CN111071384A - Three-body ship - Google Patents
Three-body ship Download PDFInfo
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- CN111071384A CN111071384A CN201811220858.3A CN201811220858A CN111071384A CN 111071384 A CN111071384 A CN 111071384A CN 201811220858 A CN201811220858 A CN 201811220858A CN 111071384 A CN111071384 A CN 111071384A
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- trimaran
- gas turbine
- radial bearing
- compressor
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- 239000004698 Polyethylene Substances 0.000 claims abstract description 28
- -1 polyethylene Polymers 0.000 claims abstract description 28
- 229920000573 polyethylene Polymers 0.000 claims abstract description 28
- 239000000463 material Substances 0.000 claims abstract description 26
- 229910052751 metal Inorganic materials 0.000 claims abstract description 11
- 239000002184 metal Substances 0.000 claims abstract description 11
- 239000011241 protective layer Substances 0.000 claims abstract description 8
- 238000004146 energy storage Methods 0.000 claims description 15
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- 238000002485 combustion reaction Methods 0.000 claims description 7
- 230000005611 electricity Effects 0.000 claims description 7
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- 229910000838 Al alloy Inorganic materials 0.000 claims description 2
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- 239000000446 fuel Substances 0.000 description 3
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B1/00—Hydrodynamic or hydrostatic features of hulls or of hydrofoils
- B63B1/02—Hydrodynamic or hydrostatic features of hulls or of hydrofoils deriving lift mainly from water displacement
- B63B1/10—Hydrodynamic or hydrostatic features of hulls or of hydrofoils deriving lift mainly from water displacement with multiple hulls
- B63B1/12—Hydrodynamic or hydrostatic features of hulls or of hydrofoils deriving lift mainly from water displacement with multiple hulls the hulls being interconnected rigidly
- B63B1/125—Hydrodynamic or hydrostatic features of hulls or of hydrofoils deriving lift mainly from water displacement with multiple hulls the hulls being interconnected rigidly comprising more than two hulls
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B5/00—Hulls characterised by their construction of non-metallic material
- B63B5/24—Hulls characterised by their construction of non-metallic material made predominantly of plastics
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B5/00—Hulls characterised by their construction of non-metallic material
- B63B5/24—Hulls characterised by their construction of non-metallic material made predominantly of plastics
- B63B2005/242—Hulls characterised by their construction of non-metallic material made predominantly of plastics made of a composite of plastics and other structural materials, e.g. wood or metal
- B63B2005/245—Hulls characterised by their construction of non-metallic material made predominantly of plastics made of a composite of plastics and other structural materials, e.g. wood or metal made of a composite of plastics and metal
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Ocean & Marine Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Magnetic Bearings And Hydrostatic Bearings (AREA)
Abstract
The invention provides a trimaran, wherein the trimaran comprises a main hull, a first auxiliary hull and a second auxiliary hull, wherein the first auxiliary hull and the second auxiliary hull are respectively arranged at two sides of the main hull, the main hull is provided with a cabin, and a power system is arranged in the cabin; the first secondary hull and the second secondary hull are both made of polyethylene material; or, the first secondary hull and the second secondary hull both comprise a metal frame structure and a polyethylene protective layer wrapping the metal frame structure. In the invention, the polyethylene material has the characteristics of large elastic modulus, strong impact absorption capacity and the like, so that the impact resistance of the ship body can be improved, and the safety of the trimaran is improved. In addition, the density of the polyethylene material is smaller than that of water, so that the weight of the ship body is lighter, the waterline of the trimaran can be reduced, the navigation resistance of the trimaran can be reduced, and the navigation speed of the trimaran can be improved.
Description
Technical Field
The invention relates to the technical field of ships, in particular to a trimaran.
Background
With the increasing demand of modern war on logistics transportation, civil transport ships play more and more important logistics transportation role in modern war, so the living environment is also threatened more and more seriously, and is often threatened by weapons such as torpedo, mine torpedo, deep water bomb and the like, which needs to enhance the protection capability of the transport ships. At present, military combat ships generally adopt a method of arranging a protective structure on a board side, and the method can effectively protect internal structures, electronic equipment, mechanical equipment and the like of a ship body from being damaged and ensure normal activities of personnel on a transport ship.
However, for civil transport ships, the added protection structure can increase the weight of the ship body, so that the gravity center position of the ship body is changed, and the stability and the rapidity of ship navigation are adversely affected; moreover, the protective structure can occupy the space in the original cabin and damage the overall layout; in addition, the installation of the side protection structure can greatly increase the manufacturing cost of the ship.
Disclosure of Invention
The present invention provides a trimaran to solve the above problems.
In a first aspect, the invention provides a trimaran, which comprises a main hull, a first auxiliary hull and a second auxiliary hull, wherein the first auxiliary hull and the second auxiliary hull are respectively arranged at two sides of the main hull;
the first secondary hull and the second secondary hull are both made of polyethylene material; alternatively, the first and second electrodes may be,
the first secondary hull and the second secondary hull both comprise a metal frame structure and a polyethylene protective layer wrapping the metal frame structure.
