Gas turbine and gas turbine engine

Abstract

The present application relates to the technical field of aero-engine, and discloses a gas turbine and a gas turbine engine, the gas turbine comprises a turbine disc, a turbine shaft assembly, a drum shaft, a back-shaped assembly and a fastening assembly, the turbine shaft assembly is in transmission connection with the turbine disc, and a first air hole is formed in the turbine shaft assembly; the drum shaft is in transmission connection with the turbine disc, and a second air hole is formed in the drum shaft; the first end of the back-shaped assembly is connected with the drum shaft, the second end of the back-shaped assembly is connected with the turbine shaft assembly, a first air flow path is formed between the back-shaped assembly and the turbine disc, the first air flow path is in communication with the first air hole and the second air hole respectively; and the fastening assembly penetrates through the back-shaped assembly, the drum shaft, the turbine disc and the turbine shaft assembly in sequence to connect the back-shaped assembly, the drum shaft, the turbine disc and the turbine shaft assembly. The present application realizes overall fastening constraint through the fastening assembly, improves the overall structural rigidity of the device, effectively resists high-speed centrifugal load, and avoids loosening and displacement of each connecting part.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, specifically to gas turbines and gas turbine engines. Background Technology

[0002] Aero engines operate under harsh conditions of high temperature, high pressure, and high speed. In gas turbine engines, the turbine blades directly bear the impact of the combustion chamber exhaust gas. Due to heat conduction from the turbine blades, the temperature at the rim of the turbine disk, where the blades are mounted, is relatively high, around 500-600℃. Meanwhile, a cooling gas stream is typically designed at the center of the turbine disk to lower the operating temperature of the turbine shaft, resulting in a temperature of around 300℃ at the center. Therefore, the temperature difference between the turbine disk rim and the center is approximately 300℃. This excessive temperature gradient leads to excessive thermal stress, reducing the strength and service life of the turbine disk and affecting its normal operation.

[0003] In existing technologies, to reduce the temperature gradient between different parts of the turbine disk, a temperature-equalizing spacer is installed at the center of the turbine disk to separate the air system flow paths between the high-pressure and low-pressure rotors, thus placing the high-pressure and low-pressure rotors in different fluid environments. However, the spacer is sealed at both ends to the compressor rear journal and bolted to the turbine disk and turbine rear journal, respectively. Each connection node is independent and lacks overall constraint, resulting in insufficient overall structural rigidity of the device. Furthermore, under the centrifugal load generated at high speeds, the connection points are prone to loosening and displacement, compromising the sealing effect. Summary of the Invention

[0004] This invention provides a gas turbine and a gas turbine engine to solve the problem of insufficient overall structural rigidity and easy loosening of the turbine disk heat insulation structure.

[0005] In a first aspect, the present invention provides a gas turbine, comprising a turbine disk, a turbine shaft assembly, a drum shaft, a loop assembly, and a fastening assembly. The turbine shaft assembly is drivenly connected to the turbine disk, and a first vent hole is provided on the turbine shaft assembly. The drum shaft is drivenly connected to the turbine disk, and a second vent hole is provided on the drum shaft. A first end of the loop assembly is connected to the drum shaft, and a second end of the loop assembly is connected to the turbine shaft assembly. The loop assembly is disposed on the outside of the turbine disk and spaced apart from the turbine disk. A first airflow path is formed between the loop assembly and the turbine disk. The first airflow path communicates with the first vent hole and the second vent hole respectively. The first vent hole is adapted to communicate with the cooling flow path of a high-pressure compressor or the cooling flow path outside the combustion chamber flame tube. The fastening assembly sequentially passes through the loop assembly, the drum shaft, the turbine disk, and the turbine shaft assembly to connect the loop assembly, the drum shaft, the turbine disk, and the turbine shaft assembly.

