Gas compressor moving blade, gas compressor and gas turbine

Abstract

The moving blade comprises a blade root, a blade body and a moving blade thinning tooth, the moving blade thinning tooth comprises a dissolving layer and a protective layer, the blade body is provided with a first end and a second end which are oppositely arranged, the first end is connected with the blade root, the dissolving layer is arranged at the second end of the blade body, and the protective layer is arranged at the second end of the blade body. The dissolving layer can be dissolved when exposed to a humid and high-temperature environment so as to reduce the abrasion resistance between the second end and the cylinder wall of the air cylinder, the protective layer wraps the peripheral side of the dissolving layer, and the protective layer is used for being abraded and / or falling off to expose the dissolving layer when the moving blade of the gas compressor makes contact with the cylinder wall. According to the movable blade of the gas compressor, rigid collision between the movable blade and the cylinder wall of the air cylinder can be avoided, the situation that the blade is prone to breakage due to the rigid effect is avoided, the running safety and reliability of a gas turbine are improved, and secondly, a smaller blade tip gap can be adopted when the blade is assembled, and the assembling compactness is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and particularly to a compressor moving blade, a compressor and a gas turbine. Background Art

[0002] During the operation of a gas turbine, problems such as excessive rotor vibration, rotor center change or serious deformation may occur. At this time, due to these changes in the rotor, a rubbing problem will occur between the tip of the moving blade on the rotor and the cylinder wall of the cylinder. In severe cases, it may even cause the fracture of the moving blade, seriously threatening the safety and reliability of the operation of the gas turbine. Summary of the Invention

[0003] The present invention aims to solve at least one of the technical problems in the related art to some extent.

[0004] To this end, an embodiment of the present invention provides a compressor moving blade, which can avoid the rigid collision between the moving blade and the cylinder wall of the cylinder, avoid the situation that the blade is easily broken due to the rigid effect, and improve the safety and reliability of the operation of the gas turbine. Secondly, since the rubbing of the blade only causes partial wear to the blade, this makes the blade have a greater space to withstand vibration, deformation, etc., so that a smaller tip clearance can be used during the assembly of the blade, improving the compactness of the assembly.

[0005] An embodiment of the present invention also provides a compressor including the above compressor moving blade.

[0006] An embodiment of the present invention also provides a gas turbine including the above compressor.

[0007] The compressor moving blade of the embodiment of the present invention includes:

[0008] A blade root and a blade body, the blade body having a first end and a second end arranged oppositely in the extending direction of the blade body, and the first end is connected to the blade root;

[0009] A dissolution layer, the dissolution layer is arranged at the second end of the blade body, and the dissolution layer can dissolve when exposed to a humid and high-temperature environment to reduce the rubbing resistance between the second end and the cylinder wall of the cylinder;

[0010] A protective layer, the protective layer wraps around the outer peripheral side of the dissolution layer, and the protective layer is used for wearing and / or falling off when the compressor moving blade touches the cylinder wall to expose the dissolution layer.

[0011] In some embodiments, the material of the dissolution layer includes at least one of the following: metallic element, soluble alloy.

[0012] In some embodiments, the metallic element is aluminum, and the soluble alloy is aluminum-magnesium alloy.

[0013] In some embodiments, the protective layer is a micro-arc oxidation ceramic film, and the composition of the micro-arc oxidation ceramic film includes magnesium oxide, aluminum oxide or silicon dioxide.

[0014] In some embodiments, the structural strength of the dissolution layer is weaker than that of the protective layer.

[0015] In some embodiments, the protective layer is connected to the blade body, a sealed cavity is defined between the protective layer and the second end, and the dissolution layer is located in the sealed cavity.