In a second aspect, the invention provides another trimaran, which comprises a main hull, a first auxiliary hull and a second auxiliary hull, wherein the main hull is provided with a cabin, a power system is arranged in the cabin, and a power source of the power system is a gas turbine engine;
the bottom of the main ship body is also provided with a pressure cabin, the cabin bottom of the pressure cabin is provided with a plurality of jet holes, the pressure cabin is communicated with an exhaust pipeline of the gas turbine engine, and a one-way valve is arranged between the exhaust pipeline and the pressure cabin.
In the invention, by arranging the auxiliary ship body made of the polyethylene material, the polyethylene material has the characteristics of large elastic modulus, strong impact absorption capacity and the like, so that the impact resistance of the ship body can be improved, the trimaran can prevent damages of underwater attack weapons such as torpedoes, mines, deep-water bombs and the like, and the safety of the trimaran is improved. In addition, the density of the polyethylene material is smaller than that of water, so that the weight of the ship body is lighter, the waterline of the trimaran can be reduced, the navigation resistance of the trimaran can be reduced, and the navigation speed of the trimaran can be improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required to be used in the description of the embodiments of the present invention will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without inventive exercise.
Fig. 1 is a schematic perspective view of a trimaran according to an embodiment of the present invention;
FIG. 2 is a top view of a trimaran according to an embodiment of the invention;
FIG. 3 is a cross-sectional view taken along line A-A of FIG. 2;
figures 4 to 5 are schematic half-sections of the trimaran of the invention viewed along the stern to the bow;
FIG. 6 is a schematic diagram of a host power system of a trimaran according to an embodiment of the present invention;
FIG. 7 is a schematic structural diagram of a gas turbine generator set of a trimaran according to an embodiment of the present invention;
FIG. 8 is a schematic view of the formation of a supercavity in front of the hull of a trimaran provided by an embodiment of the present invention;
fig. 9 to 29 are schematic layout views of a rotor system of a gas turbine generator set of a trimaran according to an embodiment of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example one
As shown in fig. 1 to 5, an embodiment of the present invention provides a trimaran 10 including a main hull 100, a first sub-hull 110, and a second sub-hull 120, the first sub-hull 110 and the second sub-hull 120 being provided on both sides of the main hull 100, the main hull 100 being provided with a nacelle 150, and a power system 160 being provided in the nacelle 150.
Wherein the first and second subsidiary hulls 110 and 120 may be symmetrically distributed on both sides of the main hull 100 to improve the stability of the trimaran. The trimaran 10 can further include a deck 130 and a cockpit 140, the first hull 110, the main hull 100, and the second hull 120 can be disposed below the deck 130, collectively supporting the deck 130, and the cockpit 140 can be located above the deck 130. Therefore, the main hull and the two auxiliary hulls can jointly support a wider deck, and the stability of the trimaran is further improved.
In order to improve the safety of a trimaran and prevent damage of underwater attack weapons such as torpedoes, mines, and deep-water bombs, it is necessary to improve the impact resistance of the hull. The high molecular polyethylene material has the characteristics of large elastic modulus, strong impact absorption capacity and the like, so that the hull of the trimaran can be made of the polyethylene material.
As an embodiment, the first and second sub-hulls 110 and 120 are each made of polyethylene material, as shown in fig. 4.
When the trimaran is attacked by weapons, the polyethylene material transmits the impact energy to the region other than the impact point, thereby absorbing the impact energy. Therefore, the sub-hull can protect the main hull 100 well, protect the power system 160 in the main hull 100 from being damaged by underwater attack weapons such as torpedoes, mines, and deep water bombs, and improve the safety of the trimaran 10. Even if the first sub-hull 110 or the second sub-hull 120 is knocked down and exploded away from the trimaran 10 under the condition of encountering violent torpedo attack, the main hull 100 and the power system 160 in the main hull are not damaged, and the safety of the sailing boat is ensured.
In addition, the density of the polyethylene material is lower than that of water, the auxiliary ship body is made of polyethylene, the weight of the ship body cannot be increased excessively, and the waterline, the stability and the rapidity of the ship body cannot be changed; and has certain floating capacity to the deck 130, can improve the stability that the vice hull supported deck 130.
In addition, the polyethylene material has strong corrosion resistance, and cannot be corroded by seawater even if the polyethylene material is used for a long time on the sea.
As another embodiment, the first and second sub-hulls 110, 120 each comprise a metal frame structure (111, 121) and a polyethylene protective layer (112, 122) wrapping the metal frame structure (111, 121), as shown in fig. 5.
For the subsidiary hulls provided with the metal frame structures (111, 121), the stability and the stationarity of the two sides of the main hull 100 are improved due to the arrangement of the metal frame structures (111, 121) because the weight of the metal frame structures (111, 121) is relatively large. The whole auxiliary ship body made of polyethylene material has light weight, low waterline and small navigation resistance, and is favorable for improving the navigation speed of the ship. Therefore, the specific arrangement of the first and second sub-hulls 110 and 120 can be specifically designed according to the driving environment and performance requirements of the ship.
As another embodiment, the outer surface of the main hull 100 is provided with a polyethylene protective layer 101. Optionally, a polyethylene protective layer 101 is disposed below the waterline of the main hull 100, and particularly, the polyethylene protective layer 101 is disposed on the outer surface of the main hull 100 where the power system 160 is installed, so as to further protect the power system 160.
