Baffle connecting structure

Abstract

The invention relates to the technical field of aero-engines, in particular to a baffle connecting structure which comprises a turbine blade, a turbine disc, an elastic check ring, a baffle and a pre-swirl nozzle. An annular groove is formed in the turbine disc; the elastic check ring is provided with an opening and arranged in the annular groove in a contracted mode. The two ends of the baffle are connected with the turbine disc, one end of the baffle is inserted into the annular groove, and the elastic check ring is clamped between the baffle and the groove wall of the annular groove. A cooling channel is defined by the baffles and the turbine disc. A cooling cavity is defined by the prewhirl nozzle and the baffle; a receiving hole is formed in the baffle, and the cooling channel communicates with the cooling cavity through the receiving hole. The pressure of cold air entering the cooling channel can be improved, the sealing pressure is guaranteed, the cooling effect is improved, the deformation probability of the baffle and the turbine disc is reduced, the temperature gradient of the turbine disc is reduced, thermal stress is reduced, the temperature level of the connecting position of all parts is reduced, and the service life of the turbine rotor is prolonged.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine technology, and specifically relates to a baffle connection structure. Background Technology

[0002] The baffles of the high-pressure and low-pressure turbine disks of aero engines are used to axially position the turbine blades and provide cooling channels for the turbine blades and turbine disks. They are one of the important functional components of the turbine rotor.

[0003] Existing boltless connections between baffles and turbine disks are typically used. Due to the high rotational speed of the turbine rotor and the large centrifugal load on the baffle, boltless connections prevent excessive local stress in the connection holes, which could compromise component reliability and lifespan. These boltless connections mainly consist of baffles, turbine disks, turbine blades, retaining rings, and circumferential stop structures. However, to ensure reliable support of the baffle on the turbine disk, the baffle size is usually reduced, and the relative connection position between the baffle and turbine disk is increased. This results in a shorter cooling channel between the baffle and turbine disk. Furthermore, because the cooling air needs to simultaneously cool and seal multiple structural components, the sealing pressure is lower, affecting cooling efficiency. Higher temperatures can even cause deformation of the baffle and turbine disk, increasing the temperature gradient of the turbine disk and the temperature level at the connection points, ultimately reducing the turbine rotor's lifespan. Summary of the Invention

[0004] To address the above problems, this invention proposes a baffle connection structure, comprising: Connected turbine blades and turbine disk, wherein an annular groove is formed on the turbine disk; An elastic retaining ring, wherein the elastic retaining ring is provided with an opening and is retracted within the annular groove; A baffle plate, the two ends of which are connected to the turbine disk, and one end of the baffle plate is inserted into the annular groove. The elastic retaining ring is engaged between the baffle plate and the groove wall of the annular groove. The baffle and the turbine disk together form a cooling channel; A pre-rotating nozzle, which together with the baffle forms a cooling chamber; The baffle is provided with a receiving hole, and the cooling channel is connected to the cooling cavity through the receiving hole.

[0005] Furthermore, the turbine disk is provided with a first stop and a second stop, the second stop being adjacent to the annular groove; The baffle has a first bend and a second bend at both ends on the side near the turbine disk. The first bend is set to correspond to the first stop. The second bend is set to correspond to the second stop.

[0006] Furthermore, there is a small gap fit between the first bend and the first stop; The second bend and the second stop are interference fit.

[0007] Furthermore, the baffle is provided with a first sealing grate and a second sealing grate on the side away from the turbine disk; The two ends of the pre-rotating nozzle are respectively connected to the first sealing grate and the second sealing grate.

[0008] Furthermore, a sealing ring is fitted onto the turbine disk; the sealing ring is located between the turbine disk and the end of the baffle furthest from the annular groove; The sealing ring is respectively embedded on both sides of the turbine disk and the end of the baffle away from the annular groove.

