A self-heating inertial stage blade that automatically adjusts the size of the water delivery trough and the thickness of the blades according to the airflow velocity.

Abstract

This invention automatically adjusts the blade thickness and water delivery channel size according to the airflow velocity. By changing the spacing of the inertial stage blades and the size of the water delivery channel, it regulates the inertial stage blades' ability to capture and transport droplets, thus solving the problem of water delivery channel clogging and ensuring high air-water separation efficiency under different airflow velocity conditions. Simultaneously, without requiring additional energy input, when the incoming air temperature drops below 0°C, the inertial stage blades generate heat through friction and collision, forming spherical protrusions on their surface as the self-heating coating expands upon cooling. This raises the blade wall temperature, solving the problem of icing in low-temperature environments and ensuring optimal aerodynamic characteristics and air-water separation efficiency. This invention features a simple structure, convenient processing, high efficiency and reliability, and low cost.

Description

Technical Field

[0001] This invention belongs to the technical field of inertial stage blades in air intake filtration devices, specifically relating to a self-heating inertial stage blade that automatically changes the size of the water tank and the thickness of the blade according to the airflow speed. Background Technology

[0002] Inertial stage blades are key components installed within the air filtration system of a gas turbine. They are used to filter out solid and liquid particles, as well as impurities such as salt spray aerosols, from the air intake of the gas turbine, primarily targeting salt spray liquid particles floating in marine environments. With the rapid development of gas turbine design and manufacturing technology, the output power of gas turbines is continuously increasing, and their inlet airflow is also increasing accordingly. Taking GE's LM2500 series gas turbine as an example, the output power and inlet airflow data are shown in Table 1.

[0003] Table 1. Output Power and Inlet Airflow Data for LM2500 Series Gas Turbines

[0004]

[0005] Table 1 shows that as the output power of the LM2500 series gas turbines increases, so does their inlet airflow. Due to the space constraints of the marine gas turbine intake system, with a constant intake flow area, the airflow velocity through the inertial stage blades of the intake filter increases accordingly with the increase of the inlet airflow. Furthermore, when the gas turbine rapidly transitions from low to high operating conditions, the velocity of the airflow through the inertial stage blades also increases. With this increased airflow velocity, the amount of salt spray droplets carried in the incoming air per unit time increases dramatically, placing immense pressure on the instantaneous water purification capacity of the inertial stage blades. Currently, the inertial stage blades use a deflected water channel structure to capture and collect liquid particles from the incoming air to improve the gas turbine's intake air quality. However, when the number of liquid particles in the air increases dramatically, the purification efficiency of the inertial stage blades is severely affected. On the one hand, droplets spread and form a liquid film on the inner wall of the water delivery tank, making it impossible for them to fall under gravity and be effectively collected. On the other hand, droplets may experience "secondary splashing" on the outer wall due to the high-speed airflow, re-incorporating incoming air and reducing the quality of the intake air. In addition, the accumulation of droplets can cause the water delivery tank to become clogged in a short period of time, weakening its ability to capture and transport droplets, thereby further threatening the stable operation of the gas turbine.

[0006] Meanwhile, as ships sail into the open ocean and the polar regions, the operating environment for marine gas turbines becomes increasingly harsh. Faced with extreme sea conditions such as giant waves, freezing rain, and blizzards, the gas turbine intake air will contain large amounts of salt spray, supercooled water droplets, and ice crystals. This will cause severe icing problems on the inertial stage blades, significantly impacting their aerodynamic drag and air-water separation efficiency. When ships navigate in low-temperature waters, supercooled droplets and ice crystals generated by sea spray, freezing rain, and snow are captured by the inertial stage blades and freeze rapidly. Within a short time, ice accumulates extensively on the blade surface, severely clogging the water channels of the inertial stage blades. This significantly reduces the channels' ability to capture and transport droplets, leading to a severe decline in the air-water separation efficiency of the inertial stage blades, ultimately failing to meet the gas turbine's intake air quality requirements. Furthermore, when the ice buildup is too large, it is prone to breakage. The broken ice fragments can then enter the gas turbine's intake system with the high-speed airflow, easily causing mechanical damage to intake system components and gas turbine inlet components, seriously threatening the gas turbine's operational safety. Therefore, icing on the inertial stage blades severely affects the efficient, stable, and safe operation of the gas turbine.

