Turbine blade of engine

Abstract

The utility model belongs to the technical field of turbine blades, and particularly relates to a turbine blade of an engine. Each blade comprises a blade main body and an edge plate, and the multiple blades are evenly distributed on the periphery of the turbine disc; the connecting mechanism comprises a connecting clamping groove formed in the periphery of the turbine disc and a connecting protrusion arranged on the margin plate and matched with the connecting clamping groove. Wherein a gap is formed between every two adjacent blades, and damping pieces capable of filling the gaps are arranged on the blades. The turbine disc has the beneficial effects that through cooperation of the connecting clamping grooves and the connecting protrusions, the blades are firmly fixed to the turbine disc, the fixing effect of the blades is effectively improved, through arrangement of the connecting clamping grooves and the connecting protrusions, the fixing effect of the blades is improved, and the risk that the blades are independently thrown away during high-speed rotation is avoided.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of turbine blades, and particularly relates to a turbine blade of an engine. BACKGROUND

[0002] The turbine blade is an important component of a turbine section in a turbine engine, and the high-speed rotating blade is responsible for sucking in airflow to maintain the operation of the engine.

[0003] The patent with the publication number CN214366219U discloses a directional alloy turbine blade for an aero-engine, which comprises a main body, a cylindrical head fixedly installed on the top of the main body, and a cylindrical base fixedly installed on the bottom of the main body.

[0004] The above patent can lock all the blades by setting a fixing ring to avoid the blades from being thrown alone, and although the locking effect can be achieved, the fixing effect of the blades themselves is poor and needs to be improved. Practical new type content

[0005] The application aims to provide a turbine blade of an engine which can solve the above problems.

[0006] The application aims to provide a turbine blade of an engine, which comprises:

[0007] A turbine disc;

[0008] A blade comprising a blade body and a rim plate, and the blade is provided with a plurality of rim plates and is uniformly distributed on the periphery of the turbine disc.

[0009] A connecting mechanism comprising a connecting slot provided on the outer periphery of the turbine disc and a connecting protrusion provided on the rim plate and matched with the connecting slot.

[0010] The gap is formed between the adjacent blades, and the damping member capable of filling the gap is arranged on the blade.

[0011] The turbine blade of the engine comprises a turbine disc used as a supporting component of the blade for transmitting the power of the engine to the blade, a blade comprising a blade body and a rim plate, and the blade is provided with a plurality of rim plates and is uniformly distributed on the periphery of the turbine disc. The connecting mechanism comprises a connecting slot provided on the outer periphery of the turbine disc and a connecting protrusion provided on the rim plate and matched with the connecting slot. The blade is firmly fixed on the turbine disc through the matching of the connecting slot and the connecting protrusion, and the fixing effect of the blade is effectively improved. Meanwhile, the gap is formed between the adjacent blades, and the damping member capable of filling the gap is arranged on the blade. The damping member can absorb the vibration energy generated in the rotating process of the blade, provide the damping effect, and further ensure the operation stability of the blade.

[0012] In the present application, the outer periphery of the turbine disc can be provided with a plurality of uniformly distributed connecting grooves, each corresponding to a connecting protrusion on the rim plate of a blade, the connecting protrusion and the connecting groove being matched in shape to ensure that the blade can be accurately and firmly fixed on the turbine disc. By providing the connecting groove and the connecting protrusion, the fixing effect of the blade is improved, and the risk of the blade being thrown off alone during high-speed rotation is avoided. By providing the damping member, good damping effect is provided, the vibration amplitude of the blade during rotation is reduced, and the operation stability of the blade is improved.

[0013] Further, the connecting groove comprises:

[0014] a first groove body;

[0015] a second groove body in communication with the first groove body, and the circumferential width of the second groove body is less than half of the circumferential width of the first groove body;

[0016] wherein the cross section of the second groove body and the first groove body after connection is in the shape of a convex character.