[0009] Furthermore, a pin is inserted into the turbine disk, and the end of the baffle away from the annular groove is engaged with the pin; The pins are provided in at least three, and the at least three pins are evenly arranged along the circumference of the turbine disk.

[0010] Furthermore, at least two crescent-shaped grooves are formed on the wall of the annular groove, and the at least two crescent-shaped grooves are symmetrical to each other; After the elastic retaining ring contracts, the two sides of the opening of the elastic retaining ring engage with one of the crescent grooves.

[0011] Furthermore, the elastic retaining ring has connecting holes on both sides of its opening, and the two connecting holes are used to connect with the tooling, so that the elastic retaining ring can be driven to contract by the tooling.

[0012] Furthermore, a nail hole is provided on the end face of the annular groove at the groove opening, and a pin is movably inserted into the nail hole; The nail hole is provided with at least three holes, and the at least three nail holes are evenly arranged along the circumference of the annular groove.

[0013] Furthermore, a pull-out ring is provided protruding on the side of the baffle away from the turbine disk.

[0014] Compared with the prior art, the baffle connection structure of the present invention has at least the following advantages: through the cooling chamber formed by the pre-swirl nozzle and the baffle, the receiving hole of the baffle, and the cooling channel formed by the baffle and the turbine disk, the low-temperature cold air from the pre-swirl nozzle can be directly introduced into the receiving hole of the baffle and reach the cooling channel through the cooling chamber, thereby cooling the turbine disk and turbine blades. It can increase the pressure of the low-temperature cold air entering the cooling channel to ensure the sealing pressure during cooling and sealing, thereby improving the cooling effect, reducing the probability of deformation of the baffle and turbine disk, thereby reducing the temperature gradient of the turbine disk, reducing thermal stress, and reducing the temperature level at the connection of various components, thus improving the service life of the turbine rotor.

[0015] Other features and advantages of the invention will be set forth in the following description, and will be apparent in part from the description, or may be learned by practicing the invention. The objects and other advantages of the invention may be realized and obtained by means of the structures pointed out in the description and the drawings. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 A schematic diagram of the baffle connection structure in an embodiment of the present invention is shown; Figure 2 A schematic diagram of the cold air flow path of the baffle connection structure in an embodiment of the present invention is shown; Figure 3 A schematic diagram of the installation of the elastic retaining ring and turbine disk in an embodiment of the present invention is shown; Figure 4 for Figure 3 A partially enlarged view of the installation of the elastic retaining ring and turbine disk; Figure 5 A schematic diagram of the baffle in an embodiment of the present invention is shown; Figure 6 A schematic diagram of the installation method of the baffle in an embodiment of the present invention is shown.

[0018] In the diagram, 1 is the turbine blade; 101 is the first stop; 102 is the second stop; 103 is the cooling chamber; 104 is the cooling channel; 2 is the sealing ring; 3 is the baffle; 31 is the first sealing grate; 32 is the second sealing grate; 33 is the receiving hole; 34 is the removal ring; 4 is the pre-rotating nozzle; 5 is the elastic retaining ring; 51 is the connecting hole; 6 is the turbine disk; 61 is the crescent groove; 62 is the pin hole; 63 is the annular groove; and 7 is the pin. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0020] Reference Figure 1 This invention provides a baffle connection structure, including: connected turbine blades 1 and turbine disk 6, elastic retaining ring 5, baffle 3, and pre-swirl nozzle 4. The turbine disk 6 has an annular groove 63. The elastic retaining ring 5 has an opening and is retracted within the annular groove 63. Both ends of the baffle 3 are connected to the turbine disk 6, and one end of the baffle 3 is inserted into the annular groove 63. The elastic retaining ring 5 is engaged between the baffle 3 and the groove wall of the annular groove 63. The baffle 3 and the turbine disk 6 together form a cooling channel 104. The pre-swirl nozzle 4 and the baffle 3 together form a cooling cavity 103. The baffle 3 has a receiving hole 33, through which the cooling channel 104 communicates with the cooling cavity 103.

