Turbine rotor blade and turbine rotor

Abstract

The invention relates to the technical field of turbines, and discloses a turbine rotor blade and a turbine rotor, and the turbine rotor blade comprises a tenon, a blade body, a first margin plate and a second margin plate. The tenon is suitable for being connected with a turbine disc. And the blade body and the tenon are connected into a whole. The first edge plate is provided with a first notch, the second edge plate is provided with a second notch, the second edge plate is connected with the first edge plate in a matched mode, the second notch and the first notch are spliced to form a containing groove, the blade body penetrates through the containing groove, and the inner wall of the containing groove is attached to the outer wall of the blade body. According to the turbine rotor blade, due to the fact that the blade body made of the ceramic matrix composite, the first margin plate and the second margin plate are machined in a split mode, sudden change of the cross section from the blade body to the margin plates is avoided, the manufacturing difficulty is reduced, the yield is improved, the cost is reduced, and the situation that the material performance of the ceramic matrix composite is weakened due to the sudden change of the cross section can be avoided.

Description

Technical Field

[0001] This application relates to the field of turbine technology, and particularly to a turbine rotor blade and a turbine rotor. Background Art

[0002] In the turbine components of an aero gas turbine engine, the turbine rotor blade is one of the most important structures. Its main function is to make the airflow expand and accelerate in the airflow passage through the profile difference between the pressure surface and the suction surface, generating a circumferential static pressure load to drive the rotor to rotate at a high speed, and realizing the conversion of the chemical energy of high-temperature gas into mechanical energy. Currently, the common turbine rotor blades are integrally cast from superalloys, mainly composed of three parts: the blade body, the shroud, and the dovetail. The blade body is driven by the high-temperature and high-pressure airflow to drive the rotor to rotate; the shroud forms the flow passage surface and protects the turbine disk, and the dovetail is connected to the dovetail groove of the turbine disk to achieve load transfer.

[0003] The demand of aero gas turbine engines for high thrust-to-weight ratio and low fuel consumption rate drives the continuous increase of the turbine inlet temperature. The turbine inlet temperature of current advanced engines has reached above 1500 °C. The service limit temperature of existing metal materials such as directionally solidified alloys and single-crystal alloys is about 1200 °C, which can no longer meet the use requirements of the turbine rotor blades of advanced engines. Ceramic matrix composites have excellent high-temperature mechanical properties and have significant advantages as engine hot-end materials compared with superalloy materials.

[0004] However, due to the limitations of the processing technology, it is difficult for ceramic matrix composites to process overly complex profiles. For the blades of the turbine rotor, the cross-section changes suddenly from the blade body to the shroud, which not only makes the manufacturing difficult but also weakens the material properties of the ceramic matrix composites.

[0005] Therefore, how to solve or improve the problems of high manufacturing difficulty and poor material properties of the turbine rotor blades integrally formed by ceramic matrix composites in the related art has become an important technical problem to be solved by those skilled in the art. Summary of the Invention

[0006] In view of this, this application provides a turbine rotor blade and a turbine rotor to solve or improve the problems of high manufacturing difficulty and poor material properties of the turbine rotor blades integrally formed by ceramic matrix composites.

[0007] In a first aspect, this application provides a turbine rotor blade, including:

[0008] A dovetail, adapted to be connected to a turbine disk;

[0009] A blade body, integrally connected to the dovetail;

[0010] A first shroud, provided with a first notch;

[0011] The second edge plate is provided with a second notch, the second edge plate is matched and connected with the first edge plate, the second notch and the first notch are combined to form a receiving groove, the blade body is arranged through the receiving groove, and the inner wall of the receiving groove is in contact with the outer wall of the blade body.

[0012] Optionally, the first edge plate is provided with a first convex portion and a first concave portion, and the second edge plate is provided with a second convex portion and a second concave portion, and the first convex portion is matched and connected with the second concave portion, and the first concave portion is matched and connected with the second convex portion.

[0013] Optionally, the first convex portion is provided with an inserting groove, and the second concave portion is provided with an inserting portion, and the inserting portion is inserted into the inserting groove.

[0014] In a second aspect, the present application further provides a turbine rotor, comprising:

[0015] Turbine rotor blades as described in any of the above;

[0016] The turbine disk is provided with a plurality of tenons along the axial direction, each tenon is distributed along the circumference of the turbine disk, each turbine rotor blade is distributed along the circumference of the turbine disk, the tenon of each turbine rotor blade is plugged into the tenon one by one, and the inner wall of the tenon is provided with a through groove for the blade piercing to protrude.