[0017] The groove comprises a first groove body and a second groove body, which together constitute one of the connecting structures of the blade and the turbine disc. The first groove body is located at the outer periphery of the turbine disc, has a large circumferential width, and is used to cooperate with the first protrusion on the rim plate of the blade. The design of the first groove body ensures the preliminary positioning and stability of the blade on the turbine disc. The second groove body is in communication with the first groove body, but its circumferential width is less than half of the circumferential width of the first groove body. The design of the second groove body not only enhances the connection strength between the blade and the turbine disc, but also limits the movement of the blade in the circumferential direction through its narrow width, further improving the fixing effect of the blade. Moreover, the cross section of the second groove body and the first groove body after connection is in the shape of a convex character. This design enables the connecting protrusion to be more stably embedded in the groove, effectively preventing the blade from loosening or falling off during high-speed rotation.

[0018] Further, the connecting protrusion comprises:

[0019] a first protrusion connected with the rim plate and cooperating with the first groove body;

[0020] a second protrusion connected with the first protrusion and cooperating with the second groove body;

[0021] wherein the cross section of the first protrusion and the second protrusion after connection is in the shape of a convex character, and a gap is left after the cooperation between the second protrusion and the second groove body.

[0022] The connecting protrusion is connected with the rim plate and comprises a first protrusion and a second protrusion, which together constitute another structure matched with the groove. The first protrusion is directly connected with the rim plate and tightly matched with the first groove body. The shape and size of the first protrusion are matched with the first groove body, which ensures the accurate positioning and preliminary fixation of the blade on the turbine disc. The second protrusion is connected with the first protrusion and matched with the second groove body. The shape and size of the second protrusion are matched with the second groove body, and a gap is left between the second protrusion and the second groove body after matching. This not only allows the blade to have a certain degree of freedom to make slight adjustment when it is subjected to thermal expansion or mechanical stress, but also prevents the connecting mechanism from extruding the turbine disc due to deformation under extreme conditions, thereby protecting the structural stability of the turbine disc.

[0023] Further, the damping member is movably mounted on the rim plate, and the damping member comprises:

[0024] The groove is provided on the rim plate, and the top surface of the inner wall of the groove is obliquely arranged;

[0025] The upper damping block is arranged in the groove, and one end of the upper damping block is matched with the top surface of the groove in an oblique manner;

[0026] The lower damping block is connected with the other end of the upper damping block and arranged outside the groove;

[0027] Wherein, after the damping member moves, the upper damping block contacts the inner wall of the groove, and the lower damping block contacts the outer wall of the groove.

[0028] The damping member is movably mounted on the rim plate, and comprises a groove, an upper damping block and a lower damping block, which together constitute a vibration damping and sealing structure of the blade gap. The groove is provided on the rim plate, and the top surface of the inner wall of the groove is obliquely arranged, so that the upper damping block can move under the guidance of the inclined surface during vibration, thereby more effectively absorbing and dispersing vibration energy. At the same time, the inclined top surface also increases the contact area between the upper damping block and the rim plate, improves the friction between them, and further enhances the damping effect. The upper damping block is arranged in the groove, and one end of the upper damping block is tightly matched with the inclined top surface of the groove, which ensures that it can stably move along the inclined surface during vibration. The lower damping block is connected with the other end of the upper damping block and arranged outside the groove, which not only enhances the overall structural strength of the damping member, but also further improves the sealing performance of the blade gap through the contact between the lower damping block and the outer wall of the groove. During the vibration process, the lower damping block can be adjusted accordingly with the movement of the upper damping block, thereby maintaining the tight sealing of the blade gap. In this application, through the design of the inclined contact surface and the movable installation, the damping member can more effectively absorb and disperse the energy generated by the blade vibration, thereby improving the damping effect. The contact between the lower damping block and the outer wall of the groove further ensures the tight sealing of the blade gap and prevents the gap from expanding due to vibration.

[0029] Further, the upper damping block and the lower damping block are provided with a movable groove, and a matching protrusion is arranged in the groove and matched with the movable groove.