[0006] Beneficial effects: By sequentially passing through the loop assembly, drum shaft, turbine disk and turbine shaft assembly with fastening components, the overall fastening constraint is achieved, which improves the overall structural rigidity of the device, effectively resists high-speed centrifugal loads, and avoids loosening and displacement of various connection parts; by using the first air passage between the loop assembly and the turbine disk, the turbine disk is surrounded, and the disk center of the turbine disk is isolated from the turbine shaft, which effectively reduces the temperature gradient of the turbine disk.

[0007] In one optional embodiment, the loop assembly includes a first loop structure and a second loop structure, the first loop structure is connected to the second loop structure, the first loop structure is connected to the drum shaft, the second loop structure is connected to the turbine shaft assembly, and the fastening assembly is disposed through the first loop structure.

[0008] Beneficial effects: The interconnected first and second loop structures form a loop assembly, eliminating the need for additional flange connections, simplifying the assembly process, facilitating the positioning and installation of each component, and ensuring the coverage of the turbine disk.

[0009] In one optional embodiment, the turbine shaft assembly includes a turbine shaft and a turbine short shaft, the turbine short shaft being connected to the turbine shaft and the turbine short shaft being connected to the second loop structure, the turbine shaft being spaced apart from the first loop structure to form a second air passage, the turbine short shaft having a third vent hole, the second air passage communicating with the third vent hole, and the fastening assembly passing through the turbine short shaft.

[0010] Beneficial effects: By setting up a second airflow path, the airflow can act on the outer side of the turbine disk and the periphery of the turbine shaft at the same time, achieving all-round heat insulation of the turbine disk and turbine shaft, and improving the overall thermal protection performance of the device.

[0011] In one optional embodiment, a third air passage is provided inside the turbine shaft, and the third air passage is arranged along the axial direction of the turbine shaft.

[0012] Beneficial effects: By setting up a third airflow path, the operating temperature of the turbine shaft is reduced, and the overall thermal protection performance of the device is improved.

[0013] In one alternative embodiment, the fastening assembly includes a bolt and a nut, the bolt passing sequentially through the loop assembly, the drum shaft, the turbine disk, and the turbine shaft assembly, and the nut being disposed at the end of the turbine shaft assembly away from the drum shaft and threadedly connected to the bolt.

[0014] Beneficial effects: The threaded connection of bolts and nuts is simple and reliable, and can achieve axial tight locking of the spiral assembly, drum shaft, turbine disk and turbine shaft assembly, ensuring no relative displacement gap between the components; the design of bolts passing through all core components in sequence allows the fastening force to be evenly transmitted to each connection point along the axial direction, forming an integral force system, which improves the structure's ability to resist centrifugal loads and effectively prevents the connection points from loosening under high speed conditions; at the same time, the threaded connection facilitates disassembly and maintenance, reducing the maintenance cost of the device.

[0015] In one alternative embodiment, the fastening assembly further includes a retaining washer fitted onto the bolt and positioned between the turbine shaft assembly and the nut.

[0016] Beneficial effects: The locking washer is fitted onto the bolt and located between the turbine shaft assembly and the nut. Utilizing the locking washer's anti-loosening properties, it effectively suppresses the risk of thread loosening caused by high-speed centrifugal vibration and temperature cycling, further enhancing the locking reliability of the fastening assembly and ensuring the stability of the connection.

[0017] Secondly, the present invention also provides a gas turbine engine, including the gas turbine described above. Attached Figure Description

[0018] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific 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 from these drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of the overall structure of the gas turbine according to an embodiment of the present invention; Figure 2 This is a schematic diagram of the airflow path of a gas turbine according to an embodiment of the present invention.

[0020] Explanation of reference numerals in the attached figures: 10. Turbine disk; 20. Turbine shaft assembly; 21. Turbine shaft; 22. Turbine short shaft; 221. Third vent; 30. Drum shaft; 40. Loop assembly; 41. First loop structure; 42. Second loop structure; 50. Fastening assembly; 51. Bolt; 52. Nut; 53. Locking washer; 61. First air passage; 62. Second air passage; 63. Third air passage. Detailed Implementation

[0021] 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.

