Thermal shock resistant gas turbine exhaust passage protection structure

Abstract

This invention belongs to the field of protective structure technology and discloses a thermal shock resistant protective structure for a gas turbine exhaust passage, including a protective half-shell A and a protective half-shell B. Both protective half-shells A and B are equipped with a fixing mechanism, a shock-absorbing structure, and a heat dissipation structure. Both protective half-shells A and B have heat dissipation grooves, and the heat dissipation structure is installed inside the heat dissipation grooves. The fixing mechanism includes a telescopic cylinder installed inside the protective half-shell A, a telescopic rod connected to the top of the telescopic cylinder, guide cylinders fixed to both sides of the telescopic cylinder, a guide rod connected inside the guide cylinders, a connecting plate fixed to the top of the telescopic rod, and a retaining plate fixed to the surface of the connecting plate. The fixing mechanism reliably connects the protective structure to the gas turbine body, achieving precise positioning and firm fixation of the protective structure to the exhaust passage and the gas turbine body, effectively avoiding installation offset and misalignment problems caused by insecure fixing in existing exhaust passages.

Description

Technical Field

[0001] This invention belongs to the field of protective structure technology, specifically relating to a thermal shock resistant protective structure for the exhaust passage of a gas turbine. Background Technology

[0002] Gas turbines, as highly efficient power machines, are widely used in many important fields such as power generation, aerospace, marine propulsion, and industrial drives. Their operational stability, safety, and service life directly affect the reliable operation and efficiency of the entire power system. The exhaust passage, as one of the core components of a gas turbine, is mainly used to guide the high-temperature, high-pressure exhaust generated by the gas turbine after it has performed work to the atmosphere, chimney, or waste heat boiler. It is an indispensable key component of the gas turbine exhaust system, and its working condition directly affects the overall operating performance and safety of the gas turbine. During actual operation of a gas turbine, the exhaust passage must withstand a harsh working environment for a long time and face multiple complex operating conditions: On the one hand, the exhaust gas temperature of the gas turbine is extremely high, usually exceeding 600 degrees Celsius. The high temperature environment can cause problems such as thermal expansion and thermal stress concentration in the exhaust passage body. If heat dissipation is not timely and effective, it will cause degradation, deformation, or even cracking of the passage material, seriously affecting the structural integrity and service life of the exhaust passage. On the other hand, the gas turbine generates continuous vibration during operation, which is transmitted to the exhaust passage through the machine body. Long-term vibration can cause loosening and wear between the exhaust passage and connecting parts, and even lead to safety hazards such as exhaust leakage and passage breakage. At the same time, vibration can also exacerbate noise pollution, affecting surrounding equipment and the environment. Furthermore, the exhaust passage requires reliable fixing during installation and operation to ensure precise alignment with the gas turbine body, subsequent exhaust pipelines, or waste heat recovery equipment. This prevents obstructed exhaust flow and excessively high local pressure caused by installation deviations or insecure fixing, which could negatively impact the gas turbine's exhaust efficiency and overall power performance. Simultaneously, the exhaust passage is constantly exposed to the complex industrial environment, making it susceptible to erosion from external dust and corrosive media, further accelerating wear and shortening its service life. However, current gas turbine exhaust channels generally lack a dedicated integrated protective structure, failing to achieve coordinated protection of vibration reduction, heat dissipation, and fixation functions. While some related technologies involve local optimization of the exhaust system, such as using bellows structures for displacement compensation or installing simple silencing or heat insulation components, these solutions all have significant limitations: bellows structures have limited buffering capacity and are prone to fatigue cracks, deformation, or even breakage under long-term high-temperature and high-pressure exhaust impacts, and cannot simultaneously meet the requirements for heat dissipation and fixation; simple heat insulation or silencing components can only solve a single problem and lack comprehensive protective design for vibration reduction, heat dissipation, and fixation, making them unable to cope with the complex operating conditions faced by the exhaust channel. Due to the lack of effective protective structures, exhaust channels are prone to a series of problems during long-term operation: high temperatures cannot dissipate in time, leading to accelerated aging of channel materials; vibration-induced loosening and wear reduce the reliability of channel connections; and loose fixing causes exhaust channel misalignment and displacement, resulting in exhaust leakage and increased exhaust resistance. This not only affects the operating efficiency and energy consumption of the gas turbine but also shortens the service life of the exhaust channel, increases equipment maintenance costs and downtime for repairs, and in severe cases, can even lead to safety accidents, causing huge economic losses and safety hazards. It cannot meet the actual needs of efficient, stable, and long-term safe operation of gas turbines and also limits the further application and promotion of gas turbines in high-end fields. Therefore, it is necessary to design a thermal shock resistant gas turbine exhaust channel protection structure to solve the above problems. Summary of the Invention

[0003] The purpose of this invention is to provide a thermal shock resistant gas turbine exhaust channel protection structure to solve the problems mentioned in the background art.