[0021] Specifically, the turbine blade 1 is mounted on the turbine disk 6. The turbine disk 6 has an annular groove 63. The elastic retaining ring 5 is a circular ring structure with a circumferential opening. By squeezing and releasing the elastic retaining ring 5, the entire elastic retaining ring 5 can be driven to shrink or loosen, thereby changing the diameter of the elastic retaining ring 5. When the diameter of the elastic retaining ring 5 is adapted to the size of the annular groove 63, the elastic retaining ring 5 can be shrunk and placed in the annular groove 63, thus completing the initial installation of the elastic retaining ring 5 in the annular groove 63. Both ends of the baffle 3 are connected to the turbine disk 6. One end of the baffle 3 extends towards the annular groove 63 and is inserted into the annular groove 63, so that the elastic retaining ring 5 can be located between the groove wall of the annular groove 63 and the end of the baffle 3 inserted into the annular groove 63, and is engaged with the end of the baffle 3 inserted into the annular groove 63. The elastic retaining ring 5 is used to fix the end of the baffle 3 inserted into the annular groove 63, thereby improving the connection stability of the baffle 3. There is a gap between the baffle 3 and the turbine disk 6, so that the baffle 3 and the turbine disk 6 together form a cooling channel 104. There is also a gap between the pre-swirl nozzle 4 and the baffle 3, so that the pre-swirl nozzle 4 and the baffle 3 together form a cooling cavity 103. The baffle 3 is provided with a receiving hole 33, and the two ends of the receiving hole 33 are respectively set towards the cooling channel 104 and the cooling cavity 103, so that the cooling channel 104 communicates with the cooling cavity 103 through the receiving hole 33. The cooling chamber 103 formed by the pre-swirl nozzle 4 and the baffle 3, the receiving hole 33 of the baffle 3, and the cooling channel 104 formed by the baffle 3 and the turbine disk 6, are connected to each other. This allows the low-temperature cold air from the pre-swirl nozzle 4 to be directly introduced into the receiving hole 33 of the baffle 3 and into the cooling channel 104, thereby cooling the turbine disk 6 and the turbine blades 1. This increases the pressure of the low-temperature cold air entering the cooling channel 104 to ensure the sealing pressure during cooling and sealing, thereby improving the cooling effect, reducing the probability of deformation of the baffle 3 and the turbine disk 6, reducing the temperature gradient of the turbine disk 6, reducing thermal stress, and reducing the temperature level at the connection of various components, thus improving the service life of the turbine rotor.

[0022] Furthermore, during the installation and assembly process, the elastic retaining ring 5 is retracted and placed in the annular groove 63 of the turbine disk 6, and the elastic retaining ring 5 is lower than the minimum inner ring surface of the baffle 3. After one end of the baffle 3 is inserted into the annular groove 63 and is axially pressed by tooling, the elastic retaining ring 5 is released, so that the elastic retaining ring 5 can pop out between the turbine disk 6 and the end of the baffle 3 inserted into the annular groove 63, thereby achieving axial limitation of the baffle 3 and also achieving axial limitation of the turbine blade 1.

[0023] In some specific embodiments of the present invention, reference is made to... Figure 2The turbine disk 6 is provided with a first stop 101 and a second stop 102, with the second stop 102 adjacent to the annular groove 63. The baffle 3 has a first bend and a second bend at both ends on the side closest to the turbine disk 6. The first bend corresponds to the first stop 101, and the second bend corresponds to the second stop 102.

[0024] Specifically, the turbine disk 6 has a first stop 101 and a second stop 102 protruding from it. The first stop 101 is located near the turbine blade 1, and the second stop 102 is located adjacent to the annular groove 63. Furthermore, the baffle 3 has a first bend and a second bend at both ends on the side near the turbine disk 6. The first bend corresponds to the first stop 101, allowing them to be positioned against each other. The second bend corresponds to the second stop 102, allowing them to be positioned against each other. Through the cooperation of the first stop 101 and the second stop 102 with the first and second bends respectively, the baffle 3 achieves a simply supported assembly state, greatly improving the connection stability of the baffle 3 under all operating conditions.