[0007] Based on the design principles of inertial stage blades, while increasing blade thickness or enlarging the size of the water delivery channel can improve droplet separation efficiency and address issues under high flow rates and large water volumes, this also increases aerodynamic drag, leading to a loss of total intake pressure and failing to meet the daily operational requirements of the gas turbine. Conversely, using thinner blades or conventionally sized water delivery channels, while reducing aerodynamic drag, results in insufficient separation efficiency and delivery capacity under high flow rates and large droplet volumes, failing to guarantee intake air quality under various operating conditions. Furthermore, current mature anti-icing measures include bleed-air devices that use high-temperature steam from boilers to raise the intake air temperature, and electric heating films applied to the surface of the inertial stage blades to raise their surface temperature. Both methods require the ship's propulsion system to provide additional energy input to the specific anti-icing devices and necessitate manual operation by professionals to activate, deactivate, and regulate the power of these devices. In addition, the complex bleed-air structure also generates additional aerodynamic drag losses for the overall intake system. All external anti-icing devices negatively impact the efficient and stable operation of the gas turbine. Therefore, it is necessary to develop a self-heating air intake filter that can automatically adjust the blade thickness and water tank size according to the incoming air velocity, so as to continuously improve the purification and separation efficiency of the inertial stage blades without significantly increasing the drag loss, solve the problem of icing on the inertial stage blades, and ensure the long-term stable and efficient operation of the gas turbine. Summary of the Invention

[0008] The purpose of this invention is to provide a self-heating inertial stage blade that automatically changes the size of the water delivery tank and the thickness of the blade according to the airflow speed. Under the condition of a large amount of salt spray liquid particles in the air intake, it can quickly transport liquid particles and continuously capture and adsorb liquid droplet particles, and ensure that the inertial stage blade does not freeze in cold sea areas, thereby improving the intake quality of the gas turbine.

[0009] A self-heating inertial stage blade that automatically adjusts the size of the water delivery trough and the blade thickness according to airflow velocity is used for separating air-water mixtures ranging from -10℃ to 0℃. The inertial stage blade includes an inlet guide plate, an outlet guide plate, and a water delivery unit. Multiple water delivery units are included, each containing a transition guide plate and a water delivery trough. The inlet guide plate, outlet guide plate, and transition guide plates of each water delivery unit all employ the same three-layer sandwich structure, comprising an upper metal material plate, a central core structure plate, and a lower metal material plate. Microporous structures are evenly distributed on both the upper and lower metal material plates. The central core structure plate is made of a first thermosensitive shrinkage composite material. When the airflow velocity exceeds a critical value, the surface temperature of the inertial stage blade is lower than that of the first thermosensitive shrinkage composite material. The critical value of the shrinkage composite material means that the central core layer structure plate only changes size in the vertical direction, causing the blade thickness of the inertial stage to change. The water delivery tanks of each group of water delivery units use the same second thermosensitive shrinkage composite material. When the airflow velocity is greater than the critical value, the surface temperature of the water delivery tank is lower than the critical value of the second thermosensitive shrinkage composite material, and the water delivery tank only changes size in the length direction. The outer walls of the inlet guide plate, outlet guide plate, and transition guide plate of each group of water delivery units are provided with a self-heating coating. After the self-heating coating comes into contact with the cold airflow below the temperature critical value, it undergoes a shaping expansion. The elastic spherical protrusions formed by the expansion collide and rub against each other under the influence of the airflow, generating heat and ensuring that the surface of the inertial stage blade does not freeze.

[0010] Furthermore, multiple sets of inertial stage blades are arranged vertically facing the direction of the incoming airflow, with each set of inertial stage blades parallel to each other and maintaining a distance between them. An airflow channel is formed between two adjacent sets of inertial stage blades. The inlet guide plate and the outlet guide plate are arranged parallel to the direction of the incoming airflow, and the opening of the water conveying tank of each water conveying unit faces the direction of the incoming airflow.

[0011] Furthermore, the installation angle between the inlet guide plate and the transition guide plate ranges from 135° to 165°; the installation angle between the transition guide plates of adjacent water conveyance units ranges from 90° to 150°.

[0012] Furthermore, in the initial state, the thickness of the inlet guide plate, the outlet guide plate, and the transition guide plate of each water conveying unit is L. The thickness of the upper metal material plate and the lower metal material plate is the same. The thickness L1 of the central core layer structure plate is L1∈[0.3L,0.5L]. Under the influence of the airflow velocity, the thickness of the central core layer structure plate is automatically adjusted within the range of L1 to 8.5L1.

