CN114562385A - Empty water integration spouts matter engine - Google Patents
Empty water integration spouts matter engine Download PDFInfo
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- CN114562385A CN114562385A CN202210275994.2A CN202210275994A CN114562385A CN 114562385 A CN114562385 A CN 114562385A CN 202210275994 A CN202210275994 A CN 202210275994A CN 114562385 A CN114562385 A CN 114562385A
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- inner duct
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- blade
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 title claims abstract description 76
- 230000010354 integration Effects 0.000 title description 2
- 238000007789 sealing Methods 0.000 claims abstract description 108
- 238000002347 injection Methods 0.000 claims abstract description 19
- 239000007924 injection Substances 0.000 claims abstract description 19
- 239000000446 fuel Substances 0.000 claims abstract description 14
- 230000007246 mechanism Effects 0.000 claims description 13
- 238000005507 spraying Methods 0.000 claims description 4
- 230000000694 effects Effects 0.000 abstract description 7
- 239000012528 membrane Substances 0.000 description 6
- 239000007921 spray Substances 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000009189 diving Effects 0.000 description 1
- 230000008595 infiltration Effects 0.000 description 1
- 238000001764 infiltration Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 230000037303 wrinkles Effects 0.000 description 1
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses an empty and water integrated fuel injection engine which comprises an inner duct and an outer duct, wherein a preposed outer duct propelling blade close to one end of an air inlet of the inner duct is arranged between the outer duct and the inner duct, a compressor blade corresponding to the outer duct propelling blade is arranged inside the inner duct, a separated connecting structure is arranged between the compressor blade and the outer duct propelling blade, and a duct sealing structure is arranged at a front opening and a rear opening of the inner duct. In the engine, the outer duct propulsion blade serving as a main structure for underwater propulsion can normally work and generate thrust when the engine propels in the air, so that dead weight is not generated, the fuel efficiency and the thrust-weight ratio during flight are greatly improved, and the increase of the flight range is facilitated. In addition, the front and back sealing of the inner duct of the invention adopts the elastic sealing film, the sealing effect is excellent, the problem that high-temperature precision parts are damaged due to water seepage is not worried about, and the inner duct can be lifted up immediately after floating up from water without waiting for the drainage of the permeated water.
Description
Technical Field
The invention belongs to the field of propulsion engines, in particular to a dual-purpose engine which can be propelled in air and water for use, and particularly relates to an air-water integrated fuel injection engine.
Background
The engines used in aircraft flying in air are generally referred to as aircraft engines, the propellant of which is air. Air is quite different from water in density and compressibility, so that an aircraft engine cannot be directly used for propelling water in water as a spray instead of air. The cross-medium propelling capability has great application value in military affairs.
CN 108891595 a discloses a medium-crossing aircraft power device adopting a medium sensing device and duct sealing, which comprises a turbofan engine jet propulsion system, and provides power for an aircraft in a jet propulsion mode; the ducted blade water jet propulsion system provides power for the aircraft in a water jet propulsion mode; the medium sensing device is used for sensing the change of the working medium; and the ducted sealing mechanism is used for opening the turbofan engine jet propulsion system and sealing the ducted blade jet propulsion system when the medium sensing device senses that the working medium is changed into air, and sealing the turbofan engine jet propulsion system and opening the ducted blade jet propulsion system when the medium sensing device senses that the working medium is changed into water.
This prior art has increased a water spray duct in ordinary turbofan jet engine's periphery, and this water spray duct is out of work when aerial, can additionally increase weight load, is unfavorable for flight state to keep. In addition, when the jet propulsion system is used in water, the sealing plates which are distributed in an annular mode are difficult to obtain a good sealing effect due to the fact that the sealing plates are used for sealing the inner duct, effective sealing of the inner duct is difficult to achieve, and the probability of damaging water seepage of the inner duct is very high, so that the jet propulsion system cannot enter water to work within a few minutes after stopping, otherwise, the high-temperature blades and other precise parts are instantly chilled once meeting water to cause structural damage, and can be submerged and propelled only after a period of time of water surface residence. Moreover, the prior art engine does not start the jet propulsion system immediately after it has risen from the water to the surface, and it also needs to wait until the water that has permeated the jet propulsion system has drained away. This prior art transition delay of the operational mode is a fatal disadvantage in wartime.