[0017] Optionally, it also includes:

[0018] The first stop bar comprises a first connecting bar, a first folded edge arranged at a first end of the first connecting bar, and a second folded edge arranged at a second end of the first connecting bar, wherein the first connecting bar is passed through the tenon groove and is located between the tenon head and the inner wall of the tenon groove,

[0019] A side of the first folded edge close to the second folded edge is in contact with the first end surface of the turbine disk, and the first folded edge is limitedly matched with the tenon in the axial direction of the turbine disk;

[0020] A side of the second folded edge close to the first folded edge is in contact with the second end surface of the turbine disk, and the second folded edge is limitedly matched with the tenon in the axial direction of the turbine disk.

[0021] Optionally, the first folded edge includes a first segment and a second segment which are sequentially arranged and connected away from the first connecting strip, an end of the first segment away from the second segment is vertically connected to the first end of the first connecting strip, a width of the second segment is greater than a width of the first segment, and the second segment is in contact with the first end surface of the turbine disc;

[0022] The second folded edge includes a third segment and a fourth segment which are arranged and connected in sequence away from the first connecting strip, one end of the third segment away from the fourth segment is vertically connected to the second end of the first connecting strip, the width of the fourth segment is greater than the width of the third segment, and the fourth segment is in contact with the second end surface of the turbine disc.

[0023] Optionally, it also includes:

[0024] A first fixing ring, an end surface of which is provided with a first slot in the circumferential direction, an end of the first edge plate which is away from the second edge plate is provided with a first plugging protrusion, and the first plugging protrusion on the first edge plate of each of the turbine rotor blades is plugged into the first slot;

[0025] The second fixing ring has a second slot arranged on its end face in the circumferential direction, and a second plugging protrusion is arranged on the end of the second edge plate facing away from the first edge plate, and the second plugging protrusion on the second edge plate of each of the turbine rotor blades is plugged into the second slot.

[0026] Optionally, it also includes:

[0027] The second baffle includes a second connecting strip, a third folded edge arranged at the first end of the second connecting strip, and a fourth folded edge arranged at the second end of the second connecting strip. One side of two adjacent first edge plates and one side of two adjacent second edge plates close to the circumferential surface of the turbine disk are both in contact with the second connecting strip, and the side of the third folded edge close to the fourth folded edge is abutted against the side of the first fixing ring away from the first edge plate, and the side of the fourth folded edge close to the third folded edge is abutted against the side of the second fixing ring away from the second edge plate.

[0028] Optionally, the third folded edge includes a fifth segment and a sixth segment which are sequentially arranged and connected away from the second connecting strip, an end of the fifth segment away from the sixth segment is vertically connected to the first end of the second connecting strip, a width of the sixth segment is greater than a width of the fifth segment, and a side of the sixth segment close to the fourth folded edge abuts against a side of the first fixing ring away from the first edge plate;

[0029] The fourth folded edge includes a seventh segment and an eighth segment which are arranged and connected in sequence away from the second connecting strip, one end of the seventh segment away from the eighth segment is vertically connected to the second end of the second connecting strip, the width of the eighth segment is greater than the width of the seventh segment, and a side of the eighth segment close to the third folded edge abuts against a side of the second fixing ring away from the second edge plate.

[0030] Optionally, a first clamping groove is formed on the side of the first fixing ring facing away from the first flange. The first clamping groove includes a first groove section and a second groove section that are arranged in sequence away from the second connecting strip and communicate with each other. The fifth body is inserted into the first groove section, and the sixth body is inserted into the second groove section. The width of the sixth body is greater than the width of the first groove section;

[0031] A second clamping groove is formed on the side of the second fixing ring facing away from the second flange. The second clamping groove includes a third groove section and a fourth groove section that are arranged in sequence away from the second connecting strip and communicate with each other. The seventh body is inserted into the third groove section, and the eighth body is inserted into the fourth groove section. The width of the eighth body is greater than the width of the third groove section.

[0032] A turbine rotor blade provided by the present application includes a tenon head, a blade body, a first flange, and a second flange. The blade body is integrally connected with the tenon head to form a blade body, and the tenon head is used to connect with a turbine disk. A first notch is formed on the first flange, and a second notch is formed on the second flange. After the first flange and the second flange are connected in a matching manner, the first notch and the second notch are combined to form a receiving groove. The blade body passes through the receiving groove, and the inner wall of the receiving groove fits with the outer wall of the blade body. Thus, the tenon head, the blade body, the first flange, and the second flange are combined to form a turbine rotor blade. Since the blade body made of ceramic matrix composite material is processed separately from the first flange and the second flange, the cross-sectional mutation from the blade body to the flange is avoided, thereby reducing the manufacturing difficulty, increasing the yield rate and reducing the cost, and also avoiding the weakening of the material properties of the ceramic matrix composite material due to the cross-sectional mutation. Description of the Drawings