[0013] Furthermore, the first thermosensitive shrinkage composite material constituting the central core layer structure is designed based on the actual operating conditions of the inertial stage blade. If the maximum airflow velocity in the operating conditions is known to be x... max The first thermosensitive anisotropic shrinkage composite material is designed to satisfy the following deformation formula:

[0014]

[0015] Where y1(x) is the deformation of the first thermosensitive anisotropic shrinkage composite material, x is the airflow velocity; x1 is the critical airflow velocity at which the first thermosensitive anisotropic shrinkage composite material begins to deform, x1 = x max / 1.8; x2 is the airflow velocity that causes the first thermosensitive anisotropically shrinking composite material to deform, that is, after x > x2, the first thermosensitive anisotropically shrinking composite material no longer expands, x2 = x max ; a is the deformation parameter of the first thermosensitive anisotropic composite material, a=1±0.2.

[0016] Furthermore, in the initial state, the length L2 of the water conveying tank of each group of water conveying units is L2∈[8L,10L]. Under the influence of airflow velocity, the length of the water conveying tank of each group of water conveying units is automatically adjusted within the range of L2 to 1.375L2.

[0017] Furthermore, the second thermosensitive shrinkable composite material constituting the water conveyance tank of each water conveyance unit is designed according to the actual application conditions of the inertial stage blades. If the maximum airflow velocity in the application conditions is known to be x... max Then, the design of the second thermosensitive anisotropic shrinkage composite material satisfies the following deformation formula:

[0018]

[0019] Where y2(x) is the deformation of the second thermosensitive anisotropic composite material, and b is the deformation parameter of the second thermosensitive anisotropic composite material, b=0.8±0.1.

[0020] Furthermore, a transition section is provided between the water conveying tank and the transition guide plate, and the length of the transition section is 0.8L to L.

[0021] Furthermore, the critical temperature for the self-heating coating to undergo shape expansion is 0℃~2℃, the thickness of the self-heating coating is 0.15L~0.25L, the diameter of the elastic spherical protrusions after the self-heating coating has undergone shape expansion is 0.1L~0.3L, and the spacing between the elastic spherical protrusions is 0.15L~0.25L.

[0022] The beneficial effects of this invention are as follows:

[0023] This invention automatically adjusts the blade thickness and water delivery channel size according to the airflow velocity. By changing the spacing of the inertial stage blades and the size of the water delivery channel, it regulates the inertial stage blades' ability to capture and transport droplets, thus solving the problem of water delivery channel clogging and ensuring high air-water separation efficiency under different airflow velocity conditions. Simultaneously, without requiring additional energy input, when the incoming air temperature drops below 0°C, the inertial stage blades generate heat through friction and collision, forming spherical protrusions on their surface as the self-heating coating expands upon cooling. This raises the blade wall temperature, solving the problem of icing in low-temperature environments and ensuring optimal aerodynamic characteristics and air-water separation efficiency. This invention features a simple structure, convenient processing, high efficiency and reliability, and low cost. Attached Figure Description

[0024] Figure 1a This is a two-dimensional structural schematic diagram of the present invention.

[0025] Figure 1b This is a partially enlarged structural schematic diagram of the present invention.

[0026] Figure 2a This is a schematic diagram of the inertial stage blade structure when the water delivery channel length is 8.3mm (not extended).

[0027] Figure 2b This is a schematic diagram of the inertial stage blade structure when the water delivery channel length is 9.8mm (1.5mm elongation).

[0028] Figure 2c This is a schematic diagram of the inertial stage blade structure when the water delivery channel is 11.3 mm long (3.0 mm elongation).

[0029] Figure 3a This is a schematic diagram of the inertial stage blade structure when the blade thickness is 1.2 mm (unextended).

[0030] Figure 3b This is a schematic diagram of the inertial stage blade structure when the blade thickness is 2.2 mm (1 mm elongation).

[0031] Figure 3c This is a schematic diagram of the inertial stage blade structure when the blade thickness is 3.2 mm (2 mm elongation).

[0032] Figure 4a This is a schematic diagram of the self-heating coating structure on the flat plate.

[0033] Figure 4b This is a schematic diagram of the self-heating coating structure at the bend.