Therefore, in the embodiment of the invention, the auxiliary ship body made of the polyethylene material is arranged, and the polyethylene material has the characteristics of large elastic modulus, strong impact absorption capacity and the like, so that the impact resistance of the ship body can be improved, the trimaran can prevent damages of underwater attack weapons such as torpedoes, mines, deep water bombs and the like, and the safety of the trimaran is improved. In addition, the density of the polyethylene material is smaller than that of water, so that the weight of the ship body is lighter, the waterline of the trimaran can be reduced, the navigation resistance of the trimaran can be reduced, and the navigation speed of the trimaran can be improved.
In an embodiment of the present invention, the power system 160 may include a main engine power system 161 and an auxiliary engine power system 162. The main engine power system 161 may be disposed at the middle rear part of the main hull 100, and the energy generated by the main engine power system may be used to provide the main power for the entire ship; an auxiliary power system 162 may be provided at the front of the main hull 100, and the energy generated by the auxiliary power system may be used to provide the necessary electrical power for the ship and to drive other auxiliary equipment on the ship, such as an air conditioner, a water pump, an oil pump, etc.
At least one of the main engine power system 161 and the auxiliary engine power system 162 may employ a gas turbine engine as a power source. The following description will be made in detail by taking the gas turbine engine as an example of the power source of the main engine power system 161.
As shown in fig. 6, the main machine power system 161 includes:
a gas turbine generator set 170 comprising a gas turbine engine 1701 and an electric machine 1702, the gas turbine engine 1701 being coupled to the electric machine 1702, the gas turbine engine 1701 being capable of driving the electric machine 1702 to generate electricity;
the motor 172, the motor 172 is electrically connected with the motor 1702, and the electric energy generated by the motor 1702 can be input to the motor 172 to drive the motor 172 to operate;
With the above arrangement, the gas turbine engine 1701 may provide power for sailing the trimaran 10 in two ways, one in which the shaft work output from the gas turbine engine 1701 is directly used to drive the propulsion system 173, and the other in which the shaft work output from the gas turbine engine 1701 is converted into electrical energy to further drive the propulsion system 173 via the electric motor 172. The two ways can be carried out simultaneously or independently, so that the engine can work under a relatively stable working condition conveniently.
Optionally, the main engine power system 161 further comprises an energy storage system 174, and the energy storage system 174 is electrically connected to the motor 172 and the motor 1702 respectively;
the electrical energy generated by the electric machine 1702 may be input to the energy storage system 174, and the electrical energy stored by the energy storage system 174 may be input to the electric motor 172.
Through the arrangement, the energy generated by the gas turbine generator set 170 can be used for driving the trimaran 10 to sail, and the redundant shaft work generated by the gas turbine generator set 170 can also be used for generating electricity, the generated electric energy can be used for driving the propulsion system 173 to further drive the trimaran 10 to advance, the redundant electric energy can also be stored in the energy storage system 174, and the stored electric energy can be used for an auxiliary power supply of the trimaran 10 or providing emergency main power for the trimaran 10 under the condition that the gas turbine generator set 170 is abnormal.
Since the shaft work output by the gas turbine engine 1701 may be utilized in two ways, the shaft work output by the gas turbine engine 1701 need only be properly distributed to the propulsion system 173 and the energy storage system 174 without changing the total power output by the gas turbine engine 1701 when the trimaran 10 is in different operating conditions. For example, when the trimaran 10 needs to travel at maximum power at full speed, all of the shaft work output by the gas turbine generator set 170 can be used to directly drive the propulsion system 173 without generating electricity via the motor 1702; when the trimaran 10 is traveling slowly or even parked briefly, part or all of the shaft power output from the gas turbine engine 1701 may be used to drive the electric motor 1702 to generate electricity, and the generated electric energy may be stored in the energy storage system 174 for auxiliary or emergency use of the trimaran 10. Thus, the gas turbine engine 1701 may operate at a stable rated power under any operating condition, which is advantageous for improving the stability of the gas turbine engine 1701 and improving the service life thereof, as well as for facilitating the sufficient combustion of fuel and improving the energy utilization rate.
Optionally, the main machine power system 161 further comprises a current converter 171, the current converter 171 is used for converting alternating current and direct current, the current converter 171 is arranged between the electric machine 1702 and the energy storage system 174, and between the electric machine 1702 and the electric motor 172, and the electric machine 1702 is electrically connected with the electric motor 172 and the energy storage system 174 through the current converter 171.
Alternatively, the electric machine 1702 is a starter-integrated electric machine, and the electric machine 1702 can be used as both a generator and a motor. At the start of the gas turbine engine 1701, electrical energy stored by the energy storage system 174 may be input to the electric machine 1702 such that the electric machine 1702 drives the gas turbine engine 1701 as a motor, and when the gas turbine engine 1701 is started and enters a normal operating condition, the electric machine 1702 acts as a generator to generate electricity driven by the gas turbine engine 1701.
As shown in fig. 7, the gas turbine engine 1701 may include a compressor 180, a turbine 181, and a combustion chamber 183, an electric motor 1702, the compressor 180, and the turbine 181 are coupled by a rotating shaft 182, the electric motor 1702, the compressor 180, and the turbine 181 are sequentially mounted to the rotating shaft 182, and the combustion chamber 183 is disposed between the compressor 180 and the turbine 181.
Wherein the air inlet of the compressor 180 is connected to an air inlet device (not shown) provided on the trimaran 10.