Disclosure of Invention
The invention aims to provide an air-water integrated fuel injection engine to reduce or avoid the problems.
In order to solve the technical problem, the invention provides an empty-water integrated fuel injection engine which comprises an inner duct and an outer duct, wherein a nose cone and a tail cone are respectively arranged at the front and the back of the inner duct; the device comprises an outer duct, an inner duct, a compressor blade, a separating connection structure and a duct sealing structure, wherein a front-end outer duct propelling blade close to one end of an air inlet of the inner duct is arranged between the outer duct and the inner duct; the separated connecting structure is used for connecting the compressor blades and the outer duct propelling blades when the blades are propelled in the air and driving the compressor blades and the outer duct propelling blades to move together through the turbine shaft; when the impeller needs to be propelled in water, the separated connecting structure enables the blades of the air compressor to be separated from the propelling blades of the outer duct, the internal rotating part of the inner duct stops working, and the propelling blades of the outer duct are driven independently through the electromagnetic coil.
Preferably, the duct sealing structure comprises a plurality of sealing plates which are respectively arranged around the outer sides of the nose cone and the tail cone in a circle, one ends of the sealing plates, which are close to the central shaft of the engine, are respectively hinged to the nose cone and the tail cone, the other ends of the sealing plates are respectively propped against the inner wall surfaces of the front opening and the rear opening of the inner duct through telescopic rods, and the outer sides of the sealing plates are hermetically wrapped with a layer of elastic sealing film; the sealing plate is exposed out of the inner duct when folded, abuts against the inner wall surfaces of the front opening and the rear opening of the inner duct when unfolded, and unfolds the elastic sealing film on the outer side to integrally seal the front opening and the rear opening of the inner duct through the elastic sealing film.
Preferably, an elastic pull film is arranged in a gap between every two adjacent sealing plates, one side of each elastic pull film is connected with the elastic sealing film, and the other side of each elastic pull film is fixedly connected with the surfaces of the nose cone and the tail cone respectively.
Preferably, the separated connecting structure comprises a plurality of sliding tiles which are connected into a ring shape and are arranged in a first annular gap on the side wall of the inner duct in a sealing manner, and a first annular bearing is arranged between each sliding tile and the first annular gap; each sliding tile is fixedly connected with the top of the compressor blade, and the compressor blade drives the sliding tiles to move in the first annular gap when driven by the turbine shaft to rotate.
Preferably, the inside of every slip tile all is provided with flexible tenon, and flexible tenon passes through the inside electromagnetic mechanism that sets up of slip tile and drives its flexible.
Preferably, the top of each outer duct propulsion blade is fixedly connected with a permanent magnet slip sheet, and a plurality of permanent magnet slip sheets are connected with one another to be annularly arranged in a second annular gap on the side wall of the outer duct to move; the bottom of the outer duct propulsion blade is provided with a socket corresponding to the telescopic tenon.
Preferably, an annular slide rail is arranged in the second annular gap, the annular slide rail is fixedly connected in the second annular gap, and the outer duct parts on two sides of the second annular gap are connected into a whole; a plurality of electromagnetic coils are arranged above the annular slide rail, the permanent magnet slide sheet is slidably clamped below the annular slide rail, and a second annular bearing is arranged between the permanent magnet slide sheet and the annular slide rail.