[0034] Figure 5 These are diagrams showing the velocity field and droplet trajectory distribution within the inertial stage blade channel. (a) shows the velocity field distribution within the inertial stage blade channel when the water tank length is 8.3 mm and the blade thickness is 1.2 mm (unextended); (b) shows the droplet trajectory distribution within the corresponding inertial stage blade channel; (c) shows the velocity field distribution within the inertial stage blade channel when the blade thickness is 3.2 mm (extended by 2 mm); (d) shows the droplet trajectory distribution within the corresponding inertial stage blade channel; (e) shows the velocity field distribution within the inertial stage blade channel when the water tank length is 11.3 mm (extended by 3.0 mm); and (f) shows the droplet trajectory distribution within the corresponding inertial stage blade channel.

[0035] Figure 6 This is a schematic diagram of the two-dimensional arrangement of the present invention in the installed state. Detailed Implementation

[0036] The present invention will now be further described with reference to the accompanying drawings.

[0037] This invention provides a self-heating inertial stage blade that automatically adjusts the size of the water delivery trough and the blade thickness according to the airflow velocity, applicable to the separation of air-water mixtures at temperatures ranging from -10°C to 0°C. The inertial stage blade includes an inlet guide plate, an outlet guide plate, and a water delivery unit. The installation angle between the inlet guide plate and the transition guide plate ranges from 135° to 165°; the installation angle between the transition guide plates of adjacent water delivery units ranges from 90° to 150°. A transition section with a length of 0.8L to L is provided between the water delivery trough and the transition guide plate.

[0038] Multiple sets of inertial stage blades are arranged vertically facing the direction of airflow. Each set of inertial stage blades is parallel to each other and maintains a distance. An airflow channel is formed between two adjacent sets of inertial stage blades. The inlet guide plate and the outlet guide plate are arranged parallel to the direction of airflow. The opening of the water conveying tank of each water conveying unit faces the direction of airflow.

[0039] The water conveying unit includes a transition guide plate and a water conveying trough. The inlet guide plate, outlet guide plate, and transition guide plates of each group of water conveying units all adopt the same three-layer sandwich structure, including an upper metal material plate, a central core structure plate, and a lower metal material plate. Microporous structures are evenly distributed on the upper and lower metal material plates. The central core structure plate adopts a first thermosensitive shrinkage composite material. When the airflow velocity is greater than the critical value, the surface temperature of the inertial stage blade is lower than the critical value of the first thermosensitive shrinkage composite material. The central core structure plate only undergoes dimensional changes in the vertical direction, causing changes in the blade thickness of the inertial stage blade. The water conveying troughs of each group of water conveying units adopt the same second thermosensitive shrinkage composite material. When the airflow velocity is greater than the critical value, the surface temperature of the water conveying trough is lower than the critical value of the second thermosensitive shrinkage composite material. The water conveying trough only undergoes dimensional changes in the length direction.

[0040] The outer walls of the inlet guide vane, outlet guide vane, and transition guide vanes of each water conveyance unit are equipped with a self-heating coating. Upon contact with cold airflow below the critical temperature value, the self-heating coating undergoes a shape-stabilizing expansion. The resulting elastic spherical protrusions collide and rub against each other under the influence of the airflow, generating heat and preventing icing on the surface of the inertial stage blades. The critical temperature for the shape-stabilizing expansion of the self-heating coating is 0℃~2℃, the thickness of the self-heating coating is 0.15L~0.25L, the diameter of the elastic spherical protrusions after shape-stabilizing expansion is 0.1L~0.3L, and the spacing between the elastic spherical protrusions is 0.15L~0.25L.

[0041] Initially, the thickness of the inlet guide plate, outlet guide plate, and transition guide plates of each water conveying unit is L. The thickness of the upper and lower metal material plates is the same. The thickness L1 of the central core structure plate is L1∈[0.3L,0.5L]. Under the influence of airflow velocity, the thickness of the central core structure plate automatically adjusts within the range of L1 to 8.5L1. Initially, the length L2 of the water conveying tank of each water conveying unit is L2∈[8L,10L]. Under the influence of airflow velocity, the length of the water conveying tank of each water conveying unit automatically adjusts within the range of L2 to 1.375L2.