[0016] In some embodiments, the blade root includes:

[0017] A wedge portion having an inclined surface and a flat surface arranged oppositely in the extending direction of the blade body, the distance between the inclined surface and the flat surface increasing along the direction from one end of the blade root to the other end of the blade root, and the blade body being connected to the inclined surface;

[0018] A tail portion in the shape of a swallow, the tail portion in the shape of a swallow being connected to the flat surface, the extending direction of the tail portion in the shape of a swallow being consistent with the extending direction of the blade root, and the width dimension of the cross section of the tail portion in the shape of a swallow decreasing along the direction close to the wedge portion.

[0019] The compressor of the embodiment of the present invention includes the compressor moving blade as described in any one of the above embodiments.

[0020] In some embodiments, a cylinder and a compressor stator blade are further included, the compressor stator blade and the compressor moving blade are arranged at intervals in the axial direction of the cylinder, a coating is provided on the inner cylinder wall of the cylinder, the coating and the protective layer of the compressor moving blade are arranged oppositely in the radial direction of the cylinder, and the coating is abradable.

[0021] The gas turbine of the embodiment of the present invention includes the compressor as described in any one of the above embodiments.

[0022] Advantageous effects: The compressor moving blade, the compressor and the gas turbine of the embodiments of the present invention can avoid the rigid collision between the moving blade and the cylinder wall of the cylinder, avoid the situation that the blade is easily broken due to the rigid effect, and improve the safety and reliability of the operation of the gas turbine.

[0023] Secondly, since the rubbing of the blade only causes partial wear to the blade, this enables the blade to have a greater space for bearing vibrations, deformations, etc., so that a smaller tip clearance can be adopted during the assembly of the blade, and the assembly compactness is improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 is a schematic structural diagram of the compressor moving blade of the embodiment of the present invention.

[0025] Figure 2 It is a schematic diagram of a partial structure of a compressor according to an embodiment of the present invention.

[0026] Figure 3 It is a schematic diagram of a partial structure of a compressor according to another embodiment of the present invention.

[0027] Figure 4 is Figure 3 a partial enlarged schematic diagram at position A in

[0028] Reference numerals:

[0029] 100 - compressor moving blade;

[0030] 1 - blade root; 11 - wedge part; 111 - inclined surface; 112 - flat surface; 12 - swallowtail part;

[0031] 2 - blade body; 21 - first end; 22 - second end;

[0032] 3 - dissolution layer; 4 - protective layer; 5 - moving blade thinning tooth;

[0033] 200 - compressor moving blade; 300 - cylinder; 301 - coating. Detailed implementation manners

[0034] The embodiments of the present invention will be described in detail below. The examples of the embodiments are shown in the drawings. The embodiments described below with reference to the drawings are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention.

[0035] As Figure 1 shown, the compressor moving blade 100 according to the embodiment of the present invention includes a blade root 1, a blade body 2, a dissolution layer 3 and a protective layer 4. Among them, the dissolution layer 3 and the protective layer 4 constitute the moving blade thinning tooth 5 of the compressor moving blade. When in use, the moving blade thinning tooth 5 can be partially or completely worn away or consumed.

[0036] The blade root 1 can be a block structure, and the blade root 1 can be processed and formed by casting. The blade body 2 has a first end 21 and a second end 22 arranged oppositely in the extending direction of the blade body 2, and the first end 21 is connected to the blade root 1.

[0037] Specifically, as Figure 1 shown, the extending direction of the blade body 2 can be the radial direction of the compressor or the inner - outer direction. Among them, the first end 21 can be the inner end of the blade body 2, and the first end 21 can also be regarded as the blade root part of the blade body 2. The inner end of the blade body 2 can be integrally formed with the above - mentioned blade root 1. In some other embodiments, the first end 21 of the blade body 2 can also be fixedly connected to the blade root 1 by welding or the like.

[0038] The second end 22 may be the outer end of the blade body 2. The second end 22 can also be regarded as the free end or the tip part of the blade body 2. After the compressor moving blade 100 is installed in the compressor, the second end 22 can face the inner cylinder wall of the compressor cylinder 300 and be arranged at an interval from the inner cylinder wall.