When the air-water integrated injection engine disclosed by the invention is propelled in air, the front opening and the rear opening of the inner duct can be opened through the duct sealing structure, and the compressor blades and the outer duct propelling blades are connected through the separated connecting structure, so that the air can be pushed to generate thrust similar to a front fan aero-engine. When the water enters the water for propulsion, the inner duct is sealed through the duct sealing structure, the internal mechanism of the inner duct stops working, and the blades of the movable outer duct can drive the water to generate thrust through the electromagnetic coil. The outer duct propulsion blade serving as the main structure of underwater propulsion can normally work and generate thrust under the drive of the turbine shaft during air propulsion, so that dead weight is not formed, the fuel efficiency and thrust-weight ratio during flight are greatly improved, and the flight range is favorably increased. In addition, the front and back sealing of the inner duct of the invention adopts the elastic sealing film, the sealing effect is excellent, the problem that high-temperature precision parts are damaged due to water seepage is not worried about, and the inner duct can be lifted up immediately after floating up from water without waiting for the drainage of the permeated water. The vehicle equipped with the engine of the invention can repeatedly enter underwater from the air or lift off underwater, and can be reused.
Drawings
The drawings are only for purposes of illustrating and explaining the present invention and are not to be construed as limiting the scope of the present invention.
Fig. 1 is a partially broken-away schematic view showing an open state of an inner duct of an air-water integrated injection engine according to an embodiment of the invention.
Fig. 2 is a partially cut-away schematic view showing a sealing state of an inner duct of an air-water integrated injection engine according to another embodiment of the invention.
Fig. 3 is a schematic cross-sectional view of an empty-water integrated injection engine according to still another embodiment of the present invention, in which the upper half shows an open state of the inner duct and the lower half shows a sealed state of the inner duct.
Figure 4 shows an enlarged partial cross-sectional view of a ducted seal structure according to an embodiment of the present invention.
FIG. 5 shows an enlarged partial cross-sectional view of an elastic sealing membrane according to an embodiment of the invention.
Fig. 6 is an exploded perspective view showing a breakaway connection structure according to an embodiment of the present invention.
Detailed Description
In order to more clearly understand the technical features, objects, and effects of the present invention, embodiments of the present invention will now be described with reference to the accompanying drawings. Wherein like parts are given like reference numerals.
On the basis of the prior jet aircraft engine, the invention provides an air-water integrated injection engine with an improved structure, which can be propelled in air and water for use, as shown in figures 1-3. In which figure 1 shows a schematic view from the front of the engine; FIG. 2 shows a schematic view from the rear of the engine; figure 3 shows, for clarity, the upper and lower halves in two different positions, respectively, when propelled in the air and in the water.
As shown in the figure, the empty-water integrated injection engine comprises an outer duct 1 and an inner duct 2, wherein a nose cone 21 and a tail cone 22 for guiding flow are respectively arranged at the front and the rear of the inner duct 2, and a compressor, a combustion chamber, a turbine and other conventional structures are sequentially arranged in the inner duct 2 from front to rear (see figure 3).
Different from the existing jet aero-engine, the empty-water integrated fuel injection engine is characterized in that a preposed outer duct propulsion blade 3 close to one end of an air inlet of an inner duct 2 is arranged between the outer duct 1 and the inner duct 2, a compressor blade 4 corresponding to the outer duct propulsion blade 3 is arranged inside the inner duct 2, a separated connecting structure 7 is arranged between the compressor blade 4 and the outer duct propulsion blade 3, and a duct sealing structure 6 is arranged at a front opening and a rear opening of the inner duct 2 (which will be further explained later). The separated connecting structure 7 is used for connecting the compressor blades 4 and the outer duct propulsion blades 3 when the blades are propelled in air, and the compressor blades 4 and the outer duct propulsion blades 3 are driven to move together through a turbine shaft 9 (figures 3 and 6); when the underwater propeller needs to be propelled, the separating connection structure 7 separates the compressor blades 4 from the outer duct propelling blades 3, the internal rotating parts of the inner duct 2 stop working (including the compressor blades 4), and the outer duct propelling blades 3 are independently driven by the electromagnetic coil 5 (which will be further described later). In the embodiment shown in fig. 3, the compressor blades 4 are connected to a high-pressure turbine via a turbine shaft 9, and a low-pressure turbine and the like may be arranged behind the high-pressure turbine.