[0030] The movable groove is arranged between the upper damping block and the lower damping block, so that the upper damping block can stably slide along the movable groove during vibration.

[0031] Further, a through groove is arranged between the upper damping block and the lower damping block, and a reinforcing rib is arranged in the through groove.

[0032] The through groove is arranged between the upper damping block and the lower damping block, so that the overall mass of the damping member is reduced, the rotational inertia and energy consumption of the turbine blade are reduced, the heat dissipation performance of the damping member is improved, and the service life of the damping member is prolonged.

[0033] The beneficial effects of the present application are as follows:

[0034] 1. The blade is firmly fixed on the turbine disc through the cooperation of the connecting clamping groove and the connecting protrusion, so that the fixing effect of the blade is effectively improved, and the fixing effect of the blade is improved through the arrangement of the connecting clamping groove and the connecting protrusion, so that the risk of the blade being thrown alone at high speed is avoided.

[0035] 2. The gap is formed between the adjacent blades, and the damping member capable of filling the gap is arranged on the blade. The damping member can absorb the vibration energy generated during the rotation of the blade, provide a damping effect, and further ensure the operation stability of the blade.

[0036] 3. The gap is left after the cooperation between the second protrusion and the second groove body, so that the blade has a certain degree of freedom for slight adjustment when subjected to thermal expansion or mechanical stress, and the connecting mechanism is prevented from being pressed against the turbine disc due to deformation under extreme conditions, so that the structural stability of the turbine disc is protected. BRIEF DESCRIPTION OF DRAWINGS

[0037] Figure 1 is a structural schematic view of the present application;

[0038] Figure 2 is a top view of the utility model;

[0039] Figure 3 is Figure 2 a sectional view in A-A direction;

[0040] Figure 4 is Figure 3 an enlarged view of A;

[0041] Figure 5 is a structure schematic view of the blade main body and the damping piece.

[0042] In the drawing, reference signs are: 100, turbine disc; 200, blade; 210, blade main body; 220, rim plate; 300, connecting clamping groove; 310, first groove body; 320, second groove body; 400, connecting protrusion; 410, first protrusion; 420, second protrusion; 430, gap; 500, gap; 600, damping piece; 610, recess; 620, upper damping block; 630, lower damping block; 640, movable groove; 650, matching protrusion; 660, through groove; 670, reinforcing rib. DETAILED DESCRIPTION

[0043] The technical solutions in the embodiments of the present application will be clearly described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, but not all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art belong to the scope of protection of the present application.

[0044] The terms "first", "second" and the like in the specification and claims of the present application are used to distinguish similar objects, and are not used to describe a specific order or sequence. It should be understood that the data used in this way can be exchanged under appropriate circumstances, so that the embodiments of the present application can be implemented in an order other than those illustrated or described herein, and the objects distinguished by "first", "second" and the like are generally of a kind, and are not limited to the number of objects, for example, the first object can be one or more. In addition, "and / or" in the specification and claims means at least one of the connected objects, and the character " / ", generally represents that the front and rear associated objects are in an "or" relationship.

[0045] The turbine blade of the engine provided by the embodiments of the present application will be described in detail below in combination with the drawings and specific embodiments and application scenarios.

[0046] Embodiment 1:

[0047] As Figures 1 to 5 shown, the embodiments of the present application provide a turbine blade of an engine, comprising:

[0048] A turbine disc 100;

[0049] A blade 200, comprising a blade body 210 and a rim plate 220, the blade 200 being provided with a plurality of and evenly distributed around the periphery of the turbine disc 100;

[0050] A connecting mechanism, comprising a connecting clamping groove 300 provided on the periphery of the turbine disc 100 and a connecting protrusion 400 provided on the rim plate 220 and matched with the connecting clamping groove 300;

[0051] Wherein, a gap 500 is formed between adjacent blades 200, and a damping member 600 capable of filling the gap 500 is provided on the blade 200.

