CN114562385B - Air-water integrated spray engine - Google Patents
Air-water integrated spray engine Download PDFInfo
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- CN114562385B CN114562385B CN202210275994.2A CN202210275994A CN114562385B CN 114562385 B CN114562385 B CN 114562385B CN 202210275994 A CN202210275994 A CN 202210275994A CN 114562385 B CN114562385 B CN 114562385B
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- duct
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- sealing
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- propulsion
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 title claims abstract description 72
- 239000007921 spray Substances 0.000 title claims abstract description 22
- 238000007789 sealing Methods 0.000 claims abstract description 106
- 238000000926 separation method Methods 0.000 claims abstract description 8
- 230000007246 mechanism Effects 0.000 claims description 16
- 230000000694 effects Effects 0.000 abstract description 7
- 239000000446 fuel Substances 0.000 abstract description 3
- 239000012528 membrane Substances 0.000 description 4
- 230000009471 action Effects 0.000 description 2
- 238000005507 spraying Methods 0.000 description 2
- 230000004075 alteration 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
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
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 air-water integrated spray engine, which comprises an inner duct and an outer duct, wherein a front 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 in the inner duct, a separation type connecting structure is arranged between the compressor blade and the outer duct propelling blade, and duct sealing structures are arranged at front and rear openings of the inner duct. In the engine, the outer duct propulsion blade which is used as a main structure of underwater propulsion can normally work and generate thrust during air propulsion, so dead weight is not formed, the fuel efficiency and thrust-weight ratio during flight are greatly improved, and the flight range is increased. In addition, the front and back sealing of the inner duct adopts the elastic sealing film, so that the sealing effect is excellent, the problem that high-temperature precise components are damaged due to water seepage is avoided, and the inner duct can be immediately operated to lift off after being lifted up from water without waiting for the permeated water to be discharged.
Description
Technical Field
The invention belongs to the field of propulsion engines, in particular to a dual-purpose engine capable of being propelled in air and water, and particularly relates to an air-water integrated spray engine.
Background
Engines used in air-flying aircraft are commonly referred to as aeroengines, whose propelled jet is air. Air has a density and compressibility that are quite different from those of water, so that an aeroengine cannot be propelled in water by directly replacing air with water as a spray medium. The cross-medium propulsion capability has great application value in military.
CN 108891595A discloses a medium-crossing spacecraft power device adopting a medium sensing device and duct sealing, which comprises a turbofan engine jet propulsion system, and the jet propulsion mode is used for providing power for the spacecraft; the duct blade water spray propulsion system provides power for the spacecraft in a water spray propulsion mode; the medium sensing device is used for sensing the change of the working medium; and the duct sealing mechanism is used for starting the turbofan engine jet propulsion system and sealing the duct blade jet propulsion system when the medium sensing device senses that the working medium is changed into air, and is used for sealing the turbofan engine jet propulsion system and starting the duct blade jet propulsion system when the medium sensing device senses that the working medium is changed into water.
According to the prior art, a water spraying duct is additionally arranged on the periphery of a common turbofan jet engine, and the water spraying duct does not work in the air, so that the weight load is additionally increased, and the maintenance of the flying state is not facilitated. In addition, when in water, because the jet propulsion system of the inner duct is sealed by adopting a sealing sheet mode, the sealing sheets distributed in an annular mode are very difficult to obtain a good sealing effect, and the inner duct is difficult to effectively seal, 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 running, otherwise, the precise parts such as high-temperature blades and the like can cause structural damage once being chilled instantly when meeting water, and the jet propulsion system can be submerged after staying for a period of time on the water surface. Moreover, the prior art engines cannot start the jet propulsion system immediately after the engine floats from the water to the surface, and also need to wait until the water that has penetrated into the jet propulsion system is drained before starting. This prior art switching delay of the mode of operation is a very fatal disadvantage in war time.
Disclosure of Invention
The technical problem to be solved by the invention is to provide an air-water integrated spray engine so as to reduce or avoid the problems.
In order to solve the technical problems, the invention provides an air-water integrated spray 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 rear of the inner duct; wherein, a front outer duct propulsion 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 propulsion blade is arranged in the inner duct, a separation type connection structure is arranged between the compressor blade and the outer duct propulsion 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 propulsion blades when the compressor blades and the outer duct propulsion blades are propelled in the air, and the compressor blades and the outer duct propulsion blades are driven to move together through the turbine shaft; when the air compressor needs to be propelled in water, the separation type connecting structure enables the air compressor blade and the outer duct propulsion blade to be separated, the inner rotating part of the inner duct stops working, and the outer duct propulsion blade is independently driven 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 on 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 a layer of elastic sealing film is sealed and wrapped on the outer sides of the sealing plates; the inner duct is exposed when the sealing plate is folded, the sealing plate is propped against the inner wall surfaces of the front opening and the rear opening of the inner duct when being unfolded, and meanwhile, the elastic sealing films on the outer side are unfolded, so that the front opening and the rear opening of the inner duct are integrally sealed through the elastic sealing films.