[0039] The dissolution layer 3 is provided at the second end 22 of the blade body 2. The dissolution layer 3 can dissolve when exposed to a humid and high-temperature environment to reduce the frictional resistance between the second end 22 and the cylinder wall of the cylinder 300. For example, as Figure 1 shown, the dissolution layer 3 can be a metal layer. When the compressor is operating, the inside of the compressor cylinder 300 can be a humid and high-temperature environment. When the dissolution layer 3 is exposed to this environment, the dissolution layer 3 will dissolve or partially dissolve, so that the texture of the part of the dissolution layer 3 acting on the cylinder wall is softer, avoiding the situation of rigid contact with the cylinder wall of the cylinder 300, reducing the frictional resistance, and further avoiding the situation that the blade is easily broken under the action of rigid contact, ensuring the safety and stability of use.

[0040] The protective layer 4 is wrapped around the outer peripheral side of the dissolution layer 3. The protective layer 4 is used to wear and / or fall off when the compressor moving blade 100 touches the cylinder wall to expose the dissolution layer 3. For example, as Figure 1 shown, the protective layer 4 can be a ceramic layer. The protective layer 4 can cover the outer surface of the dissolution layer 3. The protective layer 4 can play a blocking role, that is, when the protective layer 4 does not touch the cylinder wall of the cylinder 300, the protective layer 4 can isolate the dissolution layer 3 from the internal environment of the cylinder 300, thus avoiding the situation that the dissolution layer 3 dissolves under the action of the environment and ensuring the normal use requirements of the compressor.

[0041] When the rotor generates large vibrations or large deformations during operation, the protective layer 4 will touch the cylinder wall of the cylinder 300. Under the direct action of the cylinder wall, the protective layer 4 will collide and fall off, break, or collide and wear. At this time, the dissolution layer 3 inside the protective layer 4 will be directly exposed in the cylinder 300 due to the loss of the shielding of the protective layer 4, and then under the action of the internal environment of the cylinder 300, the dissolution layer 3 will dissolve, thus alleviating the situation of rigid contact between the moving blade and the cylinder wall.

[0042] For the compressor moving blade 100 of the embodiment of the present invention, due to the dissolution effect of the dissolution layer 3, the compressor moving blade 100 can avoid the rigid collision between the tip part of the moving blade and the cylinder wall of the cylinder 300, and further avoid the situation that the blade is easily broken due to the rigid action, improving the safety and reliability of the operation of the gas turbine.

[0043] Secondly, since the rubbing of the blade only causes partial wear to the blade, it gives the blade itself a greater space to withstand vibrations, deformations, etc., so that a smaller tip clearance can be adopted during blade assembly, improving the compactness of the assembly.

[0044] In some embodiments, the material of the dissolution layer 3 includes at least one of the following: elemental metal, soluble alloy. Optionally, the above elemental metal may be a soluble elemental metal such as aluminum, and the above soluble alloy is a soluble alloy such as aluminum-magnesium alloy.

[0045] In some embodiments, the protective layer 4 is a micro-arc oxidation ceramic film, and the components of the micro-arc oxidation ceramic film include magnesium oxide, aluminum oxide or silicon dioxide. Specifically, the main components of the micro-arc oxidation ceramic film may include MgO or Al2O3. In some other embodiments, the main components of the micro-arc oxidation ceramic film may also be other types of metal oxides. It should be noted that when the electrolyte for micro-arc oxidation is silicate, at this time, the components of the micro-arc oxidation ceramic film may also contain SiO2.

[0046] In some embodiments, the structural strength of the dissolution layer 3 is weaker than that of the protective layer 4. Specifically, the structural strength may be the anti-deformation ability, etc. The anti-deformation ability of the dissolution layer 3 may be weaker than that of the protective layer 4. In this way, while the protective layer 4 isolates and protects the dissolution layer 3, the overall structural strength can also be improved, avoiding the situation where the structural strength of the tip part of the compressor moving blade 100 cannot meet the usage requirements due to the setting of the dissolution layer 3.

