CN116357475A - Water-air dual-purpose propulsion system, aircraft thereof and control method - Google Patents
Water-air dual-purpose propulsion system, aircraft thereof and control method Download PDFInfo
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- CN116357475A CN116357475A CN202310306826.XA CN202310306826A CN116357475A CN 116357475 A CN116357475 A CN 116357475A CN 202310306826 A CN202310306826 A CN 202310306826A CN 116357475 A CN116357475 A CN 116357475A
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- turbine engine
- water
- water reaction
- combustion chamber
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/16—Composite ram-jet/turbo-jet engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
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- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The application belongs to the technical field of aircraft propulsion system design, and particularly relates to a water-air dual-purpose propulsion system, an aircraft thereof and a control method, wherein the water-air dual-purpose propulsion system comprises: a turbine engine; the water reaction storage cone is arranged at the front end of the air inlet channel of the turbine engine, is connected to the front end of the rotor shaft of the turbine engine, and is filled with metal fuel; the water reaction combustion chamber is arranged at the rear end of the nozzle of the turbine engine, is connected to the rear end of the rotor shaft of the turbine engine and is provided with a water inlet; the water reaction metal conduit penetrates through the rotor shaft of the turbine engine and is communicated with the water reaction storage cone and the water reaction combustion chamber; the water reaction spray pipe is connected to the rear end of the water reaction combustion chamber.
Description
Technical Field
The application belongs to the technical field of aircraft propulsion system design, and particularly relates to a water-air dual-purpose propulsion system, an aircraft thereof and a control method.
Background
With the lifting of the demand, the aircraft is required to fly in the air, perform aerial operation, and also navigate underwater, and perform underwater operation, however, currently, the propulsion system of the aircraft can only provide thrust in the air for the aerial flight of the aircraft, and it is difficult to provide thrust in the underwater for the underwater navigation of the aircraft.
The present application has been made in view of the existence of the above-mentioned technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present invention, which is not necessarily prior art to the present application, and should not be used for evaluating the novelty and the creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide a marine and aeronautical propulsion system, an aircraft thereof and a method of maneuvering, which overcome or mitigate the technical drawbacks of at least one aspect of the known art.
The technical scheme of the application is as follows:
in one aspect, a marine and aeronautical propulsion system is provided, comprising:
a turbine engine;
the water reaction storage cone is arranged at the front end of the air inlet channel of the turbine engine, is connected to the front end of the rotor shaft of the turbine engine, and is filled with metal fuel;
the water reaction combustion chamber is arranged at the rear end of the nozzle of the turbine engine, is connected to the rear end of the rotor shaft of the turbine engine and is provided with a water inlet;
the water reaction metal conduit penetrates through the rotor shaft of the turbine engine and is communicated with the water reaction storage cone and the water reaction combustion chamber;
the water reaction spray pipe is connected to the rear end of the water reaction combustion chamber.
According to at least one embodiment of the present application, in the above-mentioned marine and air propulsion system, the turbine engine includes a compressor, a main combustion chamber, and a turbine, wherein the compressor and the turbine adopt a monolithic rotor structure.
According to at least one embodiment of the present application, in the above-mentioned marine and air propulsion system, the method further includes:
the stamping case is sleeved on the periphery of the turbine engine case;
the punching combustion chamber is arranged between the turbine engine casings;
the punching spray pipe is connected to the rear end of the punching machine box and is positioned at the periphery of the water reaction spray pipe.
According to at least one embodiment of the present application, in the above-mentioned water-air propulsion system, the front end of the punching case extends to the periphery of the water reaction storage cone;
the water-air propulsion system further comprises:
the duct adjusting valve plate is arranged on the inner side of the stamping case and is hinged to the front end of the air inlet channel of the turbine engine.
Another aspect provides an aircraft equipped with a marine propulsion system as described above.