[0004] To achieve the above objectives, the present invention provides the following technical solution: a thermal shock resistant gas turbine exhaust channel protection structure, comprising a protective half-shell A and a protective half-shell B, wherein a fixing mechanism, a shock-absorbing structure and a heat dissipation structure are installed on both the protective half-shell A and the protective half-shell B, and heat dissipation grooves are provided on both the protective half-shell A and the protective half-shell B, wherein the heat dissipation structure is installed inside the heat dissipation grooves. The fixing mechanism includes a telescopic cylinder installed inside the protective half-shell A, a telescopic rod connected to the top of the telescopic cylinder, guide cylinders fixed on both sides of the telescopic cylinder, a guide rod connected inside the guide cylinder, a connecting plate fixed to the top of the telescopic rod, and a retaining plate fixed to the surface of the connecting plate. The shock absorption structure includes a shock absorption cylinder installed inside the protective half-shell A, a shock absorption column slidably connected inside the shock absorption cylinder, a shock absorption spring sleeved on the shock absorption cylinder and the shock absorption column, an arc-shaped plate fixed to the end of the shock absorption column, and a shock absorption plate fixed to the surface of the arc-shaped plate. The heat dissipation structure includes a nickel-based alloy block fixed inside the heat dissipation groove, a fixing frame fixed to the bottom of the nickel-based alloy block, a fluororubber clamp fixed inside the fixing frame, and a thermally conductive silicone grease cylinder clipped to the inside of the fluororubber clamp.

[0005] Preferably, the inner side of the protective half-shell A is provided with a cylinder receiving cavity, the inner side wall of the cylinder receiving cavity is fixed with a fixed seat plate, the surface of the fixed seat plate is fixedly connected with a telescopic cylinder, and the telescopic cylinder, guide cylinder and guide rod are all installed inside the cylinder receiving cavity.

[0006] Preferably, the inner side of the shock-absorbing component housing is provided with a shock-absorbing component receiving cavity, and the shock-absorbing cylinder and shock-absorbing column are both installed inside the shock-absorbing component receiving cavity. One end of the shock-absorbing spring is connected to the inner wall of the shock-absorbing component receiving cavity, and the other end is connected to the surface of the arc-shaped plate.

[0007] Preferably, the damping plate includes a silicone rubber plate, a manganese copper alloy plate, and a composite damping plate. The silicone rubber plate, the manganese copper alloy plate, and the composite damping plate are bonded and fixed together. The manganese copper alloy plate is located in the middle position, and the composite damping plate is fixed to the surface of the arc-shaped plate.

[0008] Preferably, the outer end of the fluororubber clamp is obliquely cut, the outer end of the thermal grease cylinder is open, and the interior of the thermal grease cylinder is filled with thermal grease.

[0009] Preferably, the protective half-shell A is fixed with a fixing seat A at both ends, and the protective half-shell B is fixed with a fixing seat B at both ends corresponding to the fixing seat A. Fixing holes are provided on both the fixing seat A and the fixing seat B.

[0010] Preferably, the protective half-shell A has a channel for the extension and retraction of the anti-stabilizing plate and the shock-absorbing plate, and the fixing mechanism and the shock-absorbing structure are both welded to the surface of the protective half-shell A.

[0011] Preferably, the protective half-shell A and the protective half-shell B are fixed by bolts passing through fixing holes, the fixing seat A is integrally formed with the protective half-shell A, and the fixing seat B is integrally formed with the protective half-shell B.

[0012] Preferably, the guide rod is welded to the surface of the connecting plate, and the guide rod is cylindrical.

[0013] Preferably, the shock-absorbing column is welded to the surface of the arc-shaped plate, and the shock-absorbing column is cylindrical.

[0014] Compared with the prior art, the beneficial effects of the present invention are: 1. A fixing mechanism reliably connects the protective structure to the gas turbine body, achieving precise positioning and secure fixation of the protective structure to the exhaust passage and the gas turbine body. This effectively avoids installation misalignment and displacement problems caused by insecure fixing of existing exhaust passages. The fixing mechanism ensures stable connection between the protective structure and the gas turbine body, guaranteeing comprehensive coverage and precise protection of the exhaust passage. It also prevents positional shifts in the exhaust passage caused by vibration, high-temperature expansion, and other factors during long-term operation. This ensures the connection accuracy between the exhaust passage and the gas turbine body and subsequent pipelines, reduces exhaust flow resistance, improves the exhaust efficiency and overall power performance of the gas turbine, and reduces safety hazards such as exhaust leakage caused by fixing failure.