Preferably, an elastic drawing film is arranged in the gap between two adjacent sealing plates, one side of each elastic drawing film is connected with an elastic sealing film, and the other side of each elastic drawing film is fixedly connected with the surfaces of the nose cone and the tail cone respectively.
Preferably, the split-type connecting structure comprises a plurality of sliding tiles connected in an annular sealing manner and arranged in a first annular gap on 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 when the compressor blade rotates under the drive of the turbine shaft, the sliding tiles are driven to move in the first annular gap.
Preferably, the inside of each sliding tile is provided with a telescopic tenon, and the telescopic tenon drives the sliding tile to stretch out and draw back through an electromagnetic mechanism arranged inside the sliding tile.
Preferably, the top of each outer duct propulsion blade is fixedly connected with a permanent magnet sliding sheet, and a plurality of permanent magnet sliding sheets are mutually connected into a second annular gap which is annularly arranged 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, and 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; the upper side of the annular slide rail is provided with a plurality of electromagnetic coils, 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 jet 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, the compressor blades and the outer duct propelling blades are connected through the separated connecting structure, and the air can be propelled to generate thrust similarly to a front fan aeroengine. When the inner culvert is pushed into water, the inner culvert is sealed through the culvert sealing structure, the inner mechanism of the inner culvert stops working, and the movable outer culvert blades can drive water to generate thrust through the electromagnetic coil. The outer duct propulsion blade serving as the main structure of the underwater propulsion in the invention can normally work and generate thrust under the drive of the turbine shaft during air propulsion, so dead weight can not be formed, the fuel efficiency and thrust-weight ratio during flight are greatly improved, and the flying range is favorably increased. In addition, the front and back sealing of the inner duct adopts the elastic sealing film, so that the sealing effect is excellent, the problem that high-temperature precise components are damaged due to water seepage is avoided, and the inner duct can be immediately operated to lift off after being lifted up from water without waiting for the permeated water to be discharged. An aircraft equipped with the engine of the present invention can be repeatedly brought into or lifted out of the water from the air, and can be reused.
Drawings
The following drawings are only for purposes of illustration and explanation of the present invention and are not intended to limit the scope of the invention.
Fig. 1 is a schematic partially cut-away view illustrating an open internal passage of an air-water integrated spray engine according to an embodiment of the present invention.
Fig. 2 is a schematic partially cut-away view showing an internal channel sealing state of an air-water integrated spray quality engine according to another embodiment of the present invention.
FIG. 3 is a schematic cross-sectional view of an air-water integrated spray engine according to yet another embodiment of the present invention, wherein the upper half shows an inner duct open state and the lower half shows an inner duct sealed state.
FIG. 4 shows an enlarged schematic view, partially in section, of a duct sealing structure according to an embodiment of the present invention.
Fig. 5 shows an enlarged schematic view, partially in section, of an elastic sealing membrane according to an embodiment of the invention.
Fig. 6 shows an exploded perspective view of a breakaway connection structure according to one embodiment of the present invention.
Detailed Description
For a clearer understanding of technical features, objects, and effects of the present invention, a specific embodiment of the present invention will be described with reference to the accompanying drawings. Wherein like parts are designated by like reference numerals.
On the basis of the existing jet aeroengine, the invention provides an air-water integrated jet engine with an improved structure, which can be used for both air propulsion and water propulsion, as shown in fig. 1-3. Wherein fig. 1 shows a schematic view from the front of the engine; FIG. 2 shows a schematic view from behind the engine; fig. 3 shows the upper and lower halves in two different states of propulsion in the air and in the water, respectively, for clarity.
As shown in the figure, the air-water integrated spray engine of the invention 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 in front of and behind the inner duct 2, and conventional structures such as a compressor, a combustion chamber, a turbine and the like are sequentially arranged in the inner duct 2 from front to back (see fig. 3).