[0042] The thermosensitive non-contractile composite material is designed based on the actual operating conditions of the inertial stage blade. If the maximum airflow velocity in the operating conditions is known to be x... max The first thermosensitive anisotropic shrinkage composite material is designed to satisfy the following deformation formula:

[0043]

[0044] Where y1(x) is the deformation of the first thermosensitive anisotropic shrinkage composite material, x is the airflow velocity; x1 is the critical airflow velocity at which the first thermosensitive anisotropic shrinkage composite material begins to deform, x1 = x max / 1.8; x2 is the airflow velocity that causes the first thermosensitive anisotropically shrinking composite material to deform, that is, after x > x2, the first thermosensitive anisotropically shrinking composite material no longer expands, x2 = x max ; a is the deformation parameter of the first thermosensitive anisotropic composite material, a=1±0.2.

[0045] The second thermosensitive heteroswell composite material is designed to satisfy the following deformation formula:

[0046]

[0047] Where y2(x) is the deformation of the second thermosensitive anisotropic composite material, and b is the deformation parameter of the second thermosensitive anisotropic composite material, b=0.8±0.1.

[0048] Example 1:

[0049] like Figure 1a As shown, the inertial stage blades consist of four water delivery units. The inlet guide plate 1 is connected to the first water delivery tank 3 via a first transition guide plate 2. The first water delivery tank 3 is connected to the second water delivery tank 5 via a second transition guide plate 4. The second water delivery tank 5 is connected to the third water delivery tank 7 via a third transition guide plate 6. The third water delivery tank 7 is connected to the fourth water delivery tank 9 via a fourth transition guide plate 8. The fourth water delivery tank 9 is connected to the outlet guide plate 10. The inertial stage blades have a uniform thickness of L.

[0050] like Figure 1b As shown, the first water delivery channel 3, the second water delivery channel 5, the third water delivery channel 7, and the fourth water delivery channel 9 of the inertial stage blade are made of thermosensitive anisotropic composite material. The water delivery channel structure only undergoes dimensional changes in the length direction, with no significant dimensional changes in other directions. The water delivery channels are installed in the normal direction of the transition guide plate, at a distance of 0.8L to 1.0L from the outer surface of the transition guide plate. The installation line of the composite material and the metal material of the transition guide plate is parallel to the tangent direction of the transition guide plate. The inertial stage blade inlet guide plate 1, the first transition guide plate 2, the second transition guide plate 4, the third transition guide plate 6, the fourth transition guide plate 8, and the outlet guide plate 10 are a three-layer sandwich structure. The upper and lower layers of each plate are made of metal material, and a large number of microporous structures are evenly distributed on the metal material plates. The core layer is made of thermosensitive anisotropic composite material 11, and the core layer structure only undergoes dimensional changes in the direction perpendicular to the incoming flow, with no significant dimensional changes in other directions. When no deformation occurs, the thickness of the core structure plate is 0.3L to 0.5L. At this time, the thickness ratio of the upper metal plate, the core composite material plate, and the lower metal plate in the thickness direction of the inertial stage blade is 3:4:3.

[0051] like Figure 4a and Figure 4bAs shown, a self-heating coating 12 is applied to the surfaces of the inertial stage blades, specifically the inlet guide vane 1, the first transition guide vane 2, the second transition guide vane 4, the third transition guide vane 6, the fourth transition guide vane 8, and the outlet guide vane 10. The coating thickness is approximately 0.2L. When the ambient temperature is below 0℃, the self-heating coating begins to undergo shape-stabilizing expansion. This forms regularly arranged, uniformly sized, and fixed-shape micro-spherical protrusions on the surface of the inertial stage blades. The diameter of these elastic spherical protrusions after shape-stabilizing expansion is 0.1L to 0.3L, and the spacing between them is 0.15L to 0.25L. These spherical protrusions can undergo random movement under the influence of the intake airflow. The random collisions and friction between these protrusions generate a large amount of heat energy, thus increasing the temperature of the inertial stage blade wall. There is no self-heating coating on the water tank wall.

[0052] like Figure 6 As shown, each inertial stage blade consists of inlet and outlet guide vanes, four water channels, and four transition guide vanes. The overall length of the blade along the flow direction is approximately 100L to 120L, and the blade thickness is uniform. Several blades are arranged perpendicularly to the airflow direction. The inlet guide vane 1 and the outlet guide vane 10 are arranged parallel to the airflow direction. The blades are parallel to each other and maintain equal spacing, with a blade spacing of 10.0L. To suppress airflow separation, the inlet edge of the inlet guide vane 1 and the outlet edge of the outlet guide vane 10 are rounded, rather than sharp straight edges. The inlet guide vane 1 is connected to the first transition guide vane 2 by a rounded arc, with an installation angle range of 135° to 180°. The outlet guide vane 10 is connected to the fourth transition guide vane 8 by a rounded arc, with an installation angle range of 135° to 180°.