Optionally, the shaft 182 is coupled to the propulsion system 173 via a transmission gear 184.
The operation of the gas turbine generator set 170 is as follows: air enters the compressor 180 through an air inlet device and is compressed into high-pressure air, the high-pressure air is supplied to the combustion chamber 183 to be mixed and combusted with fuel, high-temperature high-pressure gas generated by the high-pressure high.
Given that the host power system 161 employs the gas turbine engine 1701 as an engine, the trimaran 10 of the embodiment of the invention can be fabricated as a supercavitation trimaran by using the exhaust gas of the gas turbine engine 1701 as a source of pressurized gas.
As shown in fig. 3, a pressure tank 102 is further provided at the bottom of the main hull 100, a bottom 103 of the pressure tank 102 has a plurality of injection holes, the pressure tank 102 communicates with an exhaust pipe of the gas turbine engine 1701 in the main engine system 161, and a check valve 175 is provided between the exhaust pipe and the pressure tank 102. Check valve 175 allows pressurized gas discharged from gas turbine engine 1701 to enter pressure tank 102 without allowing reverse flow of pressurized gas or seawater to flow from pressure tank 102 into the exhaust duct of gas turbine engine 1701.
Wherein, the bottom 103 of the pressure chamber 102 can be made of porous material. The bottom 103 of the pressure chamber 102 may be made of foamed aluminum alloy or foamed magnesium alloy.
When the ship needs to sail at a particularly high speed, the exhaust gas of the gas turbine engine 1701 is controlled to inject pressure gas into the pressure tank 102, the pressure gas entering the pressure tank 102 is injected outwards through the injection holes of the tank bottom 103, a supercavitation environment is formed along the bottom and the front of the main hull 100, and the generation of the supercavitation enables a gas film to be formed between the hull and water, the gas film can greatly reduce the resistance of seawater to the hull, so that the speed of the ship is greatly improved, namely, a supercavitation trimaran is formed, as shown in fig. 8.
Thus, the operation of the gas turbine generator set 170 is: air enters the compressor 180 through the air inlet device and is compressed into high-pressure air, the high-pressure air is supplied to the combustion chamber 183 to be mixed and combusted with fuel, high-temperature high-pressure gas generated by the high-pressure gas expands in the turbine 181 and does work, the turbine 181 drives the rotating shaft 182 to rotate, the rotating shaft 182 drives the motor 1702 to generate electricity, and/or the transmission speed regulating device 184 drives the propulsion system 173 to work to provide main power for navigation of the trimaran 10, meanwhile, pressure gas exhausted by the turbine 181 is injected into the pressure cabin 102 as a pressure gas source, and the pressure gas forms a supercavity environment in front of and near the hull through the cabin bottom 103, so that the navigation resistance of the trimaran.
Optionally, the exhaust duct of the gas turbine engine is provided with a pressure boosting device (not shown) for boosting the pressure of the gas entering the pressure tank, thereby facilitating the formation of a supercavitation environment at the bottom and in front of the main hull 100.
Since the auxiliary power system 162 may employ a gas turbine engine as an engine, the pressure gas for forming the supercavitation may be also derived from the exhaust gas of the gas turbine engine of the auxiliary power system 162. The specific principle is the same as that of the main engine power system 161, and is not described herein again to avoid redundancy.
With the above arrangement, the trimaran 10 according to the embodiment of the present invention has a capability of preventing the attack of underwater weapons and high safety as compared with the conventional trimaran, and the trimaran 10 forms supercavity at the front portion of the main hull 100 and in the vicinity thereof by using the pressure exhaust gas discharged from the gas turbine engine 1701, thereby greatly increasing the traveling speed of the trimaran 10.
In addition, considering the running stability of the trimaran 10, the stability of the rotor system can be improved by reasonably setting the positions of the main components in the rotor system of the gas turbine engine unit 170, thereby improving the sailing stability of the trimaran 10.
Wherein the rotating shaft 182, the motor 1702, the compressor 180 and the turbine 181 form a rotor system of the gas turbine generator set;
the shaft body of the rotating shaft 182 is an integral structure, and the rotating shaft 182 is horizontally arranged;
the rotating shaft 182 is further provided with a thrust bearing 500 and at least two radial bearings, and the thrust bearing 500 and the at least two radial bearings are non-contact bearings;
the thrust bearing 500 is disposed at a predetermined position on a side of the turbine 181 close to the compressor 180, where the predetermined position is a position where the center of gravity of the rotor system is located between two radial bearings located farthest away from each other among the at least two radial bearings.
In order to keep the entire rotor system structurally stable even at high speed rotation, the center of gravity of the entire rotor system should be located between the two radial bearings that are farthest apart from each other among the at least two radial bearings. Therefore, the whole rotor system forms a spindle body structure, and the stability of the whole rotor system is improved.
In the embodiment of the present invention, the setting position of the thrust bearing may be flexibly adjusted according to the parameters such as the setting number of the radial bearings of the at least two radial bearings, the setting position of each radial bearing, and the mass of each component in the entire rotor system (including the mass of the thrust bearing itself), so that the center of gravity of the entire rotor system is located between the two radial bearings which are farthest away, and preferably, the center of gravity of the entire rotor system is located on the compressor 180.