[0033] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the related art, the following will briefly introduce the drawings required for use in the description of the specific embodiments or the related art. Obviously, the following drawings are some embodiments of the present application. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0034] Figure 1 It is a schematic structural diagram of a turbine rotor blade according to an embodiment of the present application;

[0035] Figure 2 It is an exploded view of a turbine rotor blade according to an embodiment of the present application;

[0036] Figure 3 It is a schematic structural diagram of a first perspective of a turbine rotor according to an embodiment of the present application;

[0037] Figure 4 is Figure 3 a partial enlarged schematic diagram of A in

[0038] Figure 5 It is a schematic diagram of the second perspective structure of a turbine rotor according to an embodiment of the present application;

[0039] Figure 6 It is Figure 5 a partial enlarged schematic diagram of B in

[0040] Figure 7 It is a schematic diagram of the turbine disk structure of a turbine rotor according to an embodiment of the present application;

[0041] Figure 8 It is a schematic diagram of the first retaining bar structure of a turbine rotor according to an embodiment of the present application;

[0042] Figure 9 It is a schematic diagram of the first perspective structure of the first fixing ring and the second fixing ring of a turbine rotor according to an embodiment of the present application;

[0043] Figure 10 It is Figure 9 a partial enlarged schematic diagram of C in

[0044] Figure 11 It is a schematic diagram of the first perspective structure of the first fixing ring and the second fixing ring of a turbine rotor according to an embodiment of the present application;

[0045] Figure 12 It is Figure 11 a partial enlarged schematic diagram of D in

[0046] Figure 13 It is a schematic diagram of the second retaining bar structure of a turbine rotor according to an embodiment of the present application.

[0047] Explanation of reference numerals:

[0048] 1. Tenon head; 2. Blade body; 3. First flange; 31. First notch; 32. First convex part; 321. Insertion slot; 33. First concave part; 34. First insertion protrusion; 4. Second flange; 41. Second notch; 42. Second convex part; 43. Second concave part; 431. Insertion part; 44. Second insertion protrusion; 5. Turbine disk; 51. Mortise; 6. First retaining bar; 61. First connecting bar; 62. First folded edge; 621. First section; 622. Second section; 63. Second folded edge; 631. Third section; 632. Fourth section; 7. First fixing ring; 71. First slot; 72. First clamping slot; 721. First slot section; 722. Second slot section; 8. Second fixing ring; 81. Second slot; 82. Second clamping slot; 821. Third slot section; 822. Fourth slot section; 9. Second retaining bar; 91. Second connecting bar; 92. Third folded edge; 921. Fifth section; 922. Sixth section; 93. Fourth folded edge; 931. Seventh section; 932. Eighth section. Detailed Implementation Manner

[0049] To make the objectives, technical solutions, and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application. Apparently, the described embodiments are some, but not all, of the embodiments of the present application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present application without creative efforts shall fall within the protection scope of the present application.

[0050] The following combines Figures 1 to 13 to describe the embodiments of the present application.

[0051] According to an embodiment of the present application, on the one hand, a turbine rotor blade is provided, as Figure 1 shown, including: a tenon 1, a blade body 2, a first flange 3, and a second flange 4. The blade body 2 and the tenon 1 are integrally connected to form a blade body, and the tenon 1 is used to connect to a turbine disk 5.

[0052] As Figure 2 shown, a first notch 31 with an opening is formed in the first flange 3, and a second notch 41 with an opening is formed in the second flange 4. After the first flange 3 and the second flange 4 are matched and connected, the opening of the first notch 31 abuts against the opening of the second notch 41, so that the first notch 31 and the second notch 41 are joined to form a receiving groove. The blade body 2 passes through the receiving groove and the inner wall of the receiving groove fits against the outer wall of the blade body 2, so that the tenon 1, the blade body 2, the first flange 3, and the second flange 4 are joined to form a turbine rotor blade.

[0053] With such a setting, when machining the turbine rotor blade, the blade body, the first flange 3, and the second flange 4 made of a ceramic matrix composite material can be machined separately. The first flange 3 and the second flange 4 are respectively joined on both sides of the blade body 2, so that the blade body 2 is passed through the receiving groove formed by the joining of the first notch 31 and the second notch 41, so that the tenon 1, the blade body 2, the first flange 3, and the second flange 4 are joined to form a turbine rotor blade.

[0054] Since the blade body 2 is machined separately from the first flange 3 and the second flange 4, the cross-sectional mutation from the blade body 2 to the flange is avoided, thereby reducing the manufacturing difficulty, increasing the yield rate and reducing the cost, and also avoiding the weakening of the material properties of the ceramic matrix composite material due to the cross-sectional mutation.

[0055] Among them, the blade body 2 may include a blade body main body section and a transition section. The blade body main body section is connected to the tenon 1 through the transition section, and the transition section passes through the receiving groove.