[0052] In some embodiments of the present application, as shown in Figure 1 The turbine blade 200 of the engine described above is used as a supporting component of the blade 200, and is used to transmit the power of the engine to the blade 200. The blade 200 comprises a blade body 210 and a rim plate 220, and the blade 200 is provided with a plurality of and evenly distributed around the periphery of the turbine disc 100. The connecting mechanism comprises a connecting clamping groove 300 provided on the periphery of the turbine disc 100 and a connecting protrusion 400 provided on the rim plate 220 and matched with the connecting clamping groove 300. Through the cooperation of the connecting clamping groove 300 and the connecting protrusion 400, the blade 200 is firmly fixed on the turbine disc 100, effectively improving the fixing effect of the blade 200. At the same time, a gap 500 is formed between adjacent blades 200, and a damping member 600 capable of filling the gap 500 is provided on the blade 200. The damping member 600 can absorb the vibration energy generated by the blade 200 during rotation, provide a damping effect, and further ensure the operation stability of the blade 200.

[0053] In the present application, the periphery of the turbine disc 100 can be provided with a plurality of evenly distributed connecting clamping grooves 300, each connecting clamping groove 300 corresponding to a connecting protrusion 400 on the rim plate 220 of a blade 200, the connecting protrusion 400 and the connecting clamping groove 300 matching in shape to ensure that the blade 200 can be accurately and firmly fixed on the turbine disc 100. By providing the connecting clamping groove 300 and the connecting protrusion 400, the fixing effect of the blade 200 is improved, and the risk of the blade 200 being thrown alone at high speed is avoided. By providing the damping member 600, a good damping effect is provided, the vibration amplitude of the blade 200 during rotation is reduced, and the operation stability of the blade 200 is improved.

[0054] Embodiment 2:

[0055] The engine turbine blade provided by the embodiments of the present application comprises the following technical features in addition to the above technical features.

[0056] As Figure 3 and Figure 4 shown, the connecting groove 300 comprises:

[0057] a first groove body 310;

[0058] a second groove body 320, which is in communication with the first groove body 310, and the circumferential width of the second groove body 320 is less than half of the circumferential width of the first groove body 310;

[0059] wherein the cross section of the connection between the second groove body 320 and the first groove body 310 is in the shape of a convex.

[0060] In the embodiments of the present application, the groove 610 comprises the first groove body 310 and the second groove body 320, which together constitute one of the connecting structures of the connecting blade 200 and the turbine disc 100. The first groove body 310 is located at the outer periphery of the turbine disc 100, and has a relatively large circumferential width, which is used to cooperate with the first protrusion 410 on the rim 220 of the blade 200. The design of the first groove body 310 ensures the preliminary positioning and stability of the blade 200 on the turbine disc 100. The second groove body 320 is in communication with the first groove body 310, but its circumferential width is less than half of the circumferential width of the first groove body 310. The design of the second groove body 320 not only enhances the connecting strength between the blade 200 and the turbine disc 100, but also limits the movement of the blade 200 in the circumferential direction through its narrow width, further improving the fixing effect of the blade 200. Moreover, the cross section of the connection between the second groove body 320 and the first groove body 310 is in the shape of a convex. This design enables the connecting protrusion 400 to be more stably embedded in the groove 610, effectively preventing the blade 200 from loosening or falling off during high-speed rotation.

[0061] Further, the connecting protrusion 400 comprises:

[0062] a first protrusion 410, which is connected with the rim 220 and cooperates with the first groove body 310;

[0063] a second protrusion 420, which is connected with the first protrusion 410 and cooperates with the second groove body 320;

[0064] wherein the cross section of the connection between the first protrusion 410 and the second protrusion 420 is in the shape of a convex, and a gap 430 is left between the second protrusion 420 and the second groove body 320 after cooperation.