[0047] In some embodiments, the protective layer 4 is connected to the blade body 2, and a sealed cavity is defined between the protective layer 4 and the second end 22, and the dissolution layer 3 is located in the sealed cavity. For example, the protective layer 4 may be a cap-shaped structure as a whole, and the edge of the opening of the sealed cavity inside the protective layer 4 may be directly connected to the blade body 2. The above dissolution layer 3 is directly connected to the blade body 2 and is completely covered in the sealed cavity surrounded by the protective layer 4 and the blade body 2. The direct connection between the protective layer 4 and the blade body 2 can further reduce the influence of the setting of the dissolution layer 3 on the local structural strength.

[0048] In some embodiments, as Figure 1 shown, the blade root 1 includes a wedge-shaped portion 11 and a swallowtail portion 12. The wedge-shaped portion 11 may be a wedge-shaped block as a whole, and the cross-section of the swallowtail portion 12 may be a swallowtail shape. The wedge-shaped portion 11 and the swallowtail portion 12 may be integrally formed by casting.

[0049] The wedge-shaped portion 11 has an inclined surface 111 and a flat surface 112 that are oppositely arranged in the extending direction of the blade body 2. The distance between the inclined surface 111 and the flat surface 112 shows an increasing trend along the direction from one end of the blade root 1 to the other end of the blade root 1, and the blade body 2 is connected to the inclined surface 111.

[0050] For example, as Figure 1 shown, the outer wall surface of the wedge portion 11 can be an inclined surface 111, the inner wall surface of the wedge portion 11 can be a flat surface 112, the inclined surface 111 and the flat surface 112 can be arranged opposite to each other in the inner and outer directions, the extending direction of the blade root 1 can be the left - right direction, and the distance between the inclined surface 111 and the flat surface 112 can gradually increase along the direction from left to right. The above - mentioned blade body 2 can be directly fixed on the inclined surface 111.

[0051] The tail portion 12 is connected to the flat surface 112, the extending direction of the tail portion 12 is consistent with the extending direction of the blade root 1, and the width dimension of the cross - section of the tail portion 12 shows a decreasing trend along the direction close to the wedge portion 11.

[0052] For example, as Figure 1 shown, the extending direction of the tail portion 12 can also be the above - mentioned left - right direction, the width dimension of the cross - section of the tail portion 12 can be dimension M, dimension M can gradually become smaller along the direction from inside to outside, and the outer side of the tail portion 12 can be directly connected and fixed to the flat surface 112 of the above - mentioned wedge portion 11. The setting of the tail portion 12 facilitates the assembly of the compressor moving blade 100 and the rotor, and the overall assembly stability can be ensured by the limitation of the tail portion 12 and the slot wall of the corresponding slot.

[0053] The compressor of the embodiment of the present invention will be described below.

[0054] The compressor of the embodiment of the present invention includes the compressor moving blade 100 described in any of the above embodiments.

[0055] In some embodiments, the compressor further includes a cylinder 300 and compressor stationary blades. The compressor stationary blades and the compressor moving blade 100 are arranged at intervals in the axial direction of the cylinder 300. A coating 301 is provided on the inner cylinder wall of the cylinder 300. The coating 301 and the protective layer 4 of the compressor moving blade 100 are arranged opposite to each other in the radial direction of the cylinder 300, and the coating 301 is abradable.

[0056] For example, as Figure 2 shown, both the compressor stationary blades and the compressor moving blade 100 can be provided with a plurality of them. The plurality of compressor moving blades 100 can be assembled on the outer peripheral side of the rotor and arranged at intervals along the circumferential direction of the rotor, and these compressor moving blades 100 can form a moving blade group. The compressor can include a plurality of moving blade groups arranged at intervals in the axial direction.

[0057] The plurality of compressor stationary blades can be assembled on the inner cylinder wall of the cylinder 300 and arranged at intervals along the circumferential direction of the cylinder 300, and these compressor stationary blades can form a stationary blade group. The compressor can include a plurality of stationary blade groups arranged at intervals in the axial direction. As Figure 2 shown, the above - mentioned plurality of moving blade groups and the above - mentioned plurality of stationary blade groups can be arranged alternately one by one in the axial direction.