[0056] For the mating connection between the first flange 3 and the second flange 4, in an alternative embodiment, a first convex portion 32 and a first concave portion 33 are provided on the side where the opening of the first notch 31 on the first flange 3 is located, and a second convex portion 42 and a second concave portion 43 are provided on the side where the opening of the second notch 41 on the second flange 4 is located. The first convex portion 32 on the first flange 3 is inserted into the second concave portion 43 on the second flange 4 to achieve a mating connection, and at the same time, the second convex portion 42 on the second flange 4 is inserted into the first concave portion 33 on the first flange 3 to achieve a mating connection, so as to mate-connect the first flange 3 and the second flange 4. At this time, the opening of the first notch 31 just abuts against the notch of the second notch 41, so that the first notch 31 and the second notch 41 are joined to form a receiving groove.

[0057] In this way, through the positioning method of the mating connection between the first convex portion 32 and the second concave portion 43 and the mating connection between the second convex portion 42 and the first concave portion 33, the first flange 3 and the second flange 4 are mated and connected, and the installation is more convenient.

[0058] Specifically, a first recessed groove is formed on the side where the opening of the first notch 31 on the first flange 3 is located to form the first concave portion 33, and the remaining portion forms the first convex portion 32. A second recessed groove is formed on the side where the opening of the second notch 41 on the second flange 4 is located to form the second concave portion 43, and the remaining portion forms the second convex portion 42. In this way, when the first convex portion 32 on the first flange 3 extends into the second concave portion 43 on the second flange 4, the second convex portion 42 on the second flange 4 can simultaneously extend into the first concave portion 33 on the first flange 3.

[0059] In a further embodiment, as Figure 1 and Figure 2 shown, a plugging groove 321 is provided on the first convex portion 32, and a plugging portion 431 is provided in the second concave portion 43. When the first convex portion 32 is mated and connected with the second concave portion 43, the plugging portion 431 just inserts into the plugging groove 321, so as to further position and reinforce the mating connection between the first flange 3 and the second flange 4.

[0060] Specifically, a plugging groove 321 is formed by grooving on the first convex portion 32, and a plugging protrusion is provided inside the second concave portion 43 to form the plugging portion 431. When the first convex portion 32 is mated and connected with the second concave portion 43, the plugging protrusion just inserts into the plugging groove 321 formed by grooving on the first convex portion 32.

[0061] According to an embodiment of the present application, on the other hand, a turbine rotor is further provided, as Figure 3 shown, including a turbine disk 5 and any of the above turbine rotor blades.

[0062] As Figure 7As shown, a plurality of dovetail-shaped tenon grooves 51 are formed in the turbine disk 5. The tenon grooves 51 are evenly distributed along the circumferential direction of the turbine disk 5 and are all arranged along the axial direction of the turbine disk 5. Each tenon groove 51 penetrates through both end faces of the turbine disk 5, and a through groove is formed on the inner wall of the tenon groove 51, and the through groove penetrates through the circumferential surface of the turbine disk 5.

[0063] As Figure 3 shown, a plurality of turbine rotor blades are provided. The tenon 1 of each turbine rotor blade is correspondingly inserted into a tenon groove 51, so that the turbine rotor blades are evenly distributed along the circumferential direction of the turbine disk 5 to form a turbine rotor. The blade body 2 of the turbine rotor blade passes through the turbine disk 5 through the through groove.

[0064] During installation, the tenon 1 of the turbine rotor blade is inserted into the tenon groove 51 along the axial direction of the turbine disk 5 from the outside of the end face of the turbine disk 5, and at the same time, the blade body 2 of the turbine rotor blade is inserted into the through groove.

[0065] As an optional embodiment, as Figure 3 shown, the turbine rotor further includes a first retaining bar 6. As Figure 8 shown, the first retaining bar 6 includes a first connecting bar 61, a first flanging 62 and a second flanging 63.

[0066] The first connecting bar 61 has a first end and a second end. The first flanging 62 is vertically arranged at the first end of the first connecting bar 61, and the second flanging 63 is vertically arranged at the second end of the first connecting bar 61. The first connecting bar 61 is inserted into the tenon groove 51, and the first connecting bar 61 is located between the tenon 1 and the inner wall of the tenon groove 51. The first end and the second end of the first connecting bar 61 respectively pass through both ends of the tenon groove 51.

[0067] As Figures 3 to 8 shown, the turbine disk 5 has a first end face and a second end face. The first flanging 62 is arranged in a direction close to the tenon 1, so as to be attached to the first end face of the turbine disk 5. At this time, the first flanging 62 and the tenon 1 are distributed along the axial direction of the turbine disk 5. Thus, the first flanging 62 is in limit fit with the tenon 1 in the axial direction of the turbine disk 5 to limit the tenon 1 from sliding out of the first end of the tenon groove 51.