[0065] The connecting protrusion 400 is connected with the rim plate 220 and comprises a first protrusion 410 and a second protrusion 420, which together constitute another structure matched with the groove 610. The first protrusion 410 is directly connected with the rim plate 220 and closely matched with the first groove body 310. The shape and size of the first protrusion 410 are matched with the first groove body 310, which ensures the accurate positioning and preliminary fixation of the blade 200 on the turbine disc 100. The second protrusion 420 is connected with the first protrusion 410 and matched with the second groove body 320. The shape and size of the second protrusion 420 are matched with the second groove body 320, and a gap 430 is left between the second protrusion 420 and the second groove body 320 after matching. In this way, not only is a certain degree of freedom allowed for the blade 200 to make slight adjustment when subjected to thermal expansion or mechanical stress, but also the connecting mechanism is prevented from extruding the turbine disc 100 due to deformation under extreme conditions, thereby protecting the structural stability of the turbine disc 100.

[0066] Embodiment 3:

[0067] The turbine blade of the engine provided in the embodiments of the present application further comprises the following technical features in addition to the above technical features.

[0068] As shown in Figures 3 to 5 The damping member 600 is movably installed on the rim plate 220, and the damping member 600 comprises:

[0069] The groove 610 is arranged on the rim plate 220, and the top surface of the inner wall of the groove 610 is arranged in an inclined manner;

[0070] The upper damping block 620 is arranged in the groove 610, and one end of the upper damping block 620 is matched with the top surface of the groove 610 in an inclined manner;

[0071] The lower damping block 630 is connected with the other end of the upper damping block 620 and arranged outside the groove 610;

[0072] After the damping member 600 moves, the upper damping block 620 is in contact with the inner wall of the groove 610, and the lower damping block 630 is in contact with the outer wall of the groove 610.

[0073] In the embodiment of the present application, the damping member 600 is movably mounted on the rim plate 220, and includes a groove 610, an upper damping block 620 and a lower damping block 630, which together constitute a damping and sealing structure of the gap 500 between the blades 200. The groove 610 is arranged on the rim plate 220, and the top surface of the inner wall thereof is arranged to be inclined, so that the upper damping block 620 can move under the guidance of the inclined surface when vibrating, thereby more effectively absorbing and dispersing vibration energy. At the same time, the inclined top surface also increases the contact area of the upper damping block 620 with the rim plate 220, improves the friction therebetween, and further enhances the damping effect. The upper damping block 620 is arranged in the groove 610, and one end thereof is in close cooperation with the inclined top surface of the groove 610, so as to ensure that it can stably move along the inclined surface when vibrating. The lower damping block 630 is connected to the other end of the upper damping block 620 and arranged outside the groove 610, which not only enhances the overall structural strength of the damping member 600, but also further improves the sealing performance of the gap 500 between the blades 200 through the contact with the outer wall of the groove 610. During the vibration process, the lower damping block 630 can be adjusted accordingly with the movement of the upper damping block 620, thereby maintaining the tight sealing of the gap 500 between the blades 200. In the present application, through the arrangement of the inclined contact surface and the movable mounting design, the damping member 600 can more effectively absorb and disperse the energy generated by the vibration of the blades 200, thereby improving the damping effect. The contact of the lower damping block 630 with the outer wall of the groove 610 further ensures the tight sealing of the gap 500 between the blades 200, and prevents the expansion of the gap 500 caused by vibration.

[0074] Embodiment 4:

[0075] The embodiment of the present application provides a turbine blade of an engine, in addition to the above technical features, the turbine blade of the engine of the embodiment of the present application further comprises the following technical features.

[0076] As shown in Figure 5 , the movable groove 640 is arranged between the upper damping block 620 and the lower damping block 630, and the matching protrusion 650 is arranged in the groove 610 and cooperates with the movable groove 640.