It should be noted that some conventional jet aircraft engines do not have an outer duct, and even if an outer duct is provided, the inner portion of the outer duct does not have rotatable propeller blades because power cannot be transmitted to the propeller blades in the outer duct. The inventive outduct propulsion blades 3 are therefore not structural components of the prior art, but are structural components added to the prior art. Thus, the split connection 7 is also an improved structure proposed by the present invention for the newly added outer duct propulsion blades 3.
According to the structure, the basic working principle of the air-water integrated spraying engine is as follows: when the aircraft is propelled in the air, the front opening and the rear opening of the inner duct 2 are opened through the duct sealing structure 6, the compressor blades 4 and the outer duct propelling blades 3 are connected through the separating type connecting structure 7, and the compressor blades 4 drive the outer duct propelling blades 3 to rotate together, so that the aircraft can propel the air to generate thrust similarly to a front fan aircraft engine. When the water enters the water for propulsion, the inner duct 2 is sealed through the duct sealing structure 6, the internal mechanism of the inner duct 2 stops working, the compressor blades 4 and the outer duct propulsion blades 3 are disconnected through the separated connection structure 7, and the outer duct blades 3 are driven by the electromagnetic coil 5 to generate thrust on the water.
In order to realize the above functions, the air-water integrated fuel injection engine of the present invention needs to solve two main problems, the first is the front and rear sealing problem of the inner duct 2, and the second is the design problem of the separated connection structure, which will be described below one by one.
The duct sealing structure 6 of the inner duct 2 is as shown in fig. 4-5, and referring to fig. 1-3, the duct sealing structure 6 of the invention comprises a plurality of sealing plates 61 respectively arranged around the outer sides of the nose cone 21 and the tail cone 22 in a circle, one ends of the sealing plates 61 close to the central axis of the engine are respectively hinged on the nose cone 21 and the tail cone 22, the other ends of the sealing plates 61 can be respectively propped against the inner wall surface of the front opening and the rear opening of the inner duct 2 through telescopic rods 62, and the outer sides of the sealing plates 61 are sealed and wrapped with a layer of elastic sealing film 63. In fig. 1, 2 and 4, the external appearance of the sealing plate 61 needs to be shown, and the elastic sealing film 63 outside the sealing plate 61 is not shown. The sealing plate 61 is similar to a skeleton of an umbrella, and exposes the inner duct 2 when folded, and the outer edge of the sealing plate props against the inner wall surfaces of the front opening and the rear opening of the inner duct 2 when expanded, and simultaneously expands the elastic sealing film 63 at the outer side, so that the front opening and the rear opening of the inner duct 2 are integrally sealed through the elastic sealing film 63.
The key of the fore-and-aft sealing of the endoprosthesis 2 is that an elastic sealing membrane 63 is hermetically wrapped on the outer side of a sealing plate 61 in the form of an umbrella framework, the front edge and the rear edge of the elastic sealing membrane 63 are respectively connected with the surfaces of a nose cone 21 and a tail cone 22 in a sealing mode, and the sealing plate 61 is integrally and hermetically wrapped by the elastic sealing membrane 63. The sealing plate 61 is entirely separated from the outside by the elastic sealing film 63 both in the air and in water, and the telescopic rod 62 and the hydraulic drive mechanism inside the sealing plate 61 are free from the problem of water entering inside. After the sealing plate 61 is expanded, the middle of the elastic sealing film 63 is expanded and arched by the sealing plate 61, and actually two layers of sealing films are formed (as shown in fig. 3), so that the waterproof performance is better. After the elastic sealing film 63 is propped by the sealing plate 61, the middle arched part is propped against the inner wall surface of the front opening and the rear opening of the inner duct 2 by the sealing plate 61, the elastic sealing film 63 is squeezed between the end part of the sealing plate 61 and the inner duct 2 to form a layer of elastic sealing gasket, so that the gap between the sealing plate 61 and the inner duct 2 can be further filled, and the waterproof effect is further improved.
