of description, only a portion related to the present application is shown in the drawings, and other related portions may refer to a general design.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of the application should be given the ordinary meaning as understood by one of ordinary skill in the art to which the application pertains. As used in this description of the application, the word "comprising" means that the element preceding the word covers the elements listed after the word and equivalents thereof without excluding other associated elements.
In addition, the words used in the description of the present application to indicate directions are merely used to indicate relative directions or positional relationships, and when the absolute position of the object to be described is changed, the relative positional relationship may be changed accordingly. It should also be noted that, unless explicitly stated or limited otherwise, terms such as "mounted," "connected," and the like, as used in the description of the present application, should be construed broadly, and may be, for example, fixedly connected, detachably connected, mechanically connected, electrically connected, directly connected, or indirectly connected through an intermediate medium, as would be understood by one of ordinary skill in the art in view of the specific meaning of the present application.
On the premise of not increasing the windward area of the hybrid power system of the aircraft, a large amount of fresh air can be combusted by arranging a combustion chamber behind the ducted fan to further generate thrust so as to increase the thrust of the hybrid power system and enable the hybrid power system to fly at a high speed. The air flow temperature and pressure are low after the ducted fan, aviation kerosene is used as fuel, the atomization and evaporation effects of the aviation fuel are poor, the combustion efficiency is low, the required combustion section is long, the better technical effect is difficult to design and obtain, the hydrogen has the characteristics of rapid combustion, rapid flame propagation speed and high temperature, the hydrogen is used as fuel, the hydrogen is directly mixed with air in a gaseous state, the rapid combustion can be performed in a short distance, the higher combustion efficiency is achieved, the thrust of the ducted fan can be greatly improved on the premise that the windward area and the length of the ducted fan are not increased, and the requirement of an aircraft hybrid power system on high thrust is met.
Based on the above, the embodiment of the application provides a hydrogen energy acceleration ducted fan of an aircraft hybrid power system, as shown in fig. 1, which comprises an outer casing 1, a spray pipe 2, an air inlet cone 3, an inner casing 4, a tail cone 5, an electric fan 6, a motor 7, a rectifying support plate 8, a hydrogen injection rod 9 and an ignition electric nozzle 10.
The spray pipe 2 is connected to the rear end of the outer casing 1 and is of an unadjustable shrinkage structure.
The air inlet cone 3, the inner casing 4 and the tail cone 5 are sequentially arranged in the outer casing 1, wherein a plurality of air inlet cone supporting rods 11 are supported between the air inlet cone 3 and the outer casing 1 along the circumferential direction, annular gaps are formed between the rear end of the air inlet cone and the front end of the inner casing 4, the rear end of the inner casing 4 is connected with the front end of the tail cone 5, a plurality of front end cooling air inlet holes 16 distributed along the circumferential direction are formed in the inner casing 4, the tail cone 5 extends into the spray pipe 2, and a plurality of rear end cooling air outlet holes 17 distributed along the circumferential direction are formed in the tail cone 5.
The electric fan 6 is disposed in the outer casing 1 at the annular slit position.
The motor 7 is arranged in the inner casing 4, wherein a plurality of stator struts 12 are supported between a stator of the motor 7 and the inner casing 4 along the circumferential direction, a housing of the motor 7 is connected with a rotor through bearings 13, the housing extends into the air inlet cone 3 and is supported between the housing and the air inlet cone 3 along the circumferential direction through a plurality of housing struts 14, the rotor of the motor 7 is connected with the electric fan 6, and the motor 7 can be connected with the electric fan 6 through a joggle joint structure.
The rectifying support plates 8 are supported between the outer casing 1 and the inner casing 4 along the circumferential direction and are positioned behind the front end cooling air inlet holes 16. The rectifying support plate 8 has a plurality of front edge cooling air inlet holes 18 at the front edge, a plurality of rear edge cooling air outlet holes 19 at the rear edge, a plurality of side wall cooling holes 20 at both side walls, and a plurality of hydrogen injection holes 21, the hydrogen injection holes 21 being close to the rear edge of the rectifying support plate 8 as shown in fig. 2.