[0025] Furthermore, a first radial mating surface is formed on the first stop 101, a second radial mating surface is formed on the second stop 102, a first bent radial mating surface is formed on the first bend, and a second bent radial mating surface is formed on the second bend. After the installation and assembly between the baffle 3 and the turbine disk 6 are completed, the first radial mating surface of the first stop 101 and the first bent radial mating surface are fitted together, thereby forming a first centering structure at the junction of the first stop 101 and the first bend. The second radial mating surface of the second stop 102 and the second bent radial mating surface are fitted together, thereby forming a second centering structure at the junction of the second stop 102 and the second bend. This improves the connection reliability of the boltless baffle connection structure.

[0026] In some specific embodiments of the present invention, reference is made to... Figure 2 The first bend and the first stop 101 are fitted with a small clearance. The second bend and the second stop 102 are fitted with an interference fit.

[0027] Specifically, because the first stop 101 is located close to the turbine blade 1, and the second stop 102 is located adjacent to the annular groove 63, the second stop 102 is positioned further away from the turbine flow channel than the first stop 101. This results in a significantly lower temperature at the second stop 102 during operation compared to the first stop 101, ensuring better deformation matching capability for the second stop 102. Therefore, the second bend and the second stop 102 are designed with an interference fit of H7 / r6, making the second stop 102 the primary centering point. Conversely, the second bend and the second stop 102 are designed with a small clearance fit of H7 / g6, making the first stop 101 an auxiliary centering point. By centering the first stop 101 and the second stop 102 separately, the connection reliability of this boltless baffle connection structure can be further improved.

[0028] In some specific embodiments of the present invention, reference is made to... Figure 2 The baffle 3 is provided with a first sealing grate 31 and a second sealing grate 32 on the side away from the turbine disk 6. The two ends of the pre-rotating nozzle 4 are connected to the first sealing grate 31 and the second sealing grate 32 respectively.

[0029] Specifically, the side of the baffle 3 away from the turbine disk 6 extends away from the turbine disk 6 and is provided with a first sealing grate 31 and a second sealing grate 32. The second sealing grate 32 is positioned near the second stop 102, and the first sealing grate 31 is positioned near the first stop 101. The two ends of the pre-swirl nozzle 4 engage and connect with the first sealing grate 31 and the second sealing grate 32, respectively. Thus, the pre-swirl nozzle 4, together with the first and second sealing grate 31 and the second sealing grate 32 of the baffle 3, forms a separate cooling chamber 103. This allows the low-temperature cold air from the pre-swirl nozzle 4 to directly enter the receiving hole 33 of the baffle 3 through the cooling chamber 103 and reach the cooling channel 104, thereby cooling the turbine disk 6 and the turbine blades 1, improving the cooling effect, and increasing the pressure of the low-temperature cold air entering the cooling channel 104 to ensure the sealing pressure during cooling and sealing, further enhancing the cooling effect. This reduces the probability of deformation of the baffle 3 and turbine disk 6, thereby reducing the temperature gradient of the turbine disk 6, reducing thermal stress, and lowering the temperature level at the connection points of various components, thus improving the service life of the turbine rotor.

[0030] In some specific embodiments of the present invention, reference is made to... Figure 1 A sealing ring 2 is fitted onto the turbine disk 6. The sealing ring 2 is located between the turbine disk 6 and the end of the baffle 3 away from the annular groove 63. The two sides of the sealing ring 2 are respectively embedded in the ends of the turbine disk 6 and the baffle 3 away from the annular groove 63.