[0068] The second flanging 63 is arranged in a direction close to the tenon 1, so as to be attached to the second end face of the turbine disk 5. At this time, the second flanging 63 and the tenon 1 are distributed along the axial direction of the turbine disk 5. Thus, the second flanging 63 is in limit fit with the tenon 1 in the axial direction of the turbine disk 5 to limit the tenon 1 from sliding out of the second end of the tenon groove 51.

[0069] With such an arrangement, the first flanging 62 restricts the tenon 1 from detaching from the first end of the tenon groove 51, and the second flanging 63 restricts the tenon 1 from detaching from the second end of the tenon groove 51, thereby preventing the tenon 1 from slipping out of the tenon groove 51.

[0070] Specifically, the first stop strip 6 is initially straight. After threading the first stop strip 6 into the mortise groove 51, the first end and the second end of the first stop strip 6 respectively penetrate through both ends of the mortise groove 51. After inserting the tenon 1 into the mortise groove 51, the portion of the first stop strip 6 located within the mortise groove 51 is positioned between the tenon 1 and the inner wall of the mortise groove 51.

[0071] Thereafter, the first end of the first stop strip 6 is bent 90° towards the tenon 1 to form a first folded edge 62 until the first folded edge 62 abuts against the first end face of the turbine disk 5. At this time, the first folded edge 62 is in axial limit fit with the tenon 1 on the turbine disk 5.

[0072] The second end of the first stop strip 6 is bent 90° towards the tenon 1 to form a second folded edge 63 until the second folded edge 63 abuts against the second end face of the turbine disk 5. At this time, the second folded edge 63 is in axial limit fit with the tenon 1 on the turbine disk 5, achieving the limit of the tenon 1.

[0073] In an alternative embodiment, as Figure 8 shown, the first folded edge 62 includes a first section 621 and a second section 622. The first section 621 and the second section 622 are arranged in sequence in a direction away from the first connecting strip 61, that is, the first section 621 is perpendicularly connected to the first end of the first connecting strip 61, and the second section 622 is connected to the end of the first section 621 that is away from the first connecting strip 61. The width of the second section 622 is greater than the width of the first section 621. Therefore, the first folded edge 62 is generally in the shape of a "T".

[0074] Since the width of the mortise groove 51 gradually decreases radially outward of the turbine disk 5, when the first folded edge 62 is formed by bending the first end of the first stop strip 6, a portion of the second section 622 of the first folded edge 62 can be in contact with the first end face of the turbine disk 5. At this time, the remaining portion of the second section 622 and the first section 621 are in axial limit fit with the tenon 1 on the turbine disk 5.

[0075] The second folded edge 63 includes a third section 631 and a fourth section 632. The third section 631 and the fourth section 632 are arranged in sequence in a direction away from the first connecting strip 61, that is, the third section 631 is perpendicularly connected to the first end of the first connecting strip 61, and the fourth section 632 is connected to the end of the third section 631 that is away from the first connecting strip 61. The width of the fourth section 632 is greater than the width of the third section 631. Therefore, the second folded edge 63 is generally in the shape of a "T".

[0076] Since the width of the mortise groove 51 gradually decreases radially outward of the turbine disk 5, when the second folded edge 63 is formed by bending the second end of the first stop strip 6, a portion of the fourth section 632 of the second folded edge 63 can be in contact with the second end face of the turbine disk 5. At this time, the remaining portion of the fourth section 632 and the third section 631 are in axial limit fit with the tenon 1 on the turbine disk 5.

[0077] It should be noted that the width of the second section 622 or the fourth section 632 should be less than the maximum width of the mortise groove 51 to ensure that the first retaining strip 6 can pass through the mortise groove 51.

[0078] As an optional embodiment, as Figures 3 to 6 shown, the turbine rotor further includes a first fixing ring 7 and a second fixing ring 8.

[0079] As Figure 11 shown, a first slot 71 is formed on the end face of the first fixing ring 7. The first slot 71 is annular and arranged along the circumferential direction of the first fixing ring 7.

[0080] As Figure 2 shown, for the turbine rotor blade, a first plugging protrusion 34 is provided at one end of the first flange 3 facing away from the second flange 4. The first plugging protrusions 34 on the first flanges 3 of each turbine rotor blade are inserted into the first slot 71, so that the inner wall of the first slot 71 abuts against the first plugging protrusion 34 on the periphery, thereby restricting the first flange 3 from disengaging outward, and thus tightening and fixing each first flange 3 inward.

[0081] The first plugging protrusion 34 can be a protrusion provided at one end of the first flange 3 facing away from the second flange 4.

[0082] As Figure 9 shown, a second slot 81 is formed on the end face of the second fixing ring 8. The second slot 81 is annular and arranged along the circumferential direction of the second fixing ring 8.