The rotor system described above may adopt the structure shown in fig. 9 to 26.
As shown in fig. 9 to 11, the rotor system includes:
the rotating shaft 182, the shaft body of the rotating shaft 182 is an integral structure, and the rotating shaft 182 is horizontally arranged;
a motor 1702, a compressor 180 and a turbine 181 which are sequentially arranged on the rotating shaft 182;
and a thrust bearing 500, a first radial bearing 600 and a second radial bearing 700 which are arranged on the rotating shaft 182, wherein the first radial bearing 600 is arranged on the side of the electric motor 1702 far away from the compressor 180, and the second radial bearing 700 is arranged between the compressor 180 and the turbine 181.
The thrust bearing 500 is disposed between the first radial bearing 600 and the motor 1702, as shown in fig. 9; alternatively, the thrust bearing 500 is disposed on a side of the first radial bearing 600 away from the motor 1702, as shown in fig. 10; alternatively, the thrust bearing 500 is disposed between the motor 1702 and the compressor 180, as shown in fig. 11.
In the case that the mass of the turbine 181 is large, for example, the material of the turbine 181 is a metal material, and in order to locate the center of gravity of the entire rotor system between the first radial bearing 600 and the second radial bearing 700, the embodiment shown in fig. 9 or fig. 10 may be adopted.
When the mass of the turbine 181 is small, for example, the material of the turbine 181 is a ceramic material or a ceramic fiber composite material, so that the center of gravity of the entire rotor system is located between the first radial bearing 600 and the second radial bearing 700, the embodiment shown in fig. 11 may be adopted.
In the embodiment shown in fig. 11, since the thrust bearing 500 is disposed between the motor 1702 and the compressor 180, the embodiment shown in fig. 7 is applied to the thrust bearing 500 having a small diameter of the thrust disk in order to prevent the thrust disk of the thrust bearing 500 from blocking the air inlet of the compressor 180.
In consideration of the development requirement of high rotation speed of the gas turbine or the gas turbine generator set, in order to improve the working performance of the thrust bearing and the radial bearing, in the embodiment of the present invention, the thrust bearing 500 may be a gas-magnetic hybrid thrust bearing, and the first radial bearing 600 may be a gas-magnetic hybrid radial bearing or a gas hybrid radial bearing.
In addition, since the second radial bearing 700 is close to the turbine 181, the second radial bearing 700 may employ a hybrid gas-hybrid radial bearing in consideration that the magnetic components in the magnetic bearings cannot withstand the high temperature from the turbine 181.
In another embodiment, the second radial bearing 700 may also be a gas-magnetic hybrid radial bearing, in which case the magnetic component of the second radial bearing 700 is arranged on the second radial bearing 700 in a region remote from the turbine 181. That is, the second radial bearing 700 is not provided with magnetic components in the region close to the turbine 181.
To protect the magnetic components of the second radial bearing 700, this can be achieved by reducing the heat energy radiated by the turbine 181 onto the second radial bearing 700. In particular, the turbine 181 is provided with a heat-insulating layer (not shown) on the side close to the second radial bearing 700. Here, the material of the thermal insulation layer may be aerogel or other material having good thermal insulation properties.
Fig. 12 to 14 show a schematic representation of the arrangement of magnetic components on the second radial bearing 700 of fig. 9 to 11 in a region remote from the turbine 181.
The compressor 180 can be a centrifugal compressor 180, and the turbine 181 can be a centrifugal turbine; the motor 1702 may be a dynamic pressure bearing motor, and a portion of the rotating shaft 182 corresponding to a bearing of the motor 1702 may be provided with a first dynamic pressure generating groove 201.
As shown in fig. 15 to 18, the rotor system includes:
the rotating shaft 182, the shaft body of the rotating shaft 182 is an integral structure, and the rotating shaft 182 is horizontally arranged;
a motor 1702, a compressor 180 and a turbine 181 which are sequentially arranged on the rotating shaft 182;
and a thrust bearing 500, a first radial bearing 600, a second radial bearing 700 and a third radial bearing 800 which are arranged on the rotating shaft 182, wherein the first radial bearing 600 is arranged on one side of the electric motor 1702 far away from the compressor 180, the second radial bearing 700 is arranged between the compressor 180 and the turbine 181, and the third radial bearing 800 is arranged between the electric motor 1702 and the compressor 180.
The thrust bearing 500 is disposed between the first radial bearing 600 and the motor 1702, as shown in fig. 15; alternatively, the thrust bearing 500 is disposed on a side of the first radial bearing 600 away from the motor 1702, as shown in fig. 16; alternatively, the thrust bearing 500 is disposed between the motor 1702 and the compressor 180, as shown in fig. 17 or 18.
Due to the addition of the third radial bearing 800, when the thrust bearing 500 is disposed between the motor 1702 and the compressor 180, the thrust bearing 500 may be disposed between the motor 1702 and the third radial bearing 800, as shown in fig. 17; the thrust bearing 500 may in turn be disposed between the third radial bearing 800 and the compressor 180, as shown in fig. 18.
The stability of the entire rotor system can be further improved by adding a third radial bearing 800 between the motor 1702 and the compressor 180.
