Bottom frame front and back supporting structure of gas turbine
By using modular design and stress-dispersing structure, the problem of fracture caused by stress concentration in the gas turbine underframe was solved, resulting in a lightweight and stable support structure that is easy to maintain and extends service life.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2026-02-27
- Publication Date
- 2026-04-07
AI Technical Summary
The existing gas turbine underframe front and rear support structures are heavy, have uneven stress distribution leading to stress concentration, are prone to breakage, are difficult to repair and replace, have poor shock absorption performance, and have a short service life.
The modular design breaks down the entire board into adapters, strips, fixing plates, and convex bases, which are then fixed by locking nut assemblies. The strips are reinforced at stress concentration points, and through holes are designed to disperse stress, thus achieving the assembled structure.
It achieves uniform stress distribution on all components, reduces processing costs and difficulty, improves maintenance convenience, extends service life, facilitates parts replacement, reduces vibration, reduces weight, and enhances stability and shock absorption performance.
Smart Images
Figure CN121803341A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of gas turbine technology, and more specifically to a front and rear support structure for the underframe of a gas turbine. Background Technology
[0002] Existing gas turbine underframe supports typically use a single thick plate as the main body for the front and rear supports, connected to the entire underframe with bolts. While this structure can meet the support requirements of gas turbines to some extent, it has several shortcomings. For example, the weight of the single thick plate increases the overall weight of the gas turbine system, hindering flexible equipment layout and transportation. Moreover, under complex loads, the stress distribution is uneven, easily leading to localized stress concentration, causing fatigue cracks or even fractures in the support structure, affecting the safe and stable operation of the gas turbine. Furthermore, due to its relatively simple structure, its vibration damping performance is poor, making it difficult to effectively attenuate vibrations generated during gas turbine operation. This not only reduces the service life of the equipment but may also cause vibration pollution to the surrounding environment. Additionally, the uneven stress distribution caused by gas turbine vibrations during operation can lead to cracking at locations of high stress. The large, thick plate is costly and difficult to manufacture, and replacing a single plate when the front and rear supports are worn or damaged is a significant challenge.
[0003] In summary, the existing gas turbine chassis is an integrated steel structure support structure, which is large in size and prone to breakage after long-term use, resulting in a short service life. Summary of the Invention
[0004] This invention addresses the problem that existing gas turbine chassis are integral steel structures, which are bulky, prone to breakage after prolonged use, and have a short service life. It proposes a front and rear support structure for the gas turbine chassis.
[0005] The present invention provides a front and rear support structure for the underframe of a gas turbine, comprising a converter 1, a fixing plate 3, a convex base 4, and a locking nut assembly 5;
[0006] A fixing plate 3 is provided on each of the two top sides of the convex base 4, and the bottom of the two fixing plates 3 is fixedly connected to the upper part of the convex base 4 through the locking nut assembly 5. A connector 1 is provided between the tops of the two fixing plates 3, and the bottom of the connector 1 is fixedly connected to the two fixing plates 3 through the locking nut assembly 5.
[0007] Furthermore, each of the two fixing plates 3 has a strip 2 on its outer side face;
[0008] Furthermore, a through hole is machined at the center of the top end face of the convex base 4;
[0009] Furthermore, a fixing through hole is machined at each end of the bottom surface of the convex base 4;
[0010] Furthermore, n through holes are uniformly machined along the circumferential direction on the upper part of the end face of the adapter 1, where n is a positive integer;
[0011] Furthermore, the number of through holes n on the adapter 1 is 2≤n≤10;
[0012] Furthermore, in use, this invention modularizes the rear support of the base frame, disassembling one whole plate into an adapter 1, two strips 2, two fixing plates 3, and a convex base 4, which are then fixed by a locking nut assembly 5. This invention uses strips 2 to reinforce stress concentration points, and then uses the locking nut assembly 5 for fixation. Moreover, by reinforcing the fixing plates at stress concentration points with strips, the invention prevents the fixing plates from breaking, effectively extending their service life. This structure is an assembled structure and has a small size, making it easy to disassemble and replace any damaged parts after prolonged use.