The hydrogen injection rods 9 are arranged through the outer casing 1 and extend into the rectifying support plates 8, and the nozzles on the hydrogen injection rods are aligned with the hydrogen injection holes 21 on the side walls of the two sides of the rectifying support plates 8.
The ignition nozzle 10 penetrates through the outer casing 1 and extends into the space between the rear edges of two adjacent rectifying support plates 8.
The hydrogen energy acceleration ducted fan of the aircraft hybrid power system disclosed in the above embodiment has a normal state and an acceleration state.
When the hydrogen energy accelerating ducted fan of the aircraft hybrid power system is in a normal state, the motor 7 is used for driving the electric fan 6 to operate, so that the hydrogen energy accelerating ducted fan of the aircraft hybrid power system sucks air, and the air is accelerated and sprayed out through the spray pipe 2 to generate thrust.
When the hydrogen energy accelerating ducted fan of the aircraft hybrid power system is in an accelerating state, the electric fan 6 is driven by the motor 7 to operate, so that the air is sucked into the hydrogen energy accelerating ducted fan of the aircraft hybrid power system, gaseous hydrogen is sprayed into the hydrogen energy accelerating ducted fan of the aircraft hybrid power system through each hydrogen spraying rod 9 to be mixed with the air, a backflow area generated at the tail edge of each rectifying support plate 8 is ignited by the ignition electric nozzle 10 to be subjected to tissue combustion, high-temperature fuel gas is generated, and the high-temperature fuel gas is sprayed out through the spray pipe 2 in an accelerating way to generate larger thrust.
When the hydrogen energy accelerating ducted fan of the aircraft hybrid power system disclosed by the embodiment works, part of air behind the electric fan 6 can enter the inner casing 4 through the front end cooling air inlet 16 to cool the motor 7, and then is discharged through the rear end cooling air outlet 17 to cool the inner casing 4 and the tail cone 5 along the way, so that the inner casing 4 and the tail cone 5 are protected from being ablated by high-temperature fuel gas.
When the hydrogen energy acceleration ducted fan of the aircraft hybrid power system disclosed by the embodiment works, part of air after the electric fan 6 can enter the rectifying support plate 8 through each front edge cooling air inlet 18 to cool the rectifying support plate 8, so that the rectifying support plate 8 is protected from being ablated by high-temperature fuel gas, and further is discharged through each side wall cooling hole 20 and each rear edge cooling air outlet 19, and the air flowing out through each side wall cooling hole 20 can increase the turbulence degree of the air after the electric fan 6, is beneficial to mixing with hydrogen, and the air discharged through each rear edge cooling air outlet 19 can blow flame away from the rear edge of the rectifying support plate 8 to prevent the attached surface from burning, so that the rectifying support plate 8 is further protected from being ablated by the high-temperature fuel gas.
In the hydrogen energy acceleration ducted fan of the aircraft hybrid power system disclosed in the above embodiment, the stress of the air inlet cone 3 can be transferred to the outer casing 1 through each air inlet cone strut 11, the force generated by the rotor of the motor 7 can be transferred to the casing through the bearing 13, and then transferred to the air inlet cone 3 through each casing strut 14, and the force generated by the stator of the motor 7 can be transferred to the inner casing 4 through each stator strut 12, and then transferred to the outer casing 1 through each rectifying strut 8.
Each rectifying support plate 8 is supported between the outer casing 1 and the inner casing 4 along the circumferential direction, and can transfer force between the inner casing 4 and the outer casing 1 and rectify air flow so as to enable the air flow to approach axial flow, the capability of the hydrogen energy acceleration ducted fan of the aircraft hybrid power system to generate axial thrust is increased, and the rear edge of each rectifying support plate 8 can form a backflow area so as to provide good conditions for the combustion of hydrogen. In addition, as the propagation speed of the hydrogen flame is higher, the sum of the areas of the rear edges of the rectifying support plates 8 can be designed to be 30% -50% of the flow area of the section where the rear edges of the rectifying support plates 8 are located, and the flame can be directly transferred between the rectifying support plates 8 under the area ratio, so that an additional circumferential flame connecting device is not needed.