In the embodiment of the present invention, the thrust bearing 500 may adopt a gas magnetic hybrid thrust bearing, and the first radial bearing 600 may adopt a gas magnetic hybrid radial bearing or a gas hybrid radial bearing; since the second radial bearing 700 is close to the turbine 181, the second radial bearing 700 may employ a hybrid gas-hybrid radial bearing in consideration of a magnetic component included in the magnetic bearing that cannot withstand a high temperature from the turbine 181.
In another embodiment, the second radial bearing 700 may also be a gas-magnetic hybrid radial bearing, in which case the magnetic component of the second radial bearing 700 is arranged on the second radial bearing 700 in a region remote from the turbine 181. That is, the second radial bearing 700 is not provided with magnetic components in the region close to the turbine 181.
To protect the magnetic components of the second radial bearing 700, this can be achieved by reducing the heat energy radiated by the turbine 181 onto the second radial bearing 700. In particular, the turbine 181 is provided with a heat-insulating layer (not shown) on the side close to the second radial bearing 700. Here, the insulation layer may be aerogel or other material.
Fig. 19 to 22 show a schematic representation of the arrangement of magnetic components on the second radial bearing 700 from fig. 15 to 18 in a region remote from the turbine 181.
As shown in fig. 23, the rotor system includes:
the rotating shaft 182, the shaft body of the rotating shaft 182 is an integral structure, and the rotating shaft 182 is horizontally arranged;
a motor 1702, a compressor 180 and a turbine 181 which are sequentially arranged on the rotating shaft 182;
and a thrust bearing 500, a first radial bearing 600, a second radial bearing 700 and a fourth radial bearing 900 which are arranged on the rotating shaft 182, wherein the first radial bearing 600 is arranged on one side of the motor 1702 far away from the compressor 180, the second radial bearing 700 is arranged between the compressor 180 and the turbine 181, the fourth radial bearing 900 is arranged on one side of the turbine 181 far away from the compressor 180, and the thrust bearing 500 is arranged between the compressor 180 and the second radial bearing 700.
Embodiments of the present invention can be applied to the situation where the mass of the motor 1702 is too large, and when the mass of the motor 1702 is too large, radial bearings (i.e. the first radial bearing 600 and the fourth radial bearing 900) need to be arranged at both ends of the rotor system in order to maintain the stability of the rotor system, and the thrust bearing 500 needs to move toward one side of the turbine 181.
In consideration of the high temperature of the turbine 181, when the thrust bearing 500 is a gas-magnetic hybrid thrust bearing, since the magnetic components in the magnetic bearings cannot withstand the high temperature transmitted from the turbine 181, the thrust bearing 500 may be disposed between the compressor 180 and the second radial bearing 700. Accordingly, the second radial bearing 700 may employ a hybrid gas hybrid radial bearing.
Generally, the temperature of the side of the turbine 181 close to the fourth radial bearing 900 is higher than the temperature of the side of the turbine 181 close to the second radial bearing 700, and therefore, the fourth radial bearing 900 is preferably a hybrid gas-hybrid radial bearing.
In another embodiment, the second radial bearing 700 may also be a gas-magnetic hybrid radial bearing, in which case the magnetic component of the second radial bearing 700 is arranged on the second radial bearing 700 in a region remote from the turbine 181. That is, the second radial bearing 700 is not provided with magnetic components in the region close to the turbine 181.
To protect the magnetic components of the second radial bearing 700, this can be achieved by reducing the heat energy radiated by the turbine 181 onto the second radial bearing 700. In particular, the turbine 181 is provided with a heat-insulating layer (not shown) on the side close to the second radial bearing 700. Here, the insulation layer may be aerogel or other material.
Fig. 24 shows a schematic view of the second radial bearing 700 of fig. 23 with magnetic components located in a region remote from the turbine 181.
It should be noted that when the mass of the motor 1702 is not too large, the thrust bearing 500 may be disposed between the first radial bearing 600 and the motor 1702; alternatively, the thrust bearing 500 may be disposed on a side of the first radial bearing 600 away from the motor 1702; alternatively, the thrust bearing 500 may be disposed between the motor 1702 and the compressor 180. This is not described in detail as it is readily understood.
As shown in fig. 25, the rotor system includes:
the rotating shaft 182, the shaft body of the rotating shaft 182 is an integral structure, and the rotating shaft 182 is horizontally arranged;
a motor 1702, a compressor 180 and a turbine 181 which are sequentially arranged on the rotating shaft 182;
and a thrust bearing 500, a first radial bearing 600, a second radial bearing 700, a third radial bearing 800 and a fourth radial bearing 900 which are arranged on the rotating shaft 182, wherein the first radial bearing 600 is arranged on one side of the motor 1702 far away from the compressor 180, the second radial bearing 700 is arranged between the compressor 180 and the turbine 181, the third radial bearing 800 is arranged between the motor 1702 and the compressor 180, the fourth radial bearing 900 is arranged on one side of the turbine 181 far away from the compressor 180, and the thrust bearing 500 is arranged between the compressor 180 and the second radial bearing 700.
The addition of the third radial bearing 800 between the motor 1702 and the compressor 180 further improves the stability of the entire rotor system.
In the embodiment of the present invention, the thrust bearing 500 may be a gas magnetic hybrid thrust bearing, and both the second radial bearing 700 and the fourth radial bearing 900 may be gas hybrid radial bearings.