[0053] Compared to traditional inertial stage blades, this invention can automatically adjust the thickness of the inertial stage blades and the size of the water delivery channel according to the incoming air velocity, thereby regulating the inertial stage blades' ability to capture and transport droplets and ensuring high gas-water separation efficiency under different intake conditions. This solves the problem of decreased intake air quality in gas turbines caused by a sharp increase in the number of droplets in the incoming air as the intake air velocity increases. It also addresses the problem of increased drag loss caused by the larger thickness of the inertial stage blades and the larger size of the water delivery channel during normal gas turbine operation. Furthermore, this invention can generate its own heat when the incoming air temperature drops below 0°C, without requiring additional energy input. The self-heating coating on the surface of the inertial stage blades expands upon cooling, forming spherical protrusions that generate heat through friction and collision, thus raising the blade wall temperature and solving the problem of icing in inertial stage blades in low-temperature environments. This comprehensively improves the purification and separation efficiency of the inertial stage blades. This invention has advantages such as simple structure, convenient processing, high efficiency and reliability, and low cost.

[0054] Table 2 Performance test data of traditional inertial stage blades

[0055]

[0056] As shown in Table 2, aerodynamic separation tests using traditional inertial stage blades revealed that as the inlet air velocity increases, the drag loss of the traditional inertial stage blades increases, and the air-water separation efficiency decreases due to blockage of the water delivery channel. Figure 2a , Figure 2b , Figure 2c As shown in Table 3, although the increase in the size of the water delivery tank increases the drag loss of the inertial stage blades, its separation efficiency recovers significantly, reaching and exceeding the separation efficiency of traditional inertial stage blades under normal stable operating conditions. Figure 5 As shown in (a), (b), (e), and (f), with the increase in the size of the inertial stage blade water delivery channel, the airflow velocity inside the inertial stage blade channel increases, and more incoming liquid droplets are captured and transported by the water delivery channel, thus improving the gas-liquid separation efficiency. (See Table 4 and...) Figure 3a , Figure 3b , Figure 3c As shown, while increasing the blade thickness increases the drag loss of the inertial stage blade, it also significantly restores its separation efficiency, reaching and exceeding the separation efficiency of traditional inertial stage blades under stable daily operating conditions. Figure 5 As shown in (a), (b), (c), and (d), as the thickness of the inertial stage blades increases, the airflow velocity inside the inertial stage blade channel increases, and more incoming liquid droplets are captured and transported by the water delivery tank, thus improving the gas-liquid separation efficiency.

[0057] Table 3. Simulation data of the inertial stage blade performance of the present invention under high-speed, high-volume air intake conditions.

[0058]

[0059] Table 4. Simulation data of the inertial stage blade performance of the present invention under high-speed, high-volume air intake conditions.

[0060]

[0061] This invention is used in the field of ship air intake filtration in offshore marine environments, and its specific functions are as follows:

[0062] When ships sail at sea, the air intake contains a large amount of seawater droplets, salt, and aerosols. Salt is primarily dissolved in the droplet particles. Inertial stage blades utilize the principle of inertial separation for gas-liquid separation. The mass of a unit volume of air is much smaller than the mass of a unit volume of droplets. When airflow passes through the curved flow path of the inertial stage blades, the air can easily change its direction, while the droplets, influenced by inertia, maintain their original motion. This causes the droplets to impact the blade wall, forming a water film. This water film converges and flows downstream along the blade wall, entering the drainage channel where it is separated at the bottom under gravity. Furthermore, when ships sail in the Antarctic and Arctic Oceans, the extremely low ambient temperatures and supercooled droplets in the air can cause icing on marine inertial stage blades. Icing on the inertial stage blades can severely clog the engine's air intake passages, reducing gas-liquid separation efficiency and affecting the safe, stable, and efficient operation of the gas turbine. Currently, mature solutions for addressing icing problems in marine inertial stage blades all require external energy input. This invention relies on a water delivery trough and core layer made of a thermosensitive, non-shrinkable composite material, and inertial stage blades with a self-heating coating. It can automatically adjust the size of the water delivery trough and the thickness of the blades according to the airflow velocity, and self-heat to increase the surface temperature of the blades. This ensures that the inertial stage blades maintain high air-water separation efficiency under different air intake conditions.