[0031] Specifically, a sealing ring 2 is fitted onto the turbine disk 6. The sealing ring 2 is located between the turbine disk 6 and the end of the baffle 3 away from the annular groove 63, and between the first stop 101 and the turbine blade 1. The two sides of the sealing ring 2 are respectively embedded in the ends of the turbine disk 6 and the baffle 3 away from the annular groove 63. The sealing ring 2 seals the cooling channel 104, ensuring its sealing effect and thus guaranteeing the cooling effect of the air entering the cooling channel 104.

[0032] In some specific embodiments of the present invention, reference is made to... Figure 1 A pin 7 is inserted into the turbine disk 6, and the end of the baffle 3 away from the annular groove 63 is engaged with the pin 7. At least three pins 7 are provided, and these three pins 7 are evenly distributed along the circumference of the turbine disk 6. Specifically, the pins 7 inserted into the turbine disk 6 are positioned towards the baffle 3, allowing the end of the baffle 3 away from the annular groove 63 to engage with the pins 7. This pin insertion provides circumferential stopping between the baffle 3 and the turbine disk 6, further improving the connection stability between the baffle 3 and the turbine disk 6. Furthermore, the presence of at least three pins 7, evenly distributed along the circumference of the turbine disk 6, compensates for any loss of balance in the turbine disk 6 due to the pins 7.

[0033] In some specific embodiments of the present invention, reference is made to... Figure 3 and Figure 4 The annular groove 63 has at least two crescent-shaped grooves 61 on its groove wall, and the at least two crescent-shaped grooves 61 are symmetrical to each other. After the elastic retaining ring 5 retracts, the two sides of the opening of the elastic retaining ring 5 engage with one of the crescent-shaped grooves 61.

[0034] Specifically, at least two crescent-shaped grooves 61 are formed on the wall of the annular groove 63. Protrusions are provided on both sides of the opening of the elastic retaining ring 5. When the elastic retaining ring 5 contracts, the protrusions on both sides of the opening of the elastic retaining ring 5 can be inserted into one of the crescent-shaped grooves 61, thus temporarily fixing the elastic retaining ring 5. After one end of the baffle 3 is inserted into the annular groove 63 and axially pressed by a tool, the protrusions on both sides of the opening of the elastic retaining ring 5 are released from the crescent-shaped groove 61, thus preventing the elastic retaining ring 5 from loosening. This allows the elastic retaining ring 5 to pop out between the turbine disk 6 and the end of the baffle 3 inserted into the annular groove 63, achieving axial positioning of the baffle 3 and also axial positioning of the turbine blade 1. The crescent-shaped groove 61 facilitates the assembly and disassembly of the retaining ring, while the other crescent-shaped groove 61 compensates for the loss of balance in the turbine disk 6 caused by the first crescent-shaped groove 61.

[0035] In some specific embodiments of the present invention, reference is made to... Figure 4The elastic retaining ring 5 has connecting holes 51 on both sides of its opening. These two connecting holes 51 are used to connect with a tooling fixture, which then drives the elastic retaining ring 5 to contract. Specifically, the connecting holes 51 on both sides of the opening of the elastic retaining ring 5 allow the tooling fixture to connect to both sides of the opening, facilitating the tooling fixture to compress and release the elastic retaining ring 5.

[0036] In some specific embodiments of the present invention, reference is made to... Figure 3 A pin hole 62 is provided on the end face of the annular groove 63 at the groove opening, and a pin 7 is movably inserted into the pin hole 62. At least three pin holes 62 are provided, and these at least three pin holes 62 are evenly distributed along the circumference of the annular groove 63. Specifically, the pin hole 62 provided on the end face of the annular groove 63 at the groove opening, through the insertion of the pin 7 into the pin hole 62, can cooperate with the baffle 3, thereby further achieving circumferential stopping of the baffle 3. The fact that at least three pin holes 62 are provided, and that these at least three pin holes 62 are evenly distributed along the circumference of the annular groove 63, can compensate for the loss of balance of the turbine disk 6 due to the pin hole 62.