[0083] As Figure 2 shown, for the turbine rotor blade, a second plugging protrusion 44 is provided at one end of the second flange 4 facing away from the first flange 3. The second plugging protrusions 44 on the second flanges 4 of each turbine rotor blade are inserted into the second slot 81, so that the inner wall of the second slot 81 abuts against the second plugging protrusion 44 on the periphery, thereby restricting the second flange 4 from disengaging outward, and thus tightening and fixing each second flange 4 inward.

[0084] The second plugging protrusion 44 can be a protrusion provided at one end of the second flange 4 facing away from the first flange 3.

[0085] With such a setting, the fixation of the first flange 3 and the second flange 4 is achieved, and at the same time, the connection stability between the turbine rotor blade and the turbine disk 5 is increased.

[0086] The surfaces of the first plug-in protrusion 34 and the second plug-in protrusion 44 are both coated with a wear-resistant coating. After the first plug-in protrusion 34 is inserted into the first slot 71, the wear-resistant coating on the first plug-in protrusion 34 is located between the outer wall of the first plug-in protrusion 34 and the inner wall of the first slot 71, thereby reducing the wear on the outer wall of the first plug-in protrusion 34 and the inner wall of the first slot 71.

[0087] After the second plugging protrusion 44 is inserted into the second slot 81 , the wear-resistant coating on the second plugging protrusion 44 is located between the outer wall of the second plugging protrusion 44 and the inner wall of the second slot 81 , reducing wear on the outer wall of the second plugging protrusion 44 and the inner wall of the second slot 81 .

[0088] In an optional embodiment, if Figures 3 to 6 As shown, the turbine rotor also includes a second baffle bar 9. Figure 13 As shown, the second stop bar 9 includes a second connecting bar 91 , a third folded edge 92 and a fourth folded edge 93 .

[0089] The second connecting strip 91 has a first end and a second end, the third folded edge 92 is disposed at the first end of the second connecting strip 91, and the third folded edge 92 is perpendicular to the second connecting strip 91. The fourth folded edge 93 is vertically disposed at the second end of the second connecting strip 91, and the fourth folded edge 93 is perpendicular to the second connecting strip 91.

[0090] For the first edge plates 3 of any two adjacent turbine rotor blades, the second connecting strip 91 of a second stop strip 9 is attached to the joint of the two first edge plates 3 on one side close to the peripheral surface of the turbine disk 5, so that the two adjacent first edge plates 3 are attached to the second connecting strip 91. At the same time, for the second edge plates 4 of any two adjacent turbine rotor blades, the second connecting strip 91 is attached to the joint of the two second edge plates 4 on one side close to the peripheral surface of the turbine disk 5, so that the two adjacent second edge plates 4 are attached to the second connecting strip 91. In this way, the second connecting strip 91 covers the joint between the two adjacent turbine rotor blades.

[0091] The third folded edge 92 is arranged in a direction close to the first edge plate 3, so that the side close to the fourth folded edge 93 abuts against the side of the first fixing ring 7 away from the first edge plate 3. The fourth folded edge 93 is arranged in a direction close to the second edge plate 4, so that the side close to the third folded edge 92 abuts against the side of the second fixing ring 8 away from the second edge plate 4.

[0092] Thus, the third folded edge 92 and the fourth folded edge 93 clamp the first fixing ring 7, the first edge plate 3, the second edge plate 4 and the second fixing ring 8 in the middle in sequence, so as to prevent the first fixing ring 7 from being separated from the first edge plate 3, the first edge plate 3 from being separated from the second edge plate 4, and the second edge plate 4 from being separated from the second fixing ring 8.

[0093] Specifically, the second retaining strip 9 is initially straight. The middle part of the second retaining strip 9 is attached to the joint between two adjacent turbine rotor blades. Then, the first end of the second retaining strip 9 is bent 90° towards the direction close to the first flange 3 to form a third folded edge 92, so that the third folded edge 92 abuts against the side of the first fixing ring 7 away from the first flange 3. The second end of the second retaining strip 9 is bent 90° towards the direction close to the second flange 4 to form a fourth folded edge 93, so that the fourth folded edge 93 abuts against the side of the second fixing ring 8 away from the second flange 4.

[0094] In an alternative embodiment, Figure 13 As shown, the third folded edge 92 includes a fifth section 921 and a sixth section 922. The fifth section 921 and the sixth section 922 are arranged in sequence along the direction away from the second connecting strip 91, that is, the fifth section 921 is perpendicularly connected to the first end of the second connecting strip 91, and the sixth section 922 is connected to the end of the fifth section 921 away from the second connecting strip 91. The width of the sixth section 922 is greater than the width of the fifth section 921. Therefore, the third folded edge 92 is generally in a "T" shape.