[0063] When a high-power gas turbine is installed, or when the gas turbine rapidly maneuvers to increase output power, the gas turbine's intake airflow increases, the incoming air velocity to the inertial stage blades increases, and the droplet content in the incoming airflow increases dramatically. This enhances convective heat transfer on the inertial stage blade surface, leading to a decrease in blade surface temperature. When the incoming air velocity increases to a critical value (5 m / s), the thermosensitive anisotropic composite material with different expansion coefficients receives the signal of increased airflow velocity and decreased wall temperature. The thermosensitive anisotropic composite material expands, causing the water delivery channel to expand along its length, thus increasing its size. The blades also expand perpendicular to the incoming flow direction, increasing their thickness and improving the water delivery capacity and separation efficiency of the inertial stage blades. However, as the size of the water delivery channel increases, the flow space through the channel gaps decreases, further increasing the flow velocity and raising the drag loss of the inertial stage blades. Therefore, by sacrificing some drag characteristics, the gas-water separation efficiency under high flow velocity conditions is significantly improved, ensuring the gas turbine's intake air quality.

[0064] When a ship is sailing under normal operating conditions, the intake airflow of the gas turbine decreases, the incoming air velocity of the inertial stage blades decreases, the incoming droplet content decreases, the convective heat transfer on the surface of the inertial stage blades weakens, and the blade surface temperature rises. When the incoming air velocity is below the critical value (5m / s), the size of the water channel made of thermosensitive shrinkage composite material decreases, the blade thickness decreases, the airflow space increases, and the airflow velocity decreases. While ensuring the separation efficiency of the inertial stage blades, the pressure loss is reduced, ensuring the requirements of the gas turbine for total intake pressure loss during long-term operation.

[0065] Meanwhile, when ships navigate in low-temperature sea areas such as the Antarctic and Arctic, when the ambient temperature is below 0°C, the self-heating coating on the blade surface undergoes cooling and expansion, forming numerous elastic spherical protrusions on the inertial stage blade surface. These protrusions move randomly under the influence of the intake airflow, and the random collisions and friction between them generate a large amount of heat energy, thus raising the surface temperature of the inertial stage blade. When the ambient temperature is above 0°C, the self-heating coating contracts upon heating, resulting in a smooth and flat surface with good aerodynamic characteristics, ensuring the drag characteristics and gas-liquid separation efficiency of the inertial stage blade. Ultimately, this improves the overall gas-liquid separation efficiency of the inertial stage blade under complex intake conditions, thus improving the intake quality of the gas turbine.

[0066] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A self-heating inertial stage blade that automatically changes the size of the water delivery channel and the blade thickness according to the airflow velocity, characterized in that: This system is applied to separate air-water mixtures ranging from -10℃ to 0℃. The inertial stage blades include an inlet guide vane, an outlet guide vane, and a water delivery unit. Multiple water delivery units are included, each containing a transition guide vane and a water delivery trough. The inlet guide vane, outlet guide vane, and transition guide vanes of each water delivery unit all employ the same three-layer sandwich structure, comprising an upper metal material plate, a central core structure plate, and a lower metal material plate. Microporous structures are evenly distributed on both the upper and lower metal material plates. The central core structure plate utilizes a first thermosensitive anisotropic shrinkage composite material. When the airflow velocity exceeds a critical value, the surface temperature of the inertial stage blades falls below the critical value of the first thermosensitive anisotropic shrinkage composite material, thus activating the central core structure. The structural plates only change size in the vertical direction, causing changes in the blade thickness of the inertial stage blades. The water delivery channels of each water delivery unit use the same second thermosensitive shrinkage composite material. When the airflow velocity is greater than the critical value, the surface temperature of the water delivery channel is lower than the critical value of the second thermosensitive shrinkage composite material, and the water delivery channel only changes size in the length direction. The outer walls of the inlet guide plate, outlet guide plate, and transition guide plate of each water delivery unit are provided with a self-heating coating. After the self-heating coating comes into contact with the cold airflow below the temperature critical value, it undergoes a shape-setting expansion. The elastic spherical protrusions formed by the expansion collide and rub against each other under the influence of the airflow, generating heat and ensuring that the surface of the inertial stage blades does not freeze.