Unlike the existing jet aeroengine, the air-water integrated jet mass engine of the present invention is provided with a front outer duct propulsion blade 3 near one end of the air inlet of the inner duct 2 between the outer duct 1 and the inner duct 2, the inner duct 2 is internally provided with a compressor blade 4 corresponding to the outer duct propulsion blade 3, a separation type connection structure 7 is provided between the compressor blade 4 and the outer duct propulsion blade 3, and front and rear openings of the inner duct 2 are provided with duct sealing structures 6 (which will be further described later). The separating connecting structure 7 is used for connecting the compressor blades 4 and the outer duct propulsion blades 3 when the blades are propelled in the air, and the blades are driven to move together through the turbine shaft 9 (figures 3 and 6); when propulsion in water is required, the split connection 7 separates the compressor blades 4 from the outer duct propulsion blades 3, the inner rotating parts of the inner duct 2 are deactivated (including the compressor blades 4), and the outer duct propulsion blades 3 are individually driven by the electromagnetic coil 5 (which will be further described later). In the embodiment shown in fig. 3, the compressor blade 4 is connected to a high-pressure turbine through a turbine shaft 9, and a low-pressure turbine may be further disposed behind the high-pressure turbine.
It should be noted that some conventional jet aeroengines have no outer duct, and even with an outer duct, there are no rotatable propulsion blades inside the outer duct, as power cannot be transmitted to the propulsion blades in the outer duct. Therefore, the outer duct propulsion blade 3 of the present invention is not a structural component of the prior art, but is a structural component added to the present invention on the basis of the prior art. Thus, the breakaway connection 7 is also an improved structure proposed by the present invention for the newly added outer duct advancing blade 3.
The basic working principle of the air-water integrated spray quality engine is as follows: when the air is propelled, 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 propulsion blades 3 are connected through the separated connecting structure 7, and the compressor blades 4 drive the outer duct propulsion blades 3 to rotate together, so that the air is propelled to generate thrust like a front fan aeroengine. When the inner duct 2 is pushed in water, the inner duct sealing structure 6 is used for sealing the inner duct 2, the internal mechanism of the inner duct 2 stops working, the compressor blades 4 and the outer duct pushing blades 3 are disconnected through the separated connecting structure 7, and the movable outer duct blades 3 drive water through the electromagnetic coil 5 to generate thrust.
In order to achieve the above-mentioned functions, the air-water integrated spray engine of the present invention needs to solve two main problems, namely, the front-back sealing problem of the internal channel 2 and the design problem of the separate connection structure, which will be described one by one.
The duct sealing structure 6 of the inner duct 2 is shown in fig. 4-5, and referring to fig. 1-3, the duct sealing structure 6 of the present invention includes a plurality of sealing plates 61 respectively disposed around the outer sides of the nose cone 21 and the tail cone 22, one ends of the sealing plates 61 near 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 surfaces of the front and rear openings of the inner duct 2 by being respectively propped by a telescopic rod 62, and a layer of elastic sealing film 63 is sealed and wrapped on the outer sides of the sealing plates 61. In fig. 1, 2 and 4, the elastic sealing film 63 outside the sealing plate 61 is omitted because the external appearance of the sealing plate 61 is required. The sealing plate 61 is similar to a framework of an umbrella, when being folded, the inner duct 2 is exposed, when being unfolded, the outer side edge is propped against the inner wall surfaces of the front opening and the rear opening of the inner duct 2, and meanwhile, the outer side elastic sealing film 63 is unfolded, 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 point of the front-back closure of the inner channel 2 is that an elastic sealing film 63 is sealed and 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 film 63 are respectively and hermetically connected with the surfaces of a nose cone 21 and a tail cone 22, and the elastic sealing film 63 is used for integrally sealing and wrapping the sealing plate 61. The whole sealing plate 61 is separated from the outside by the elastic sealing film 63 in the air or in water, and the telescopic rod 62, the hydraulic driving mechanism and the like inside the sealing plate 61 do not worry about the problem of water inflow inside. When the sealing plate 61 is spread, the middle of the elastic sealing film 63 is spread by the sealing plate 61 to arch, so that two layers of sealing films (shown in fig. 3) are actually formed, and 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 surfaces of the front and rear openings of the inner duct 2 by the sealing plate 61, the elastic sealing film 63 is extruded between the end part of the sealing plate 61 and the inner duct 2 to form a layer of elastic sealing gasket, so that a 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, a piece of elastic pulling film 64 is disposed in the gap between two adjacent sealing plates 61, one side of each piece of elastic pulling film 64 is connected with an elastic sealing film 63, and the other side is fixedly connected with the surfaces of the nose cone 21 and the tail cone 22 respectively. One function of the elastic pulling film 64 is that when the sealing plates 61 are folded, the elastic pulling film 64 can pull the elastic sealing film 63 into the space surrounded by the sealing plates 61 from the gaps of the adjacent sealing plates 61, so as to avoid that the sealing plates 61 are blocked and cannot be folded by the surface uncontrollable folds when the elastic sealing film 63 is folded. The other function of the elastic pulling film 64 is that when the engine is propelled in the air, the inner channel 2 generates high-speed air flow, extremely high pressure is formed on the surface of the elastic sealing film 63, and the elastic sealing film 63 may be torn by the pressure of the air flow under the high-speed air flow, so that the elastic pulling film 64 can firmly pull the elastic sealing film 63, and the elastic sealing film is prevented from being broken and damaged under the action of the high-speed air flow. In a preferred embodiment, the elastic coefficient of elasticity of the elastic pull film 64 needs to be greater than the elastic coefficient of elasticity of the elastic seal film 63.