[0058] As shown Figure 2 in the figure, multiple coatings 301 may also be coated on the inner peripheral wall of the cylinder 300. Each coating 301 may be annular and may be arranged in a circle along the circumferential direction of the cylinder 300, and the multiple coatings 301 may be arranged at intervals along the axial direction of the cylinder 300. Each coating 301 may be located on the outer peripheral side of the corresponding moving blade group. The coating 301 may have an abradable function. When the tip portion of the compressor moving blade 100 in the moving blade group touches the cylinder wall of the cylinder 300, the coating 301 may be abraded first, thereby also alleviating the rigid contact between the compressor moving blade 100 and the cylinder wall and avoiding blade breakage.

[0059] In some other embodiments, as shown Figure 3 and Figure 4 in the figure, the coating 301 may not be provided on the inner peripheral wall of the cylinder 300. At this time, the tip portion of the compressor moving blade 100 is provided with the above-mentioned moving blade thinning teeth 5. During use, the rigid contact between the compressor moving blade 100 and the cylinder 300 is avoided through the abrasion of the protective layer 4 and the dissolution of the dissolution layer 3 of the moving blade thinning teeth 5.

[0060] The gas turbine according to the embodiment of the present invention will be described below.

[0061] The gas turbine according to the embodiment of the present invention includes a compressor as described in any of the above embodiments. In addition to the compressor, the gas turbine may further include a combustion chamber, a gas turbine, etc.

[0062] A specific example of the gas turbine according to the embodiment of the present invention will be described below.

[0063] Attached Figure 1 shows a schematic diagram of the tip structure of the moving blade of the compressor of the gas turbine. The matrix part of this structure is mainly composed of a metal layer (dissolution layer 3) and a protective layer 4. The protective layer 4 completely wraps the metal layer. The metal layer may be a single metal or an alloy layer; the protective layer 4 may be a micro-arc oxidation ceramic film.

[0064] The main component of the single metal is a series of soluble metals such as aluminum, and the main component of the alloy layer is aluminum-magnesium alloy or other soluble alloys. The main components of the micro-arc oxidation ceramic film are MgO, Al2O3, or other oxides. If the electrolyte for micro-arc oxidation is silicate, the micro-arc oxidation ceramic film layer also contains SiO2.

[0065] When the gas turbine is operating, if there are situations such as excessive rotor vibration, changes in the rotor center, or severe deformation of the inner circle of the cylinder 300, the tip of the moving blade will rub against the wall of the cylinder 300. During the rubbing process, the protective layer 4 at the tip of the moving blade will be scraped off first, and then the exposed metal layer will experience partial dissolution of the matrix in a humid and high-temperature environment, which can reduce the resistance of the rubbing and prevent the occurrence of blade fracture, thus ensuring the safety of the unit.

[0066] Beneficial effects: The structure of the tip of the moving blade designed in the embodiment of the present invention realizes the design of wearability and solubility of the metal layer at the blade tip under the working conditions inside the cylinder, thereby reducing the occurrence of blade fracture.

[0067] Secondly, the inner wall of the cylinder can also adopt a design without spraying a wear-resistant coating. That is, the wearability and solubility of the moving blade tip structure can avoid the direct rigid interaction between the moving blade and the cylinder wall, which can avoid the problems that the wear-resistant coating is prone to cracking during use and falling off during the operation of the unit when only a wear-resistant coating is provided.

[0068] In addition, since the rubbing of the compressor moving blade in the embodiment of the present invention only damages the tip part of the moving blade, this enables a smaller tip clearance to be set in terms of technical effects for the compressor moving blade, and the wear state can also be evaluated by checking the remaining amounts of the protective layer and the metal layer at the tip part of the test unit during operation, which helps to correct the clearance of commercial units.