[0022] The following is combined Figures 1 to 2 The following describes embodiments of the present invention.

[0023] According to an embodiment of the present invention, in a first aspect, a gas turbine is provided, comprising a turbine disk 10, a turbine shaft assembly 20, a drum shaft 30, a loop assembly 40, and a fastening assembly 50. The turbine shaft assembly 20 is drivenly connected to the turbine disk 10, and a first vent hole is provided on the turbine shaft assembly 20. The drum shaft 30 is drivenly connected to the turbine disk 10, and a second vent hole is provided on the drum shaft 30. A first end of the loop assembly 40 is connected to the drum shaft 30, and a second end of the loop assembly 40 is connected to the turbine shaft assembly 20. The 40 is disposed on the outside of the turbine disk 10 and spaced apart from the turbine disk 10. The 40 is connected to the turbine disk 10 to form a first air passage 61. The first air passage 61 is connected to a first vent and a second vent. The first vent is adapted to be connected to the cooling passage of the high-pressure compressor or the cooling passage outside the combustion chamber flame tube. The fastening assembly 50 passes through the 40, the drum shaft 30, the turbine disk 10 and the turbine shaft assembly 20 in sequence to connect the 40, the drum shaft 30, the turbine disk 10 and the turbine shaft assembly 20.

[0024] It should be noted that in the relevant technologies, the two ends of the spacer are respectively sealed to the compressor rear journal and bolted to the turbine disk and turbine rear journal. Each connection node is independent and lacks overall constraint, resulting in insufficient overall structural rigidity of the device. Furthermore, under the centrifugal load generated at high speeds, the connection parts are prone to loosening and displacement, compromising the sealing effect. In addition, the axial space of turboshaft engines is compact, and the heat insulation layer structure in the relevant technologies is formed by two parts with an assembly relationship: the front short shaft and the grate. To meet the compact space requirements, the design requirements for the axial space of each component are stringent.

[0025] The gas turbine of this embodiment uses a fastening assembly 50 that sequentially passes through the loop assembly 40, the drum shaft 30, the turbine disk 10, and the turbine shaft assembly 20 to achieve overall fastening and constraint, improve the overall structural rigidity of the device, effectively resist high-speed centrifugal loads, and prevent loosening or displacement of various connection parts. The first air passage 61 between the loop assembly 40 and the turbine disk 10 surrounds the turbine disk 10, isolates the disk center of the turbine disk 10 from the turbine shaft 21, and heats the disk center of the turbine disk 10, effectively reducing the temperature gradient of the turbine disk 10. Furthermore, the fastening assembly 50 connects the turbine disk 10 to other components, reducing the number of axial connection points between components, thereby reducing the axial space occupied by the connection nodes and relaxing the design requirements for other components in the axial space.

[0026] Specifically, the first vent is connected to the cooling flow path of the high-pressure compressor. The gas in the cooling flow path exchanges heat with the high-pressure compressor and its temperature rises, thereby using the heated gas to heat the core of the turbine disk 10.

[0027] Specifically, such as Figure 2 As shown, Figure 2 The solid arrow in the figure indicates the gas flow direction of the first air passage 61. The gas from the high-pressure compressor enters the first air passage 61 through the second vent hole (not shown in the figure) of the drum shaft 30, heats the center of the turbine disk 10 through the first air passage 61, and then exits through the first vent hole on the turbine shaft assembly 20.

[0028] It should be noted that, as Figure 2 As shown, the first airflow path 61 is approximately a "U"-shaped flow path. The U-shaped component 40 achieves overall coverage and heating of the turbine disk 10's center, isolates the center of the turbine disk 10 from the turbine shaft 21, and effectively reduces the temperature gradient of the turbine disk 10.

[0029] Of course, in other alternative embodiments, the gas in the first gas passage 61 may also be derived from bleed air outside the combustion chamber.