[0013] Compared with the prior art, the present invention has the following advantages:
[0014] This invention overcomes the shortcomings of existing technologies by modularizing the rear support of the underframe. A single plate is disassembled into a connector, two strips, two fixing plates, and a convex base, all secured by a locking nut assembly. This modular design ensures more even stress distribution across components, preventing cracking caused by stress concentration. Furthermore, the assembly-type structure reduces processing costs and complexity while significantly improving maintenance convenience. When a component wears or is damaged, only the corresponding component needs replacement, rather than the entire support structure, thus extending the service life of the gas turbine underframe. In addition, the through-hole design on the convex base and fixing plates makes the entire structure lighter while ensuring sufficient strength and stability.
[0015] Furthermore, this invention uses slats to reinforce the stress concentration points and then uses a locking nut assembly for fixation. Reinforcing the fixing plate with slats at stress concentration points prevents breakage and effectively extends its service life. This structure is an assembly structure and is relatively small in size; if a part is damaged after prolonged use, it is easy to disassemble and replace. Attached Figure Description
[0016] Figure 1 This is a front view of the underframe and front and rear support structure of a gas turbine according to the present invention;
[0017] Figure 1 1. Transition connector, 2. Slat, 3. Fixing plate, 4. Convex base, and 5. Locking nut assembly. Detailed Implementation
[0018] Specific implementation method one: Combining Figure 1 This embodiment describes a gas turbine underframe front and rear support structure, which comprises an adapter 1, a fixing plate 3, a convex base 4, and a locking nut assembly 5.
[0019] A fixing plate 3 is provided on each of the two top sides of the convex base 4, and the bottom of the two fixing plates 3 is fixedly connected to the upper part of the convex base 4 through the locking nut assembly 5. A connector 1 is provided between the tops of the two fixing plates 3, and the bottom of the connector 1 is fixedly connected to the two fixing plates 3 through the locking nut assembly 5.
[0020] In this specific embodiment, the rear support of the base frame is modularized. One of the original plates is disassembled into an adapter 1, two strips 2, two fixing plates 3, and a convex base 4, which are then fixed by a locking nut assembly 5. This invention uses strips 2 to reinforce stress concentration points, and then uses the locking nut assembly 5 for fixation. Furthermore, by reinforcing the fixing plates at stress concentration points with strips, breakage of the fixing plates is prevented, effectively extending service life. This structure is an assembled structure and has a small size; if a part is damaged after prolonged use, it is easy to disassemble and replace.
[0021] Specific Implementation Method Two: Combining Figure 1 This embodiment further defines the support structure described in Specific Embodiment 1. In this embodiment, a gas turbine underframe front and rear support structure is provided, wherein the two fixed plates 3 are respectively provided with a strip 2 on their opposite outer end faces.
[0022] In practical use, these two slats 2 play a crucial reinforcing role. Because the gas turbine vibrates during operation, uneven stress distribution occurs, particularly at certain locations on the fixed plate 3, where stress concentration is more pronounced. The slats 2 are designed to provide additional support at these stress concentration points, thereby dispersing stress and preventing the fixed plate 3 from cracking due to excessive stress. Simultaneously, the slats 2 are tightly connected to the fixed plate 3 via the locking nut assembly 5, ensuring the structural stability and reliability. Furthermore, the design of the slats 2 also considers ease of processing and installation, making the manufacturing and maintenance of the entire support structure more convenient.
[0023] Specific implementation method three: Combining Figure 1 This embodiment further defines the support structure described in Specific Embodiment Two. In this embodiment, a front and rear support structure for the underframe of a gas turbine is provided, wherein a through hole is machined at the center of the top end face of the convex base 4.
[0024] The through-hole design serves multiple purposes. First, it provides additional weight reduction for the entire support structure, helping to lower the overall weight of the gas turbine and improve operating efficiency. Second, the through-hole facilitates installation and commissioning; for example, it allows for positioning or installation of other auxiliary components, enabling the two fixing plates 3 to be mounted on the through-hole on the top end face of the convex base 4 via the locking nut assembly 5. Furthermore, when needed, the through-hole can also serve as an inspection port, facilitating the inspection and maintenance of the two fixing plates 3. Simultaneously, the machining precision of the through-hole is strictly controlled to ensure it does not affect the strength and stability of the entire support structure.