A further aspect provides a method of maneuvering an aircraft, wherein the aircraft is an aircraft as described above, comprising:
when the aircraft flies from the air to the underwater navigation, the turbine engine and the stamping combustion chamber are closed, after entering the water, the water reaction metal conduit is opened, so that metal fuel in the water reaction storage cone can enter the water reaction combustion chamber to react with water entering the water reaction combustion chamber through the water inlet, the water is sprayed out through the water reaction spray pipe to provide thrust for the underwater navigation of the aircraft, and the size of the thrust is adjusted by controlling the amount of the metal fuel entering the water reaction combustion chamber, so that the turbine engine runs in the windmill under the water;
when the aircraft flies from underwater navigation to air, the water reaction metal conduit is closed, after the water surface is flushed, the turbine engine and the ram combustion chamber are started, thrust is provided for the air flight of the aircraft, and the air quantity entering the turbine engine and the ram combustion chamber is regulated by the bypass regulating valve plate.
Drawings
FIG. 1 is a schematic illustration of a marine and air propulsion system provided in an embodiment of the present application;
wherein:
1-a turbine engine; 2-water reaction storage cone; 3-water reaction combustion chamber; 4-water reactive metal conduit; 5-water reaction nozzle; 6-a compressor; 7-a main combustion chamber; 8-a turbine; 9-stamping the case; 10-ram combustion chamber; 11-punching the spray pipe; 12-a bypass regulating valve plate.
For the purpose of better illustrating the present embodiments, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the actual product dimensions, and furthermore, the drawings are for illustrative purposes only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solution of the present application and the advantages thereof more apparent, the technical solution of the present application will be more fully described in detail below 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, not for limitation of the present application. It should be noted that, for convenience of description, only the portion relevant to the present application is shown in the drawings, and other relevant portions may refer to a general design, and without conflict, the embodiments and technical features in the embodiments may be combined with each other to obtain new embodiments.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of this application should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in this description are merely used to indicate relative directions or positional relationships, and do not imply that a device or element must have a particular orientation, be configured and operated in a particular orientation, and that the relative positional relationships may be changed when the absolute position of the object being described is changed, and thus should not be construed as limiting the present application. The terms "first," "second," "third," and the like, as used in the description herein, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the invention are not to be construed as limited in number to the precise location of at least one. As used in this description, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term and that is listed after the term and its equivalents, without excluding other elements or articles.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description herein are to be construed broadly and refer to either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The present application is described in further detail below in conjunction with fig. 1.
In one aspect, a marine and aeronautical propulsion system is provided, comprising:
a turbine engine 1;
the water reaction storage cone 2 is arranged at the front end of an air inlet channel of the turbine engine 1, is connected to the front end of a rotor shaft of the turbine engine 1, and is filled with metal fuel;
the water reaction combustion chamber 3 is arranged at the rear end of the nozzle of the turbine engine 1, is connected to the rear end of the rotor shaft of the turbine engine 1 and is provided with a water inlet;
the water reaction metal conduit 4 is arranged to penetrate through the rotor shaft of the turbine engine 1, is communicated with the water reaction storage cone 2 and the water reaction combustion chamber 3, and can be provided with corresponding valves thereon for opening and closing;
and the water reaction spray pipe 5 is connected with the rear end of the water reaction combustion chamber 3.
As for the water-air propulsion system disclosed in the above embodiment, it can be understood by those skilled in the art that the design takes the turbine engine 1 as the core, and integrates thereon a water reaction engine which is mainly composed of a water reaction storage cone 2, a water reaction combustion chamber 3, a water reaction metal conduit 4 and a water reaction spray pipe 5, so that the structure is compact, and the water-air propulsion system can provide thrust for the aircraft equipped with the water-air propulsion system to navigate in the air and underwater, and is specifically as follows:
when the aircraft sails underwater, the turbine engine 1 is closed, the water reaction metal conduit 4 is opened, so that metal fuel in the water reaction storage cone 2 can enter the water reaction combustion chamber 3 to react with water entering the water reaction combustion chamber 3 through the water inlet, the water reaction fuel is sprayed out through the water reaction spray pipe 5 to provide thrust for the underwater navigation of the aircraft, namely the thrust is provided by the water reaction engine, the amount of the metal fuel entering the water reaction combustion chamber 3 can be controlled, the size of the thrust is regulated, and the turbine engine 1 runs in a windmill underwater;
when the aircraft flies in the air, the water reaction metal conduit 4 is closed, the turbine engine 1 is started, and thrust is provided for the flying of the aircraft in the air.