[0095] In this way, for the third folded edge 92, the side of the sixth section 922 close to the fourth folded edge 93 abuts against the side of the first fixing ring 7 away from the first flange 3, and the abutting surface is larger, increasing the abutting reliability. Moreover, the side of the fifth section 921 close to the fourth folded edge 93 also abuts against the side of the first fixing ring 7 away from the first flange 3.

[0096] The fourth folded edge 93 includes a seventh section 931 and an eighth section 932. The seventh section 931 and the eighth section 932 are arranged in sequence along the direction away from the second connecting strip 91, that is, the seventh section 931 is perpendicularly connected to the first end of the eighth connecting strip, and the eighth section 932 is connected to the end of the seventh section 931 away from the second connecting strip 91. The width of the eighth section 932 is greater than the width of the seventh section 931. Therefore, the fourth folded edge 93 is generally in a "T" shape.

[0097] In this way, for the fourth folded edge 93, the side of the eighth section 932 close to the third folded edge 92 abuts against the side of the second fixing ring 8 away from the second flange 4, and the abutting surface is larger, increasing the abutting reliability. Moreover, the side of the seventh section 931 close to the third folded edge 92 also abuts against the side of the second fixing ring 8 away from the second flange 4.

[0098] In a further embodiment, as Figure 9 and Figure 10As shown, a first card slot 72 is formed on the side of the first fixing ring 7 away from the first flange 3. The first card slot 72 includes a first slot section 721 and a second slot section 722. The first slot section 721 and the second slot section 722 are arranged in sequence in the direction away from the second connecting strip 91, and the first slot section 721 and the second slot section 722 communicate with each other. When the first end of the second retaining strip 9 is bent 90° towards the first flange 3 to form a third folded edge 92, the fifth body 921 is exactly inserted into the first slot section 721, and the sixth body 922 is exactly inserted into the second slot section 722.

[0099] The width of the sixth body 922 is greater than the width of the first slot section 721, so that the sixth body 922 cannot enter the first slot section 721, thus preventing the sixth body 922 from disengaging from the second slot section 722 and increasing the stability of the second retaining strip 9.

[0100] As Figure 11 and Figure 12 shown, a second card slot 82 is formed on the side of the second fixing ring 8 away from the second flange 4. The second card slot 82 includes a third slot section 821 and a fourth slot section 822. The third slot section 821 and the fourth slot section 822 are arranged in sequence in the direction away from the second connecting strip 91, and the third slot section 821 and the fourth slot section 822 communicate with each other. When the second end of the second retaining strip 9 is bent 90° towards the second flange 4 to form a fourth folded edge 93, the seventh body 931 is exactly inserted into the third slot section 821, and the eighth body 932 is exactly inserted into the fourth slot section 822.

[0101] The width of the eighth body 932 is greater than the width of the third slot section 821, so that the eighth body 932 cannot enter the third slot section 821, thus preventing the eighth body 932 from disengaging from the fourth slot section 822 and increasing the stability of the second retaining strip 9.

[0102] Although the embodiments of the present application have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the present application, and such modifications and variations fall within the scope defined by the present application.

Claims

1. A turbine rotor blade, characterized in that, Comprising: A tenon (1), adapted to be connected to a turbine disk (5); A blade body (2), integrally connected to the tenon (1); A first flange (3), provided with a first notch (31); A second flange (4), provided with a second notch (41), the second flange (4) being connected in a matching manner with the first flange (3), the second notch (41) and the first notch (31) being joined to form a receiving groove, the blade body (2) passing through the receiving groove, and the inner wall of the receiving groove being in contact with the outer wall of the blade body (2).

2. The turbine rotor blade according to claim 1, characterized in that, The first flange (3) is provided with a first protrusion (32) and a first recess (33), the second flange (4) is provided with a second protrusion (42) and a second recess (43), the first protrusion (32) is connected in a matching manner with the second recess (43), and the first recess (33) is connected in a matching manner with the second protrusion (42).

3. The turbine rotor blade according to claim 2, characterized in that, The first protrusion (32) is provided with a plugging groove (321), the second recess (43) is provided with a plugging portion (431), and the plugging portion (431) is inserted into the plugging groove (321).

4. A turbine rotor, characterized in that, Comprising: The turbine rotor blade according to any one of claims 1-3; A turbine disk (5), axially penetratingly provided with a plurality of tenon grooves (51), each tenon groove (51) being circumferentially distributed along the turbine disk (5), each of the turbine rotor blades being circumferentially distributed along the turbine disk (5), the tenons (1) of each of the turbine rotor blades being inserted into the tenon grooves (51) in a one-to-one correspondence, and the inner wall of the tenon groove (51) having a through groove for the blade body (2) to pass through.