The split connecting structure 7 is shown in fig. 6, and referring to fig. 1-3, the split connecting structure 7 of the air-water integrated spray engine of the present invention includes a plurality of sliding tiles 71 connected in an annular seal and 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 rotates under the drive of the turbine shaft 9, the sliding tile 71 is driven to move in the first annular gap 23. In order to avoid water seepage, it is preferable that the first annular bearing 72 is a sealed bearing, and the adjacent sliding tiles 71 are connected in a sealing manner, so that leakage is not formed at the position of the first annular gap 23 while the sliding tiles 71 move in the first annular gap 23. The structural parts of the inner duct 2 on both sides of the first annular gap 23 can be fixedly connected with the outer duct 1 on the outside by means of a support.
The inside of each sliding tile 71 is provided with a telescopic tenon 73, and the telescopic tenon 73 can be driven to stretch and retract through an electromagnetic mechanism arranged inside the sliding tile 71.
Similarly, a permanent magnet sliding piece 31 is fixedly connected to the top of each outer duct propulsion blade 3, and a plurality of permanent magnet sliding pieces 31 are connected to each other to move in a second annular gap 33 formed on the side wall of the outer duct 1 in an annular shape, that is, the permanent magnet sliding pieces 31 connected to each other in an annular shape can move in the second gap 33. The bottom of the outer duct propulsion blade 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 blade 4 and the outer ducted propulsion blade 3 together, the two are first aligned by the control mechanism and then the telescoping tenon 73 is driven by the electromagnetic mechanism inside the sliding tile 71 to extend and insert into the socket at the bottom of the outer ducted propulsion blade 3. When the compressor blade 4 and the outer duct propulsion blade 3 need to be disconnected, the telescopic tenon 73 is driven to retract.
Further, an annular slide rail 8 is disposed in the second annular gap 33, and 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 on 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 blade 4 and the outer duct propulsion blade 3 are disconnected, the permanent magnet sliding vane 31 can be driven to move through the electromagnetic coil 5 arranged on the outer side of the annular sliding rail 8, so that the outer duct propulsion blade 3 is driven to independently rotate.
The following describes further an air-water integrated operation process of an aircraft equipped with the air-water integrated spray quality engine of the present invention with reference to the accompanying drawings.
When the aircraft needs to fly from underwater into the air, the aircraft firstly floats to the water surface to enable the engine to be out of contact with the water, then drives the duct sealing structure 6 to enable the inner duct 2 to be opened, and the compressor blades 4 and the outer duct propulsion blades 3 need to be connected together to rotate through the separation type connecting structure 7 as described above, so that the air-water integrated spray engine pushes air to generate thrust similar to a front fan aeroengine, and the aircraft slides and lifts off from the water surface. When the underwater submarine is required to enter from the air, the engine can be stopped in the air directly, then the duct sealing structure 6 is driven to seal the inner duct 2, the compressor blades 4 and the outer duct propulsion blades 3 are disconnected through the separation type connecting structure 7 as described above, the aircraft can directly drill into the water and be submerged like a submarine immediately, and the outer duct propulsion blades 3 generate thrust to the water under the independent driving of the electromagnetic coil 5.