In another embodiment, the second radial bearing 700 may also be a gas-magnetic hybrid radial bearing, in which case the magnetic component of the second radial bearing 700 is arranged on the second radial bearing 700 in a region remote from the turbine 181. That is, the second radial bearing 700 is not provided with magnetic components in the region close to the turbine 181.
To protect the magnetic components of the second radial bearing 700, this can be achieved by reducing the heat energy radiated by the turbine 181 onto the second radial bearing 700. In particular, the turbine 181 is provided with a heat-insulating layer (not shown) on the side close to the second radial bearing 700. Here, the insulation layer may be aerogel or other material.
Fig. 26 shows a schematic view of the second radial bearing 700 of fig. 25 with magnetic components located in a region remote from the turbine 181.
In order to reduce the machining precision and the assembling precision of the rotor system and improve the stability of the whole rotor system, the rotor system of the embodiment of the invention can also adopt the following technical scheme: the bearing is completely arranged in the first casing, and the compressor and the turbine are arranged in the second casing, so that only the machining precision of a part for arranging the bearing stator in the first casing is required to be ensured, and the part for connecting the bearing stator in the first casing can be machined by one-time clamping during assembly; and the impeller of the compressor is arranged close to the impeller of the turbine, so that the axial length in the second casing is shortened, and the stability of the whole rotor system can be improved.
The rotor system described above may also adopt the structure shown in fig. 27 to 29. As shown in fig. 27 to 29, the rotor system includes:
the rotating shaft 182, the shaft body of the rotating shaft 182 is an integral structure, and the rotating shaft 182 is horizontally arranged;
the motor 1702, the compressor 180, the turbine 181, the thrust bearing 500, the first radial bearing 600 and the second radial bearing 700 are arranged on the rotating shaft 182, and the thrust bearing 500, the first radial bearing 600 and the second radial bearing 700 are all non-contact bearings;
the first casing 801 is connected with the second casing 901, the motor 1702, the thrust bearing 500, the first radial bearing 600 and the second radial bearing 700 are all arranged in the first casing 801, and the compressor 180 and the turbine 181 are all arranged in the second casing 901; the impeller of the compressor 180 is disposed adjacent to the impeller of the turbine 181 in the second casing 901.
The first radial bearing 600 is disposed on a side of the motor 1702 far from the second casing 901, and the second radial bearing 700 is disposed on a side of the motor 1702 near the second casing 901.
The thrust bearing 500 is disposed between the first radial bearing 600 and the motor 1702, as shown in fig. 27; alternatively, the thrust bearing 500 is disposed between the motor 1702 and the second radial bearing 700, as shown in fig. 28; alternatively, the thrust bearing 500 is disposed on a side of the second radial bearing 700 close to the second casing 901, as shown in fig. 29.
In the embodiment shown in fig. 29, since the thrust bearing 500 is disposed on the side of the second radial bearing 700 close to the second casing 901, that is, the thrust bearing 500 is disposed close to the compressor in the second casing 901, the embodiment shown in fig. 29 is applied to the thrust bearing 500 having a small thrust disk diameter in order to prevent the thrust disk of the thrust bearing 500 from blocking the air inlet of the compressor 180.
Therefore, in consideration of the development requirement of the high rotation speed of the gas turbine generator set, in order to improve the working performance of the thrust bearing and the radial bearing, in the embodiment of the present invention, the thrust bearing 500 may adopt a gas-magnetic hybrid thrust bearing, and the first radial bearing 600 may adopt a gas-magnetic hybrid radial bearing or a gas hybrid radial bearing; the second radial bearing 700 may employ a gas-magnetic hybrid radial bearing or a gas hybrid radial bearing.
Optionally, the bearing capacity of the second radial bearing 700 is greater than the bearing capacity of the first radial bearing 600.
In the present embodiment, the motor 1702 and the thrust bearing 500 generally have a larger weight, and the center of gravity of the entire rotor system is biased toward the first radial bearing 600. In view of this, increasing the bearing capacity of the second radial bearing 700 helps to increase the stability of the entire rotor system.
In the embodiment of the invention, the compressor 180 can be a centrifugal compressor 180, and the turbine of the turbine 181 can be a centrifugal turbine; the bearing of the motor 1702 may be a hydrodynamic bearing, and a portion of the rotating shaft 182 corresponding to the bearing of the motor 1702 may be provided with a first dynamic pressure generating groove 201.
Further, the motor 1702 may also be a starter-integral motor.
Thus, at the initial start of the rotor system, the motor 1702 may be turned on in a start mode to rotate the rotor system, and after the rotational speed of the rotor system is increased to a preset rotational speed, the operation mode of the motor 1702 may be switched to a power generation mode.
Example two
The embodiment of the invention also provides another trimaran, which comprises a main hull, a first auxiliary hull and a second auxiliary hull, wherein the main hull is provided with a cabin, a power system is arranged in the cabin, and a power source of the power system is a gas turbine engine;
the bottom of the main ship body is also provided with a pressure cabin, the cabin bottom of the pressure cabin is provided with a plurality of jet holes, the pressure cabin is communicated with an exhaust pipeline of the gas turbine engine, and a one-way valve is arranged between the exhaust pipeline and the pressure cabin.