[0030] In one embodiment, such as Figure 1 As shown, the loop assembly 40 includes a first loop structure 41 and a second loop structure 42. The first loop structure 41 is connected to the second loop structure 42. The first loop structure 41 is connected to the drum shaft 30. The second loop structure 42 is connected to the turbine shaft assembly 20. The fastening assembly 50 is disposed through the first loop structure 41.

[0031] Specifically, the first loop structure 41 is mounted on the turbine disk 10 by fastening assembly 50, and the second loop structure 42 is fixed to the turbine shaft assembly 20 by welding.

[0032] It is worth noting that the loop assembly 40 is formed by the interconnected first loop structure 41 and second loop structure 42, eliminating the need for additional flange connections, simplifying the assembly process, facilitating the positioning and installation of each component, and ensuring the coverage of the turbine disk 10.

[0033] In one embodiment, such as Figure 1 As shown, the turbine shaft assembly 20 includes a turbine shaft 21 and a turbine short shaft 22. The turbine short shaft 22 is connected to the turbine shaft 21 and is also connected to the second loop structure 42. Figure 2 As shown, the turbine shaft 21 is spaced apart from the first loop structure 41 to form a second air passage 62. A third air passage 221 is provided on the turbine short shaft 22. The second air passage 62 is connected to the third air passage 221. The fastening assembly 50 is installed through the turbine short shaft 22.

[0034] Specifically, the turbine short shaft 22 is connected to the second loop structure 42 by welding.

[0035] Specifically, such as Figure 2 As shown, Figure 2 The hollow arrow in the middle indicates the gas flow direction of the second air passage 62. The gas enters the second air passage 62 through the third vent 221 on the turbine short shaft 22, and flows outward from the first loop structure 41 away from the outer wall of the turbine disk 10 to seal the loop assembly 40.

[0036] It is worth noting that by setting a second air passage 62, the gas can act on the outer side of the turbine disk 10 and the periphery of the turbine shaft 21 at the same time, thereby sealing the loop assembly 40 and improving the overall thermal protection performance of the device.

[0037] In one embodiment, such as Figure 2 As shown, a third air passage 63 is provided inside the turbine shaft 21, and the third air passage 63 is arranged along the axial direction of the turbine shaft 21.

[0038] Specifically, the gas in the third airflow path 63 is cold air, such as... Figure 2 As shown, Figure 2 The direction of gas flow in the third air passage 63 is indicated by a forked arrow.

[0039] It is worth noting that by setting a third airflow path 63, the operating temperature of the turbine shaft 21 is reduced, thereby improving the overall thermal protection performance of the device.

[0040] In one embodiment, such as Figure 1As shown, the fastening assembly 50 includes a bolt 51 and a nut 52. The bolt 51 passes through the loop assembly 40, the drum shaft 30, the turbine disk 10 and the turbine shaft assembly 20 in sequence. The nut 52 is located at the end of the turbine shaft assembly 20 away from the drum shaft 30 and is threadedly connected to the bolt 51.

[0041] It is worth noting that the threaded connection of bolt 51 and nut 52 is simple and reliable, enabling axial tight locking of the spiral assembly 40, drum shaft 30, turbine disk 10 and turbine shaft assembly 20, ensuring no relative displacement gap between the components; the design of bolt 51 passing through all core components in sequence allows the fastening force to be evenly transmitted to each connection point along the axial direction, forming an overall force system, improving the structure's ability to resist centrifugal loads, and effectively preventing loosening of the connection points under high-speed conditions; at the same time, the threaded connection facilitates disassembly and maintenance, reducing the maintenance cost of the device.

[0042] In one embodiment, such as Figure 1 As shown, the fastening assembly 50 also includes a retaining washer 53, which is fitted onto the bolt 51 and positioned between the turbine shaft assembly 20 and the nut 52.