The operation mode of the invention has the advantages that when the air is propelled, the outer duct propulsion blade 3 which is a main structure of the water propulsion normally works and generates thrust under the drive of the turbine shaft 9, so dead weight is not formed, the fuel efficiency and thrust weight ratio during flying are greatly improved, and the flying range is increased. In addition, the front and rear closure of the inner duct 2 of the present invention adopts the elastic sealing film 63, which is excellent in sealing effect, free from the problem of damaging high temperature precision parts due to water seepage, and can be operated to lift up immediately after rising up from water, because a small amount of permeated water is rapidly vaporized and discharged during the ignition of the engine, and thus it is unnecessary to wait for the permeated water to be completely discharged. Further, the aircraft equipped with the engine of the present invention can be repeatedly brought into or lifted out of the water from the air, 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 inner mechanism of the inner duct 2 needs to be pushed into the water from the air, the operation problem of the inner mechanism of the inner duct 2 needs to be considered, that is, if the inner duct 2 is already sealed and the inner mechanism of the inner duct 2 is still rotating, under the action of the compressor, a huge suction force is formed at the air inlet position of the inner duct 2, and a huge pushing force is formed at the air outlet position, and these two forces break the elastic sealing membrane 63 to tear it. In order to avoid this, the air-water integrated spray engine of the present invention is also required to be provided with a brake mechanism (not shown in the drawings) for stopping rotation of the internal mechanism of the inner duct 2. By providing a braking mechanism to stop the internal mechanism of the inner duct 2 and an elastic sealing membrane 63, an aircraft equipped with the engine of the invention can directly span the water-air medium without having to land on the water surface to wait for internal cooling or to empty internal water seepage, greatly improving the capability of the aircraft to evade tracking.
It should be understood by those skilled in the art that while the present invention has been described in terms of several embodiments, not every embodiment contains only one independent technical solution. The description is given for clearness of understanding only, and those skilled in the art will understand the description as a whole and will recognize that the technical solutions described in the various embodiments may be combined with one another to understand the scope of the present invention.
The foregoing is illustrative of the present invention and is not to be construed as limiting the scope of the invention. Any equivalent alterations, modifications and combinations thereof will be effected by those skilled in the art without departing from the spirit and principles of this invention, and it is intended to be within the scope of the invention.
Claims (3)
1. An air-water integrated spray 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 inner culvert is characterized in that a front outer culvert propelling blade close to one end of an air inlet of the inner culvert is arranged between the outer culvert and the inner culvert, a compressor blade corresponding to the outer culvert propelling blade is arranged in the inner culvert, a separation type connecting structure is arranged between the compressor blade and the outer culvert propelling blade, and a culvert sealing structure is arranged at the front opening and the rear opening of the inner culvert; the separated connecting structure is used for connecting the compressor blades and the outer duct propulsion blades when the compressor blades and the outer duct propulsion blades are propelled in the air, and the compressor blades and the outer duct propulsion blades are driven to move together through the turbine shaft; when the air compressor needs to be propelled in water, the separation type connecting structure enables the air compressor blade and the outer duct propulsion blade to be separated, the internal rotating part of the inner duct stops working, and the outer duct propulsion blade is independently driven by the electromagnetic coil; the split type connecting structure comprises a plurality of sliding tiles connected in an annular sealing manner and arranged in a first annular gap on 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 when the compressor blade rotates under the drive of the turbine shaft, the sliding tiles are driven to move in the first annular gap; the inside of each sliding tile is provided with a telescopic tenon, and the telescopic tenon drives the sliding tile to stretch through an electromagnetic mechanism arranged inside the sliding tile; the top of each outer duct propulsion blade is fixedly connected with a permanent magnet sliding blade, and a plurality of permanent magnet sliding blades are mutually connected into a second annular gap which is annularly arranged 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; an annular slide rail is arranged in the second annular gap, 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; the upper side of the annular slide rail is provided with a plurality of electromagnetic coils, 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.
2. The air-water integrated spray engine as claimed in claim 1, wherein the duct sealing structure comprises a plurality of sealing plates respectively arranged around the outer sides of the nose cone and the tail cone, one ends of the sealing plates close to the central shaft of the engine are respectively hinged on 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 a layer of elastic sealing film is sealed and wrapped on the outer sides of the sealing plates; the inner duct is exposed when the sealing plate is folded, the sealing plate is propped against the inner wall surfaces of the front opening and the rear opening of the inner duct when being unfolded, and meanwhile, the elastic sealing films on the outer side are unfolded, so that the front opening and the rear opening of the inner duct are integrally sealed through the elastic sealing films.
3. The air-water integrated spray engine as claimed in claim 2, wherein an elastic pulling film is arranged in the gap between two adjacent sealing plates, one side of each elastic pulling film is connected with an elastic sealing film, and the other side is fixedly connected with the surfaces of the nose cone and the tail cone respectively.
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| CN202210275994.2A CN114562385B (en) | 2022-03-21 | 2022-03-21 | Air-water integrated spray engine |
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| CN202210275994.2A CN114562385B (en) | 2022-03-21 | 2022-03-21 | Air-water integrated spray engine |
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| CN114562385B true CN114562385B (en) | 2023-10-31 |
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| CN209800119U (en) * | 2019-05-12 | 2019-12-17 | 西北工业大学 | Self-driven outer duct contra-rotating annular fan blade compression device |
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