In some alternative embodiments, in the above-mentioned water-air propulsion system, the turbine engine 1 includes the compressor 6, the main combustion chamber 7, and the turbine 8, where the compressor 6 and the turbine 8 adopt an integral rotor structure to enhance the sealing performance.
In some alternative embodiments, the above-mentioned water-air propulsion system further comprises:
the punching machine case 9 is sleeved on the periphery of the machine case of the turbine engine 1;
a ramjet combustion chamber 10 provided between the cases of the turbine engine 1 and the ramjet case 9;
the punching jet pipe 11 is connected to the rear end of the punching machine case 9 and is positioned on the periphery of the water reaction jet pipe 5.
As for the water-air propulsion system disclosed in the above embodiment, it can be understood by those skilled in the art that the design uses the turbine engine 1 as a core, and further integrates the ram air compressor using the ram casing 9, the ram combustion chamber 10 and the ram nozzle 11 as main components on the basis of integrating the water reaction engine, so that the structure is compact, the aircraft equipped with the water-air propulsion system closes the ram combustion chamber 10 during underwater navigation, i.e. closes the ram air compressor, does not work when not ignited, only serves as a duct, and starts the ram combustion chamber 10 during air flight, i.e. starts the ram air compressor, and the turbine engine 1 and the ram air compressor jointly provide thrust for the aircraft in the air flight.
In some alternative embodiments, in the above-mentioned water-air propulsion system, the front end of the punching case 9 extends to the periphery of the water reaction storage cone 2;
the water-air propulsion system further comprises:
the duct adjusting valve plate 12 is arranged at the inner side of the stamping case 9 and hinged at the front end of an air inlet channel of the turbine engine 1, a corresponding actuating mechanism can be designed to drive the duct valve plate 12, so that the duct valve plate 12 is expanded or contracted, the relative air inlet area of the turbine engine 1 and the stamping combustion chamber 10 can be changed, namely the duct ratio of the turbine engine 1 and the stamping compressor is changed, and the water-air dual-purpose propulsion system is adjusted to be capable of being efficiently adapted to various flight working conditions of an aircraft.
Another aspect provides an aircraft equipped with a marine propulsion system as described above.
For the aircraft disclosed in the foregoing embodiments, those skilled in the art will understand that the main improvement lies in the configuration of the above-mentioned aero-water propulsion system, and the description is simpler, and specific relevant points can be referred to the description of the above-mentioned aero-water propulsion system, and the technical effects of the invention can also be referred to the technical effects of the relevant parts of the above-mentioned aero-water propulsion system, which are not described herein again.
A further aspect provides a method of maneuvering an aircraft, wherein the aircraft is an aircraft as described above, comprising:
when the aircraft flies from the air to the underwater navigation, the turbine engine 1 and the stamping combustion chamber 10 are closed, after entering the underwater, the water reaction metal conduit 4 is opened, so that the metal fuel in the water reaction storage cone 2 can enter the water reaction combustion chamber 3 to react with water entering the water reaction combustion chamber 3 through the water inlet, the water is sprayed out through the water reaction spray pipe 5 to provide thrust for the underwater navigation of the aircraft, and the amount of the metal fuel entering the water reaction combustion chamber 3 is controlled to adjust the amount of the thrust, so that the turbine engine 1 runs in a windmill underwater;
when the aircraft flies from underwater navigation to air, the water reaction metal conduit 4 is closed, after the water surface is flushed, the turbine engine 1 and the ram combustion chamber 10 are started, thrust is provided for the air flight of the aircraft, and the air quantity entering the turbine engine 1 and the ram combustion chamber 10 is regulated by the bypass regulating valve plate 12.