[0025] Specific implementation method four: Combination Figure 1 This embodiment further defines the support structure described in Specific Embodiment 3. In this embodiment, a gas turbine underframe front and rear support structure is provided, wherein a fixed through hole is machined at each end of the bottom surface of the convex base 4.
[0026] In this specific embodiment, the convex base 4 employs two fixing through holes, primarily to facilitate the fixation of the entire support structure to the gas turbine's underframe. During installation, bolts or other fasteners can be used through these two fixing through holes to tightly connect the convex base 4 to the underframe, ensuring the stability of the support structure. Furthermore, the position and size of the fixing through holes have been carefully designed to accommodate different models and specifications of gas turbine underframes, improving the versatility and applicability of the support structure. In addition, high-precision machining is used for the fixing through holes to ensure the accuracy and reliability of their connection to the underframe.
[0027] Specific Implementation Method Five: Combining Figure 1 This embodiment further defines the support structure described in Specific Embodiment 4. In this embodiment, a gas turbine underframe front and rear support structure is provided, wherein the upper part of the end face of the adapter 1 is uniformly machined with n through holes along the circumferential direction, where n is a positive integer.
[0028] In this specific embodiment, the design of these through holes on the adapter 1 provides more connection possibilities for the entire support structure. In practical applications, these through holes can be used to install various auxiliary components or connect other equipment, thereby meeting the usage requirements under different working conditions. Simultaneously, since the through holes are evenly distributed along the circumference, it ensures that the adapter 1 is subjected to more uniform force, avoiding stress concentration. Furthermore, the number of through holes, n, can be adjusted according to specific needs, allowing the support structure to adapt to more types of gas turbines. During the manufacturing process, the precision of these through holes is also strictly controlled to ensure that they do not affect the overall strength and stability of the adapter 1, effectively improving the versatility of the structure.
[0029] Specific Implementation Method Six: Combination Figure 1 This embodiment further defines the support structure described in Specific Embodiment Five. In this embodiment, the number of through holes n on the adapter 1 is 2≤n≤10.
[0030] This specific embodiment explicitly limits the number of through holes on the adapter 1, specifically controlling the number of through holes n between 2 and 10. This design considers both the strength requirements of the adapter 1 and the versatility of its connection functions. Too few through holes may not meet the connection needs under certain complex operating conditions; while too many through holes may weaken the overall strength of the adapter 1 and affect its service life. Therefore, by reasonably controlling the range of the number of through holes n, the connection function can be maximized while ensuring the strength of the adapter 1. Simultaneously, this design also makes the support structure more flexible and adaptable, capable of adapting to different models and specifications of gas turbines, thus enhancing its market application value.
Claims
1. A front and rear support structure for the underframe of a gas turbine, characterized in that: It includes an adapter (1), a fixing plate (3), a convex base (4), and a locking nut assembly (5); A fixing plate (3) is provided on each side of the top of the convex base (4), and the bottom of the two fixing plates (3) is fixedly connected to the upper part of the convex base (4) through the locking nut assembly (5). A connector (1) is provided between the tops of the two fixing plates (3), and the bottom of the connector (1) is fixedly connected to the two fixing plates (3) through the locking nut assembly (5).
2. The underframe front and rear support structure of a gas turbine according to claim 1, characterized in that: Each of the two fixing plates (3) has a strip (2) on its outer side.
3. The underframe front and rear support structure of a gas turbine according to claim 2, characterized in that: A through hole is machined at the center of the top end face of the convex base (4).
4. The front and rear support structure of the gas turbine underframe according to claim 3, characterized in that: The bottom surface of the convex base (4) is machined with a fixed through hole at each end.
5. The underframe front and rear support structure of a gas turbine according to claim 4, characterized in that: The adapter (1) has n through holes uniformly machined along the circumferential direction on the upper part of its end face, where n is a positive integer.
6. The underframe front and rear support structure of a gas turbine according to claim 5, characterized in that: The number of through holes n on the adapter (1) is 2≤n≤10.