Further, as shown in fig. 3-4, an elastic pulling film 64 is disposed in the gap between two adjacent sealing plates 61, one side of each elastic pulling film 64 is connected to the elastic sealing film 63, and the other side is fixedly connected to the surface of the nose cone 21 and the surface of the tail cone 22. One function of the elastic pulling film 64 is that when the sealing plate 61 is folded, the elastic pulling film 64 can pull the elastic sealing film 63 into the space surrounded by the sealing plate 61 from the gap of the adjacent sealing plate 61, so as to avoid the uncontrollable surface wrinkles from blocking the sealing plate 61 and preventing the sealing plate from folding when the elastic sealing film 63 is folded. The elastic pull film 64 has another function that when the engine is propelled in the air, the inner duct 2 generates high-speed airflow, great pressure is formed on the surface of the elastic sealing film 63, the elastic sealing film 63 can be torn by the pressure of the airflow under the high-speed airflow, and therefore the elastic pull film 64 can firmly pull the elastic sealing film 63 to avoid breakage and damage under the action of the high-speed airflow. In a preferred embodiment, the elastic modulus of the elastic pull film 64 needs to be greater than the elastic modulus of the elastic sealing film 63.
The separate connection structure 7 is shown in fig. 6 and referring to fig. 1-3, the separate connection structure 7 of the air-water integrated injection engine of the present invention comprises a plurality of sliding tiles 71 connected in a ring shape and hermetically disposed in a first annular gap 23 on the side wall of the inner duct 2, and a first annular bearing 72 is disposed between the sliding tiles 71 and the first annular gap 23. Each sliding tile 71 is fixedly connected with the top of the compressor blade 4, and when the compressor blade 4 is driven by the turbine shaft 9 to rotate, the sliding tile 71 is driven to move in the first annular notch 23. In order to avoid water seepage, the first annular bearing 72 is preferably a sealed bearing, and the adjacent sliding tiles 71 are connected in a sealing manner, so that the sliding tiles 71 can move in the first annular gap 23, and meanwhile, no leakage can be formed at the position of the first annular gap 23. The structural parts of the endoprosthesis 2 on both sides of the first annular gap 23 can be fixedly connected to the outer endoprosthesis 1 by means of supporting elements.
The inside of every slip tile 71 all is provided with flexible tenon 73, and flexible tenon 73 can drive its flexible through the inside electromagnetic mechanism that sets up of slip tile 71.
Similarly, a permanent magnet sliding vane 31 is fixedly connected to the top of each bypass propulsion blade 3, and a plurality of permanent magnet sliding vanes 31 are connected to each other to move in a second annular notch 33 arranged on the side wall of the bypass 1 in an annular manner, that is, the permanent magnet sliding vanes 31 connected in an annular manner can move in the second notch 33. The bottom of the outtake propulsion blades 3 is provided with a socket (not shown in the figures) corresponding to the telescopic tenon 73.
When it is desired to connect the compressor blades 4 and the bypass propeller blades 3 together, they are first aligned by the control means and then the expansion tenons 73 are driven by the electromagnetic means inside the sliding tiles 71 to extend and insert into the sockets at the bottom of the bypass propeller blades 3. When the compressor blade 4 and the bypass propelling blade 3 need to be disconnected, the telescopic tenon 73 is driven to retract.