For the method for operating an aircraft disclosed in the foregoing embodiment, it will be understood by those skilled in the art that the difference between the operations is that the aircraft is equipped with the above-mentioned amphibious propulsion system, and the description is simpler, and specific relevant points can be referred to the description of the above-mentioned amphibious propulsion system, and the technical effects of the above-mentioned related parts of the above-mentioned amphibious propulsion system are referred to, which are not repeated herein.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
Having thus described the technical aspects of the present application with reference to the preferred embodiments illustrated in the accompanying 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 relevant technical features without departing from the principles of the present application, and those changes or substitutions will now fall within the scope of the present application.
Claims (6)
1. A marine and air propulsion system comprising:
a turbine engine (1);
the water reaction storage cone (2) is arranged at the front end of an air inlet channel of the turbine engine (1), is connected to the front end of a rotor shaft of the turbine engine (1), and is filled with metal fuel;
the water reaction combustion chamber (3) is arranged at the rear end of a nozzle of the turbine engine (1), is connected to the rear end of a rotor shaft of the turbine engine (1), and is provided with a water inlet;
a water reaction metal conduit (4) which penetrates through the rotor shaft of the turbine engine (1) and is communicated with the water reaction storage cone (2) and the water reaction combustion chamber (3);
the water reaction spray pipe (5) is connected with the rear end of the water reaction combustion chamber (3).
2. A marine and air propulsion system as claimed in claim 1, wherein,
the turbine engine (1) comprises a compressor (6), a main combustion chamber (7) and a turbine (8), wherein the compressor (6) and the turbine (8) adopt an integral rotor structure.
3. The marine and air propulsion system of claim 2, further comprising:
the punching machine case (9) is sleeved on the periphery of the machine case of the turbine engine (1);
a ramjet combustion chamber (10) provided between the cases of the turbine engine (1) and the ramjet case (9);
the punching spray pipe (11) is connected to the rear end of the punching machine box (9) and is positioned at the periphery of the water reaction spray pipe (5).
4. A marine and air propulsion system as claimed in claim 3 wherein,
the front end of the punching machine box (9) extends to the periphery of the water reaction storage cone (2);
the water-air propulsion system further comprises:
the duct adjusting valve plate (12) is arranged on the inner side of the stamping case (9) and is hinged to the front end of an air inlet channel of the turbine engine (1).
5. An aircraft equipped with a marine and air propulsion system as claimed in claim 4.
6. A method of maneuvering an aircraft, wherein the aircraft is the aircraft of claim 5, comprising:
when the aircraft flies from the air to the underwater navigation, the turbine engine (1) and the stamping combustion chamber (10) are closed, after entering the underwater, the water reaction metal conduit (4) is opened, so that metal fuel in the water reaction storage cone (2) can enter the water reaction combustion chamber (3) to react with water entering the water reaction combustion chamber (3) through the water inlet, thrust is provided for the underwater navigation of the aircraft through the water reaction spray pipe (5), the amount of the metal fuel entering the water reaction combustion chamber (3) is controlled, the thrust is regulated, and the turbine engine (1) performs windmill operation under the water;
when the aircraft flies from underwater navigation to air, the water reaction metal conduit (4) is closed, after the aircraft rushes out of the water surface, the turbine engine (1) and the ram combustion chamber (10) are started, thrust is provided for the air flight of the aircraft, and the air quantity entering the turbine engine (1) and the ram combustion chamber (10) is regulated by the ducted regulating valve plate (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310306826.XA CN116357475A (en) | 2023-03-27 | 2023-03-27 | Water-air dual-purpose propulsion system, aircraft thereof and control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310306826.XA CN116357475A (en) | 2023-03-27 | 2023-03-27 | Water-air dual-purpose propulsion system, aircraft thereof and control method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116357475A true CN116357475A (en) | 2023-06-30 |
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ID=86929988
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310306826.XA Pending CN116357475A (en) | 2023-03-27 | 2023-03-27 | Water-air dual-purpose propulsion system, aircraft thereof and control method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116357475A (en) |
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2023
- 2023-03-27 CN CN202310306826.XA patent/CN116357475A/en active Pending
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