Under the condition that the aircraft does not need to carry out supersonic flight, the temperature of the hydrogen energy acceleration duct fan outlet of the aircraft hybrid power system can be designed to be within 1000K, the hydrogen injection holes 21 on the side walls of the two sides of the rectification support plate 8 are designed, the hydrogen injection holes 21 are arranged in the range of 1/2-2/3 of the length of the rectification support plate 8 in the middle, as shown in figure 3, X/Y=1/2-2/3 is arranged, wherein X is the height of the distribution range of the hydrogen injection holes 21 on the side walls of the two sides of the rectification support plate 8, Y is the height of the rectification support plate 8, the temperature of the hydrogen energy acceleration duct fan outlet of the aircraft hybrid power system can be limited within 1000K, and ablation can not be generated on the external casing 1.
The motor 7 is connected with an external power supply through a circuit 15, and the circuit 15 is designed to run through the rectifying support plate 8, so that the scouring of high-speed air flow can be avoided.
Having thus described the technical aspects of the present application with reference to the preferred embodiments shown in the drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the related technical features without departing from the principle of the present application, and those changes or substitutions will fall within the scope of the present application.
Claims (6)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202510126234.9A CN119551182B (en) | 2025-01-27 | 2025-01-27 | Hydrogen energy accelerating duct fan of aircraft hybrid power system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202510126234.9A CN119551182B (en) | 2025-01-27 | 2025-01-27 | Hydrogen energy accelerating duct fan of aircraft hybrid power system |
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| Publication Number | Publication Date |
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| CN119551182A CN119551182A (en) | 2025-03-04 |
| CN119551182B true CN119551182B (en) | 2025-04-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202510126234.9A Active CN119551182B (en) | 2025-01-27 | 2025-01-27 | Hydrogen energy accelerating duct fan of aircraft hybrid power system |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2522912A1 (en) * | 2011-05-11 | 2012-11-14 | Alstom Technology Ltd | Flow straightener and mixer |
| CN114348243A (en) * | 2022-03-18 | 2022-04-15 | 四川凯德源科技有限公司 | Hydrogenation type multistage combustion and explosion propelling device |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7681399B2 (en) * | 2006-11-14 | 2010-03-23 | General Electric Company | Turbofan engine cowl assembly and method of operating the same |
| US8689538B2 (en) * | 2009-09-09 | 2014-04-08 | The Boeing Company | Ultra-efficient propulsor with an augmentor fan circumscribing a turbofan |
| US9212625B2 (en) * | 2010-11-19 | 2015-12-15 | Rudolph Allen SHELLEY | Hybrid gas turbine propulsion system |
| US20170218975A1 (en) * | 2016-01-29 | 2017-08-03 | United Technologies Corporation | Variable pitch fan blade arrangement for gas turbine engine |
| US11965425B2 (en) * | 2022-05-31 | 2024-04-23 | General Electric Company | Airfoil for a turbofan engine |
| US12006866B2 (en) * | 2022-07-08 | 2024-06-11 | Rtx Corporation | Hybrid electric hydrogen engine for aircraft |
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2025
- 2025-01-27 CN CN202510126234.9A patent/CN119551182B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2522912A1 (en) * | 2011-05-11 | 2012-11-14 | Alstom Technology Ltd | Flow straightener and mixer |
| CN114348243A (en) * | 2022-03-18 | 2022-04-15 | 四川凯德源科技有限公司 | Hydrogenation type multistage combustion and explosion propelling device |
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| Publication number | Publication date |
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| CN119551182A (en) | 2025-03-04 |
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