[0037] In some specific embodiments of the present invention, reference is made to... Figure 5 and Figure 6 A pull-out ring 34 protrudes from the side of the baffle 3 away from the turbine disk 6. Specifically, by holding the pull-out ring 34, the baffle 3 can be driven to move closer to or away from the turbine disk 6, thereby facilitating the mutual engagement of the first radial mating surface of the first stop 101 with the first bent radial mating surface of the first bend, and the mutual engagement of the second radial mating surface of the second stop 102 with the second bent radial mating surface of the second bend, thus facilitating installation and assembly.

[0038] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A baffle connection structure, characterized in that, include: The turbine blades (1) and turbine disk (6) are connected, and the turbine disk (6) has an annular groove (63). An elastic retaining ring (5) is provided with an opening, and the elastic retaining ring (5) is retracted and disposed within the annular groove (63); Baffle (3), both ends of the baffle (3) are connected to the turbine disk (6), and one end of the baffle (3) is inserted into the annular groove (63), and the elastic retaining ring (5) is stuck between the baffle (3) and the groove wall of the annular groove (63); The baffle (3) and the turbine disk (6) together form a cooling channel (104); A pre-rotating nozzle (4) is formed by the pre-rotating nozzle (4) and the baffle (3) together to form a cooling chamber (103); The baffle (3) has a receiving hole (33), and the cooling channel (104) is connected to the cooling cavity (103) through the receiving hole (33).

2. The baffle connection structure according to claim 1, characterized in that, The turbine disk (6) is provided with a first stop (101) and a second stop (102), the second stop (102) being adjacent to the annular groove (63); The baffle (3) has a first bend and a second bend at both ends on the side near the turbine disk (6); The first bend is set corresponding to the first stop (101); The second bend is set in correspondence with the second stop (102).

3. The baffle connection structure according to claim 2, characterized in that, The first bend and the first stop (101) are fitted with a small clearance; The second bend and the second stop (102) are interference fit.

4. The baffle connection structure according to claim 1, characterized in that, The baffle (3) is provided with a first sealing tooth (31) and a second sealing tooth (32) on the side away from the turbine disk (6); The two ends of the pre-rotating nozzle (4) are respectively connected to the first sealing grate (31) and the second sealing grate (32).

5. The baffle connection structure according to claim 1, characterized in that, A sealing ring (2) is fitted on the turbine disk (6); the sealing ring (2) is located between the turbine disk (6) and the end of the baffle (3) away from the annular groove (63); The sealing ring (2) is respectively embedded on both sides of the turbine disk (6) and the end of the baffle (3) away from the annular groove (63).

6. The baffle connection structure according to claim 1, characterized in that, A pin (7) is inserted into the turbine disk (6), and the end of the baffle (3) away from the annular groove (63) is engaged with the pin (7); At least three pins (7) are provided, and the at least three pins (7) are evenly arranged along the circumference of the turbine disk (6).

7. The baffle connection structure according to claim 1, characterized in that, The annular groove (63) has at least two crescent-shaped grooves (61) on its groove wall, and the at least two crescent-shaped grooves (61) are symmetrical to each other; After the elastic retaining ring (5) contracts, the two sides of the opening of the elastic retaining ring (5) engage with one of the crescent grooves (61).

8. The baffle connection structure according to claim 1, characterized in that, The elastic retaining ring (5) has connecting holes (51) on both sides of its opening. The two connecting holes (51) are used to connect with the tooling, and the tooling drives the elastic retaining ring (5) to contract.

9. The baffle connection structure according to claim 1, characterized in that, A nail hole (62) is provided on the end face of the groove opening of the annular groove (63), and a pin (7) is movably inserted into the nail hole (62); The nail hole (62) has at least three holes, and the at least three nail holes (62) are evenly arranged along the circumference of the annular groove (63).

10. The baffle connection structure according to claim 2, characterized in that, The baffle (3) has a pull-out ring (34) protruding from the side away from the turbine disk (6).

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