5. The turbine rotor according to claim 4, characterized in that, Further comprising: A first retaining strip (6), comprising a first connecting strip (61), a first folded edge (62) provided at the first end of the first connecting strip (61), and a second folded edge (63) provided at the second end of the first connecting strip (61), the first connecting strip (61) being inserted into the tenon groove (51) and located between the tenon (1) and the inner wall of the tenon groove (51), One side of the first folded edge (62) close to the second folded edge (63) is in contact with the first end face of the turbine disk (5), and the first folded edge (62) is in limit cooperation with the tenon (1) in the axial direction of the turbine disk (5); One side of the second folded edge (63) close to the first folded edge (62) is in contact with the second end face of the turbine disk (5), and the second folded edge (63) is in limit cooperation with the tenon (1) in the axial direction of the turbine disk (5).

6. The turbine rotor according to claim 5, characterized in that, The first folded edge (62) comprises a first section (621) and a second section (622) which are sequentially arranged and connected away from the first connecting strip (61), one end of the first section (621) away from the second section (622) is perpendicularly connected to the first end of the first connecting strip (61), the width of the second section (622) is greater than the width of the first section (621), and the second section (622) is in contact with the first end face of the turbine disk (5); The second folded edge (63) comprises a third segment (631) and a fourth segment (632) which are arranged and connected in sequence away from the first connecting strip (61); one end of the third segment (631) away from the fourth segment (632) is vertically connected to the second end of the first connecting strip (61); the width of the fourth segment (632) is greater than the width of the third segment (631); and the fourth segment (632) is in contact with the second end surface of the turbine disc (5).

7. The turbine rotor according to claim 4, characterized in that Also includes: A first fixing ring (7) has an end surface provided with a first slot (71) in the circumferential direction, an end of the first edge plate (3) facing away from the second edge plate (4) is provided with a first plugging protrusion (34), and the first plugging protrusion (34) on the first edge plate (3) of each turbine rotor blade is plugged into the first slot (71); The second fixing ring (8) has a second slot (81) arranged on its end surface along the circumferential direction, and a second plug-in protrusion (44) is arranged on one end of the second edge plate (4) facing away from the first edge plate (3), and the second plug-in protrusion (44) on the second edge plate (4) of each turbine rotor blade is plugged into the second slot (81).

8. The turbine rotor according to claim 7, wherein, Also includes: The second stop bar (9) comprises a second connecting bar (91), a third folded edge (92) arranged at the first end of the second connecting bar (91) and a fourth folded edge (93) arranged at the second end of the second connecting bar (91); one side of two adjacent first edge plates (3) and one side of two adjacent second edge plates (4) close to the peripheral surface of the turbine disc (5) are both in contact with the second connecting bar (91); the side of the third folded edge (92) close to the fourth folded edge (93) abuts against the side of the first fixing ring (7) facing away from the first edge plate (3); and the side of the fourth folded edge (93) close to the third folded edge (92) abuts against the side of the second fixing ring (8) facing away from the second edge plate (4).

9. The turbine rotor according to claim 8, characterized in that, The third folded edge (92) comprises a fifth segment (921) and a sixth segment (922) which are arranged and connected in sequence away from the second connecting strip (91); one end of the fifth segment (921) away from the sixth segment (922) is vertically connected to the first end of the second connecting strip (91); the width of the sixth segment (922) is greater than the width of the fifth segment (921); and a side of the sixth segment (922) close to the fourth folded edge (93) abuts against a side of the first fixing ring (7) away from the first edge plate (3); The fourth folded edge (93) comprises a seventh segment (931) and an eighth segment (932) which are arranged and connected in sequence away from the second connecting strip (91); one end of the seventh segment (931) away from the eighth segment (932) is vertically connected to the second end of the second connecting strip (91); the width of the eighth segment (932) is greater than the width of the seventh segment (931); and a side of the eighth segment (932) close to the third folded edge (92) abuts against a side of the second fixing ring (8) away from the second edge plate (4).

10. The turbine rotor according to claim 9, characterized in that, A first slot (72) is provided on a side of the first fixing ring (7) away from the first edge plate (3); the first slot (72) comprises a first slot section (721) and a second slot section (722) which are arranged in sequence away from the second connecting strip (91) and are connected to each other; the fifth section (921) is inserted into the first slot section (721); the sixth section (922) is inserted into the second slot section (722); and the width of the sixth section (922) is greater than the width of the first slot section (721); A second slot (82) is provided on a side of the second fixing ring (8) away from the second edge plate (4); the second slot (82) comprises a third slot section (821) and a fourth slot section (822) which are arranged in sequence away from the second connecting strip (91) and are interconnected; the seventh section (931) is inserted into the third slot section (821); the eighth section (932) is inserted into the fourth slot section (822); and the width of the eighth section (932) is greater than the width of the third slot section (821).

Images