Further, an annular slide rail 8 is arranged in the second annular gap 33, the annular slide rail 8 is fixedly connected in the second annular gap 33 through a connecting piece such as a bolt, and the outer duct parts at two sides of the second annular gap 33 are connected into a whole. A plurality of electromagnetic coils 5 are arranged above the annular slide rail 8, the permanent magnet slide sheet 31 is slidably clamped below the annular slide rail 8, and a second annular bearing 32 is arranged between the permanent magnet slide sheet 31 and the annular slide rail 8. After the compressor blades 4 and the outer duct propulsion blades 3 are disconnected, the permanent magnet sliding blades 31 can be driven to move through the electromagnetic coils 5 arranged on the outer sides of the annular sliding rails 8, and then the outer duct propulsion blades 3 are driven to rotate independently.
The operation of an aircraft equipped with an air-water integrated jet engine according to the invention will be further described with reference to the accompanying drawings.
When the aircraft needs to enter the air from the underwater for flying, the aircraft floats to the water surface firstly, so that the engine is separated from the contact with the water, then the duct sealing structure 6 is driven to open the inner duct 2, the compressor blades 4 and the outer duct propelling blades 3 need to be connected together through the separated connecting structure 7 to rotate as described above, so that the air-water integrated mass spraying engine pushes the air to generate thrust like a front fan aircraft engine, and the aircraft slides and lifts from the water surface. When underwater diving needs to be carried out from the air, the engine can be directly stopped in the air, then the duct sealing structure 6 is driven to seal the inner duct 2, the compressor blades 4 and the outer duct propelling blades 3 need to be disconnected through the separated connecting structure 7 as described above, at the moment, the aircraft can directly drill into the water and immediately fill water like a submarine to dive, and the outer duct propelling blades 3 generate thrust to the water under the independent driving of the electromagnetic coils 5.
The operation mode of the invention has the advantages that when the aircraft propels in the air, the outer duct propulsion blades 3 which are used as the main structure of underwater propulsion can also work normally under the drive of the turbine shaft 9 and generate thrust, so dead weight is not formed, the fuel efficiency and thrust-weight ratio during flight are greatly improved, and the flight range is favorably increased. In addition, the fore and aft sealing of the inner duct 2 of the present invention employs the elastic sealing film 63, which is excellent in sealing effect, does not have a problem of damaging high-temperature precision parts due to water infiltration, and can be operated to lift up immediately after floating up from water, since a small amount of infiltrated water is rapidly vaporized and discharged during the engine ignition process, and thus there is no need to wait for the infiltrated water to be completely discharged. Further, a vehicle equipped with the engine of the present invention can be repeatedly airborne into the water, or lifted from the water, and can be reused.
Of course, since the sealing effect of the elastic sealing membrane 63 of the present invention is too good, when the propulsion from the air into the water is needed, the operation problem of the internal mechanism of the culvert 2 needs to be considered, that is, if the culvert 2 is sealed and the internal mechanism of the culvert 2 is still rotating, under the action of the compressor, a huge suction force is formed at the air inlet position of the culvert 2, and a huge thrust force is formed at the air outlet position, and the two forces can damage the elastic sealing membrane 63 and tear it. In order to avoid this, the air-water integrated injection engine of the present invention needs to be further provided with a brake mechanism (not shown in the drawings) for stopping the rotation of the internal mechanism of the inner duct 2. By arranging the brake mechanism for stopping the internal mechanism of the inner duct 2 and the elastic sealing film 63, the aircraft provided with the engine can directly cross over the water-air medium without falling on the water surface to wait for internal cooling or emptying internal water seepage, thereby greatly improving the capability of avoiding and tracking the aircraft.
It should be appreciated by those of skill in the art that while the present invention has been described in terms of several embodiments, not every embodiment includes only a single embodiment. The description is given for clearness of understanding only, and reference should be made to the fact that the description is made to the preferred embodiment and that the technical solutions referred to in the embodiments are regarded as being combinable with each other in order to understand the scope of the present invention.
The above description is only an exemplary embodiment of the present invention, and is not intended to limit the scope of the present invention. Any equivalent alterations, modifications and combinations can be made by those skilled in the art without departing from the spirit and principles of the invention.