Further, the implementation manners related to the impact-resistant structure and/or the structure of the power system of the trimaran in the first embodiment can also be applied to the trimaran in the embodiments of the present invention, and have the same beneficial effects, and are not described herein again to avoid repetition.
The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention, and the changes or substitutions should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (13)
1. A trimaran is characterized by comprising a main hull, a first auxiliary hull and a second auxiliary hull, wherein the first auxiliary hull and the second auxiliary hull are respectively arranged on two sides of the main hull, the main hull is provided with a cabin, and a power system is arranged in the cabin;
the first secondary hull and the second secondary hull are both made of polyethylene material; alternatively, the first and second electrodes may be,
the first secondary hull and the second secondary hull both comprise a metal frame structure and a polyethylene protective layer wrapping the metal frame structure.
2. Trimaran according to claim 1, characterized in that the outer surface of the main hull is provided with a protective layer of polyethylene.
3. The trimaran of claim 1, wherein the power system comprises a main engine power system and an auxiliary engine power system, the main engine power system being disposed at a middle rear portion of the main hull, the auxiliary engine power system being disposed at a front portion of the main hull.
4. Trimaran according to claim 1, characterized in that the power system comprises:
the gas turbine generator set comprises a gas turbine engine and an electric motor, wherein the gas turbine engine is connected with the electric motor, and the gas turbine engine can drive the electric motor to generate electricity;
an electric motor electrically connected to the motor, the electric motor generating electric power that can be input to the electric motor;
a propulsion system coupled to the electric motor, the propulsion system further coupled to the gas turbine engine, the propulsion system being drivable by the electric motor and/or the gas turbine engine.
5. Trimaran according to claim 4, characterized in that the power system further comprises an energy storage system, which is electrically connected with the electric motor and the electric machine, respectively;
the electric energy generated by the electric machine may be input to the energy storage system, and the electric energy stored by the energy storage system may be input to the electric motor.
6. Trimaran according to claim 5, characterized in that the power system further comprises a current converter, by means of which the electric machine is electrically connected with the electric motor and the energy storage system, respectively;
and/or the presence of a gas in the gas,
the electric machine is a starting integrated electric machine, and the electric energy stored by the energy storage system can be input into the electric machine so that the electric machine can be used as a motor to drive the gas turbine engine.
7. Trimaran according to claim 4, characterized in that the gas turbine engine comprises a compressor, a turbine and a combustion chamber, the electric machine, the compressor and the turbine being connected by a shaft, the combustion chamber being arranged between the compressor and the turbine, the shaft, the electric machine, the compressor and the turbine forming a rotor system of the gas turbine generator set; wherein the content of the first and second substances,
the shaft body of the rotating shaft is of an integrated structure, and the rotating shaft is horizontally arranged;
the rotating shaft is also provided with a thrust bearing and at least two radial bearings, and the thrust bearing and the at least two radial bearings are non-contact bearings;
the thrust bearing is arranged at a preset position on one side of the turbine close to the compressor, and the preset position is a position which can enable the gravity center of the rotor system to be located between two radial bearings which are farthest away from each other in the at least two radial bearings; or the generator, the thrust bearing and the at least two radial bearings are all arranged in a first casing, and the compressor and the turbine are arranged in a second casing; the impeller of the compressor and the impeller of the turbine are arranged in the second casing in an abutting mode; the first case is connected with the second case.
8. Trimaran according to claim 4, characterized in that the shaft of the gas turbine engine is connected to the propulsion system by means of a transmission governor.
9. Trimaran according to claim 4, characterized in that the bottom of the main hull is further provided with a pressure tank, the tank bottom of which has a number of injection holes, the pressure tank communicating with an exhaust duct of a gas turbine engine in the power system, a one-way valve being arranged between the exhaust duct and the pressure tank.
10. Trimaran according to claim 9, characterized in that the bilge of the pressure tank is made of a porous material.
11. Trimaran according to claim 10, characterized in that the floor of the pressure tank is made of foamed aluminium alloy or foamed magnesium alloy.
12. Trimaran according to claim 9, characterized in that the exhaust gas duct of the gas turbine engine is provided with a pressure boosting device for boosting the pressure of the gas entering the pressure tank.
13. A trimaran comprises a main hull, a first auxiliary hull and a second auxiliary hull, and is characterized in that the main hull is provided with a cabin, a power system is arranged in the cabin, and a power source of the power system is a gas turbine engine;
the bottom of the main ship body is also provided with a pressure cabin, the cabin bottom of the pressure cabin is provided with a plurality of jet holes, the pressure cabin is communicated with an exhaust pipeline of the gas turbine engine, and a one-way valve is arranged between the exhaust pipeline and the pressure cabin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811220858.3A CN111071384A (en) | 2018-10-19 | 2018-10-19 | Three-body ship |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811220858.3A CN111071384A (en) | 2018-10-19 | 2018-10-19 | Three-body ship |
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| CN111071384A true CN111071384A (en) | 2020-04-28 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115264646A (en) * | 2022-08-09 | 2022-11-01 | 珠海格力电器股份有限公司 | Water fetching fan blade, water fetching motor and air conditioner |
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2018
- 2018-10-19 CN CN201811220858.3A patent/CN111071384A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115264646A (en) * | 2022-08-09 | 2022-11-01 | 珠海格力电器股份有限公司 | Water fetching fan blade, water fetching motor and air conditioner |
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