[0069] In the description of the present invention, it should be understood that the orientation or positional relationships indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. are based on the orientation or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention.

[0070] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present invention, the meaning of "a plurality" is at least two, such as two, three, etc., unless otherwise specifically defined.

[0071] In the present invention, unless otherwise clearly specified or limited, terms such as "installed", "connected", "coupled", "fixed", etc. shall be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection, an electrical connection, or communicable with each other; it may be directly connected, or indirectly connected through an intermediate medium, and may be the internal communication between two components or the interaction relationship between two components, unless otherwise clearly limited. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0072] In the present invention, unless otherwise clearly specified or limited, the first feature being "on" or "under" the second feature may be that the first and second features are in direct contact, or the first and second features are indirectly in contact through an intermediate medium. Moreover, the first feature being "above", "over" and "on top of" the second feature may be that the first feature is directly above or obliquely above the second feature, or merely indicates that the first feature has a higher horizontal height than the second feature. The first feature being "under", "below" and "beneath" the second feature may be that the first feature is directly below or obliquely below the second feature, or merely indicates that the first feature has a lower horizontal height than the second feature.

[0073] In the present invention, terms such as "one embodiment", "some embodiments", "example", "specific example", or "some examples", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0074] Although the above embodiments have been shown and described, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Modifications, alterations, substitutions, and variations made by those of ordinary skill in the art to the above embodiments are all within the protection scope of the present invention.

Claims

1. A compressor moving blade, characterized in that, Comprising: A blade root and a blade body, the blade body having a first end and a second end oppositely arranged in the extending direction of the blade body, the first end being connected to the blade root; A dissolving layer provided at the second end of the blade body, the dissolving layer being soluble when exposed to a humid and high-temperature environment to reduce the abrasion resistance between the second end and the cylinder wall of the cylinder; A protective layer wrapped around the outer peripheral side of the dissolving layer, the protective layer being worn and / or shed when the moving blade of the compressor touches the cylinder wall to expose the dissolving layer.

2. The compressor moving blade according to claim 1, characterized in that, The material of the dissolving layer comprises at least one of the following: metallic element, soluble alloy.

3. The compressor moving blade according to claim 2, wherein, The metallic element is aluminum, and the soluble alloy is aluminum-magnesium alloy.

4. The compressor moving blade according to claim 1, wherein The protective layer is a micro-arc oxidation ceramic film, and the composition of the micro-arc oxidation ceramic film comprises magnesium oxide, aluminum oxide or silicon dioxide.

5. The compressor moving blade according to claim 1, wherein The structural strength of the dissolving layer is weaker than that of the protective layer.

6. The compressor moving blade according to claim 5, wherein, The protective layer is connected to the blade body, and a sealed cavity is defined between the protective layer and the second end, and the dissolving layer is located in the sealed cavity.

7. The compressor moving blade according to any one of claims 1-6, characterized in that, The blade root comprises: A wedge-shaped part having an inclined surface and a flat surface oppositely arranged in the extending direction of the blade body, the distance between the inclined surface and the flat surface increasing along the direction from one end of the blade root to the other end of the blade root, and the blade body being connected to the inclined surface; A tail part in the shape of a swallow's tail connected to the flat surface, the extending direction of the tail part in the shape of a swallow's tail being consistent with the extending direction of the blade root, and the width dimension of the cross-section of the tail part in the shape of a swallow's tail decreasing along the direction close to the wedge-shaped part.

8. A compressor, characterized in that, Comprising the moving blade of the compressor according to any one of the above claims 1-7.

9. The compressor according to claim 8, wherein, Further comprising a cylinder and a stationary blade of the compressor, the stationary blade of the compressor and the moving blade of the compressor being arranged at intervals in the axial direction of the cylinder, a coating being provided on the inner cylinder wall of the cylinder, the coating and the protective layer of the moving blade of the compressor being oppositely arranged in the radial direction of the cylinder, and the coating being abradable.

10. A gas turbine, characterized in that, Comprising the compressor according to the above claim 9.

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