[0043] It is worth noting that the locking washer 53 is fitted onto the bolt 51 and located between the turbine shaft assembly 20 and the nut 52. By utilizing the anti-loosening properties of the locking washer 53, the risk of thread loosening caused by high-speed centrifugal vibration and temperature cycle changes is effectively suppressed, further enhancing the locking reliability of the fastening assembly 50 and ensuring the stability of the connection.

[0044] The gas turbine of this embodiment cools the turbine shaft 21 with cold air through the third air passage 63, while warm gas through the first air passage 61 heats the center of the turbine disk 10 to prevent a large temperature difference in the radial direction of the turbine disk 10. Furthermore, the gas through the second air passage 62 isolates the temperature transfer between the outer side of the turbine disk 10 and the periphery of the turbine shaft 21, thereby sealing the spiral assembly 40 and reducing the temperature impact of the low-temperature turbine shaft 21 on the center of the turbine disk 10.

[0045] According to an embodiment of the present invention, in a second aspect, a gas turbine engine is also provided, including the gas turbine described above.

[0046] Although embodiments of the invention 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 invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A gas turbine, characterized in that, include: Turbine disk (10); Turbine shaft assembly (20), which is connected to the turbine disk (10) in a transmission manner, and a first vent hole is provided on the turbine shaft assembly (20); A drum shaft (30) is connected to the turbine disk (10) in a transmission manner, and a second vent hole is provided on the drum shaft (30); A loop assembly (40) is provided, the first end of which is connected to the drum shaft (30), and the second end of which is connected to the turbine shaft assembly (20). The loop assembly (40) is disposed on the outside of the turbine disk (10) and spaced apart from the turbine disk (10). A first air passage (61) is formed between the loop assembly (40) and the turbine disk (10). The first air passage (61) is connected to the first vent and the second vent respectively. The first vent is adapted to be connected to the cooling flow path of the high-pressure compressor or the cooling flow path outside the combustion chamber flame tube. Fastening assembly (50) passes sequentially through the loop assembly (40), the drum shaft (30), the turbine disk (10) and the turbine shaft assembly (20) to connect the loop assembly (40), the drum shaft (30), the turbine disk (10) and the turbine shaft assembly (20).

2. The gas turbine according to claim 1, characterized in that, The loop assembly (40) includes a first loop structure (41) and a second loop structure (42). The first loop structure (41) is connected to the second loop structure (42). The first loop structure (41) is connected to the drum shaft (30). The second loop structure (42) is connected to the turbine shaft assembly (20). The fastening assembly (50) is disposed through the first loop structure (41).

3. The gas turbine according to claim 2, characterized in that, The turbine shaft assembly (20) includes a turbine shaft (21) and a turbine short shaft (22). The turbine short shaft (22) is connected to the turbine shaft (21) and is connected to the second loop structure (42). The turbine shaft (21) and the first loop structure (41) are spaced apart to form a second air passage (62). A third air hole (221) is provided on the turbine short shaft (22). The second air passage (62) communicates with the third air hole (221). The fastening assembly (50) is provided through the turbine short shaft (22).

4. The gas turbine according to claim 3, characterized in that, A third air passage (63) is provided inside the turbine shaft (21), and the third air passage (63) is arranged along the axial direction of the turbine shaft (21).

5. The gas turbine according to any one of claims 1-4, characterized in that, The fastening assembly (50) includes a bolt (51) and a nut (52). The bolt (51) passes through the loop assembly (40), the drum shaft (30), the turbine disk (10) and the turbine shaft assembly (20) in sequence. The nut (52) is located at one end of the turbine shaft assembly (20) away from the drum shaft (30) and is threadedly connected to the bolt (51).

6. The gas turbine according to claim 5, characterized in that, The fastening assembly (50) also includes a retaining washer (53), which is fitted onto the bolt (51) and positioned between the turbine shaft assembly (20) and the nut (52).

7. A gas turbine engine, characterized in that, Includes the gas turbine as described in any one of claims 1-6.

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