[0077] In the embodiment of the present application, the active groove 640 is arranged between the upper damping block 620 and the lower damping block 630, which ensures that the upper damping block 620 can stably slide along the active groove 640 during vibration. The matching protrusion 650 is arranged in the groove 610 and matches the shape and size of the active groove 640, so that the upper damping block 620 can keep close contact with the inner wall of the groove 610 during sliding, thereby improving the damping effect and sealing performance of the damping member 600. When the blade 200 vibrates during high-speed rotation, the upper damping block 620 moves under the guidance of the inclined top surface of the groove 610. At this time, the cooperation of the active groove 640 and the matching protrusion 650 enables the upper damping block 620 to stably slide along the predetermined path, and the sliding process not only absorbs vibration energy, but also further enhances the damping effect by increasing the contact area and friction with the rim plate 220.

[0078] Embodiment 5:

[0079] The embodiment of the present application provides a turbine blade of an engine. In addition to the above technical features, the turbine blade of the engine of the embodiment of the present application further comprises the following technical features.

[0080] As shown in Figure 5 The through groove 660 is arranged between the upper damping block 620 and the lower damping block 630, and the reinforcing rib 670 is arranged in the through groove 660.

[0081] In the embodiment of the present application, the through groove 660 is arranged between the upper damping block 620 and the lower damping block 630, which can reduce the overall mass of the damping member 600, thereby reducing the rotational inertia and energy consumption of the turbine blade 200, and also improving the heat dissipation performance of the damping member 600, which helps to prolong the service life. The reinforcing rib 670 is arranged in the through groove 660, which reduces the mass while maintaining the structural rigidity of the damping member 600, prevents the damping member 600 from deforming or being damaged during vibration, and thereby improves the reliability and durability.

[0082] It should be noted that, in the present document, the terms "comprises", "comprising", or any other variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can also include other elements not expressly listed or inherent to such process, method, article, or apparatus. An element proceeded by "comprises... a" does not, without more constraints, exclude the presence of additional identical elements in the process, method, article, or apparatus that comprises the element. Furthermore, it should be noted that the methods and apparatus of the present embodiments are not limited by the order of the steps or the sequence for performing the steps, as some steps can occur in different orders and / or concurrently with one another; for example, described methods can be performed in an order other than that described, and / or additional steps can be added, or steps can be omitted, or a combination thereof. Also, characteristics described in relation to certain examples can be combined in other examples.

[0083] The embodiments of the present application described above are merely exemplary and are not intended to limit the present application to the above-described embodiments, but the above-described embodiments are merely illustrative, and the present application is not limited to the above-described embodiments. The above-described embodiments can be modified in various ways by those skilled in the art without departing from the scope of the present application, and all modifications belong to the scope of the present application.

Claims

1. A turbine blade of an engine, characterized by: The utility model relates to a turbine disc (100) and a connecting mechanism thereof. The turbine disc (100) comprises a plurality of blades (200) arranged on the periphery of the turbine disc (100). The connecting mechanism comprises a connecting groove (300) arranged on the periphery of the turbine disc (100) and a connecting protrusion (400) arranged on the rim plate (220) and matched with the connecting groove (300). The connecting groove (300) comprises a first groove body (310) and a second groove body (320) in communication with the first groove body (310). The connecting protrusion (400) comprises a first protrusion (410) matched with the first groove body (310) and a second protrusion (420) matched with the second groove body (320). The damping member (600) is movably arranged on the rim plate (220). The damping member (600) comprises a groove (610) arranged on the rim plate (220) and an upper damping block (620) arranged in the groove (610). The upper damping block (620) is matched with the top surface of the inner wall of the groove (610) in an inclined manner. The damping member (600) comprises a lower damping block (630) connected with the other end of the upper damping block (620) and arranged outside the groove (610). The upper damping block (620) is matched with the inner wall of the groove (610) in an inclined manner after the damping member (600) is moved. The upper damping block (620) and the lower damping block (630) are arranged with a movable groove (640). The upper damping block (620) and the lower damping block (630) are arranged with a through groove (660) and a reinforcing rib (670) arranged in the through groove (660). ​ ​ ​ ​ ​ ​ 2. A turbine blade for an engine according to claim 1, wherein: ​ 3. A turbine blade for an engine according to claim 2, wherein: ​

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