Claims (7)
1. An empty-water integrated mass-spraying engine comprises an inner duct and an outer duct, wherein a nose cone and a tail cone are respectively arranged at the front and the rear of the inner duct; the device is characterized in that a preposed outer duct propelling blade close to one end of an air inlet of an inner duct is arranged between the outer duct and the inner duct, a compressor blade corresponding to the outer duct propelling blade is arranged inside the inner duct, a separated connecting structure is arranged between the compressor blade and the outer duct propelling blade, and a duct sealing structure is arranged at the front opening and the rear opening of the inner duct; the separated connecting structure is used for connecting the compressor blades and the outer duct propelling blades when the blades are propelled in the air and driving the compressor blades and the outer duct propelling blades to move together through the turbine shaft; when the impeller needs to be propelled in water, the separated connecting structure enables the blades of the air compressor to be separated from the propelling blades of the outer duct, the internal rotating part of the inner duct stops working, and the propelling blades of the outer duct are driven independently through the electromagnetic coil.
2. The air-water integrated fuel injection engine according to claim 1, wherein the duct sealing structure comprises a plurality of sealing plates which are respectively arranged around the outer sides of the nose cone and the tail cone in a circle, one ends of the sealing plates, which are close to the central shaft of the engine, are respectively hinged to the nose cone and the tail cone, the other ends of the sealing plates are respectively propped against the inner wall surfaces of the front opening and the rear opening of the inner duct through telescopic rods, and the outer sides of the sealing plates are hermetically wrapped with a layer of elastic sealing film; the sealing plate is exposed out of the inner duct when folded, abuts against the inner wall surfaces of the front opening and the rear opening of the inner duct when unfolded, and unfolds the elastic sealing film on the outer side to integrally seal the front opening and the rear opening of the inner duct through the elastic sealing film.
3. The air-water integrated quality spraying engine as claimed in claim 2, wherein an elastic pulling film is arranged in a gap between two adjacent sealing plates, one side of each elastic pulling film is connected with an elastic sealing film, and the other side of each elastic pulling film is fixedly connected with the surfaces of the nose cone and the tail cone respectively.
4. The air-water integrated fuel injection engine according to claim 1, wherein the split connection structure comprises a plurality of sliding tiles connected in an annular sealing manner in a first annular gap formed in the side wall of the inner duct, and a first annular bearing is arranged between the sliding tiles and the first annular gap; each sliding tile is fixedly connected with the top of the compressor blade, and the compressor blade drives the sliding tiles to move in the first annular gap when driven by the turbine shaft to rotate.
5. The air-water integrated fuel injection engine as claimed in claim 4, wherein each sliding tile is provided with a retractable tenon inside, and the retractable tenon drives the sliding tile to retract through an electromagnetic mechanism arranged inside the sliding tile.
6. The air-water integrated fuel injection engine as claimed in claim 5, wherein a permanent magnet sliding vane is fixedly connected to the top of each outer duct propulsion blade, and a plurality of permanent magnet sliding vanes are connected with each other to move in a second annular gap annularly arranged on the side wall of the outer duct; the bottom of the outer duct propulsion blade is provided with a socket corresponding to the telescopic tenon.
7. The air-water integrated fuel injection engine as claimed in claim 6, wherein the second annular gap is provided with an annular slide rail, the annular slide rail is fixedly connected in the second annular gap and connects the outer duct parts at two sides of the second annular gap into a whole; a plurality of electromagnetic coils are arranged above the annular slide rail, the permanent magnet slide sheet is slidably clamped below the annular slide rail, and a second annular bearing is arranged between the permanent magnet slide sheet and the annular slide rail.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210275994.2A CN114562385B (en) | 2022-03-21 | 2022-03-21 | Air-water integrated spray engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210275994.2A CN114562385B (en) | 2022-03-21 | 2022-03-21 | Air-water integrated spray engine |
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| CN114562385A true CN114562385A (en) | 2022-05-31 |
| CN114562385B CN114562385B (en) | 2023-10-31 |
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2022
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