2. The self-heating inertial stage blade that automatically changes the size of the water delivery channel and the blade thickness according to the airflow velocity as described in claim 1, characterized in that: Multiple sets of inertial stage blades are arranged vertically facing the direction of airflow. Each set of inertial stage blades is parallel to each other and maintains a distance. An airflow channel is formed between two adjacent sets of inertial stage blades. The inlet guide plate and the outlet guide plate are arranged parallel to the direction of airflow. The opening of the water conveying tank of each water conveying unit faces the direction of airflow.

3. The self-heating inertial stage blade that automatically changes the size of the water delivery channel and the blade thickness according to the airflow velocity as described in claim 1, characterized in that: The installation angle between the inlet guide plate and the transition guide plate is 135° to 165°; the installation angle between the transition guide plates of adjacent water conveyance units is 90° to 150°.

4. The self-heating inertial stage blade that automatically changes the size of the water delivery trough and the blade thickness according to the airflow velocity as described in claim 1, characterized in that: In the initial state, the thickness of the inlet guide plate, the outlet guide plate, and the transition guide plate of each water conveying unit is L. The thickness of the upper metal material plate and the lower metal material plate is the same. The thickness L1 of the central core layer structure plate is L1∈[0.3L,0.5L]. Under the influence of the airflow velocity, the thickness of the central core layer structure plate is automatically adjusted within the range of L1 to 8.5L1.

5. A self-heating inertial stage blade that automatically changes the size of the water delivery trough and the blade thickness according to the airflow velocity, as described in claim 4, is characterized in that: The first thermosensitive, non-shrinkable composite material constituting the central core layer structure is designed based on the actual operating conditions of the inertial stage blade. If the maximum airflow velocity in the operating conditions is known to be x... max The first thermosensitive anisotropic shrinkage composite material is designed to satisfy the following deformation formula: Where y1(x) is the deformation of the first thermosensitive anisotropic composite material, x is the airflow velocity; x1 is the critical airflow velocity at which the first thermosensitive anisotropic composite material begins to deform, x1 = x max / 1.8; x2 is the airflow velocity that causes the first thermosensitive anisotropic shrinkage composite material to deform, that is, after x > x2, the first thermosensitive anisotropic shrinkage composite material no longer expands, x2 = x max ; a is the deformation parameter of the first thermosensitive anisotropic composite material, a=1±0.

2.

6. The self-heating inertial stage blade that automatically changes the size of the water delivery trough and the blade thickness according to the airflow velocity as described in claim 5, characterized in that: In the initial state, the length L2 of the water conveying tank of each group of water conveying units is L2∈[8L,10L]. Under the influence of airflow velocity, the length of the water conveying tank of each group of water conveying units is automatically adjusted within the range of L2 to 1.375L2.

7. A self-heating inertial stage blade that automatically changes the size of the water delivery trough and the blade thickness according to the airflow velocity, as described in claim 6, is characterized in that: The second thermosensitive shrinkable composite material of the water conveyance tank that constitutes each water conveyance unit is designed according to the actual application conditions of the inertial stage blades. If the maximum airflow velocity in the application conditions is known to be x... max Then, the design of the second thermosensitive anisotropic shrinkage composite material satisfies the following deformation formula: Where y2(x) is the deformation of the second thermosensitive anisotropic composite material, and b is the deformation parameter of the second thermosensitive anisotropic composite material, b=0.8±0.

1.

8. The self-heating inertial stage blade that automatically changes the size of the water delivery channel and the blade thickness according to the airflow velocity as described in claim 1, characterized in that: A transition section is provided between the water conveying tank and the transition guide plate, and the length of the transition section is 0.8L to L.

9. A self-heating inertial stage blade that automatically changes the size of the water delivery trough and the blade thickness according to the airflow moisture content, as described in claim 1, is characterized in that: The critical temperature for the self-heating coating to undergo shape expansion is 0℃~2℃, the thickness of the self-heating coating is 0.15L~0.25L, the diameter of the elastic spherical protrusions after the self-heating coating has undergone shape expansion is 0.1L~0.3L, and the spacing between the elastic spherical protrusions is 0.15L~0.25L.

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