[0015] 2. The integrated vibration damping structure in the protective structure can specifically absorb the vibrations generated during gas turbine operation, effectively reducing the transmission of vibrations to the exhaust passage and solving problems such as loosening, wear, and breakage of connecting parts caused by long-term vibration in existing exhaust passages. The vibration damping structure can buffer the impact of vibration, reduce the vibration amplitude of the exhaust passage itself, reduce vibration-induced noise pollution, protect the structural integrity of the exhaust passage and connecting parts, avoid safety accidents such as exhaust leakage caused by vibration, extend the service life of the exhaust passage and protective structure, and reduce equipment maintenance costs and the frequency of downtime for maintenance.

[0016] 3. The integrated heat dissipation structure on the protective structure can quickly dissipate the heat generated by the exhaust channel under long-term exposure to high-temperature exhaust gases, effectively alleviating the problems of thermal expansion and thermal stress concentration in the exhaust channel, and solving the defects such as material performance degradation, deformation, and cracking caused by untimely heat dissipation in existing exhaust channels. The heat dissipation structure can accelerate the dissipation of heat from the surface of the exhaust channel, reduce the temperature of the channel body, avoid damage to the channel material from high temperatures, maintain the structural stability and mechanical properties of the exhaust channel, further extend the service life of the exhaust channel, and at the same time reduce the impact of high-temperature environment on surrounding equipment, thereby improving the operational safety of the entire gas turbine system. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the overall structure of the present invention; Figure 2 This is a schematic diagram of the orthographic section of the fixing mechanism of the present invention; Figure 3 This is a schematic cross-sectional view of the shock-absorbing structure of the present invention; Figure 4 This is a front sectional view of the heat dissipation structure of the present invention; Figure 5 This is a schematic diagram of the layered structure of the shock-absorbing plate of the present invention; In the diagram: 1. Protective half-shell A; 2. Protective half-shell B; 3. Fixing mechanism; 31. Support plate; 32. Fixed structure bearing shell; 33. Fixing base plate; 34. Telescopic cylinder; 35. Cylinder housing; 36. Guide cylinder; 37. Guide rod; 38. Connecting plate; 39. Telescopic rod; 4. Vibration damping structure; 41. Vibration damping component bearing shell; 42. Vibration damping cylinder; 43. Vibration damping plate; 431. Silicone rubber plate; 432. Manganese copper alloy plate; 433. Composite vibration damping plate; 44. Arc plate; 45. Vibration damping spring; 46. Vibration damping column; 47. Vibration damping component housing; 5. Heat dissipation structure; 51. Nickel-based alloy block; 52. Fixing frame; 53. Thermal grease cylinder; 54. Fluororubber clamp; 6. Fixing base A; 7. Fixing base B; 8. Fixing hole; 9. Heat dissipation groove. Detailed Implementation

[0018] 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, and 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.

[0019] Example: This invention provides a technical solution: such as Figure 1 As shown, the core structure includes a protective half-shell A1 and a protective half-shell B2. The protective half-shells A1 and B2 are symmetrical arc-shaped structures. The two ends of each are integrally formed with a fixing seat A6 and a fixing seat B7, respectively. Both fixing seats A6 and B7 are provided with coaxial fixing holes 8. The protective half-shells A1 and B2 are detachably fixed by bolts passing through the fixing holes 8. Together, they form a cylindrical protective structure that is adapted to the exhaust passage of the gas turbine. It can be flexibly disassembled and assembled according to the pipe diameter specifications of the exhaust passage.

[0020] The inner walls of the protective half-shell A1 and the protective half-shell B2 are evenly equipped with fixing mechanisms 3 and shock-absorbing structures 4, and the outer walls of both are provided with several heat dissipation grooves 9, in which heat dissipation structures 5 are fixedly installed. The wall of the protective half-shell A1 is provided with a through channel for the expansion and contraction of the abutment plate 31 of the fixing mechanism 3 and the shock-absorbing plate 43 of the shock-absorbing structure 4. The outer shells of the fixing mechanism 3 and the shock-absorbing structure 4 are fixedly connected to the inner walls of the protective half-shell A1 and the protective half-shell B2 by welding to ensure the connection strength and structural stability.

[0021] like Figure 2 As shown, the fixing mechanism 3 includes a fixed structure bearing shell 32, a cylinder receiving cavity 35, a fixed base plate 33, a telescopic cylinder 34, a guide cylinder 36, a guide rod 37, a connecting plate 38, a telescopic rod 39, and a retaining plate 31. The fixed structure bearing shell 32 is welded to the inner wall of the protective half shell A1, and a cylinder receiving cavity 35 is opened on its inner side. The fixed base plate 33 is welded to the inner wall of the cylinder receiving cavity 35. The telescopic cylinder 34 is fixed to the surface of the fixed base plate 33 by bolts, and the output end of the telescopic cylinder 34 is vertically connected to the telescopic rod. 39; Guide cylinders 36 are symmetrically welded on both sides of the telescopic cylinder 34. A cylindrical guide rod 37 is slidably connected inside the guide cylinder 36. The top of the guide rod 37 is welded to the lower surface of the connecting plate 38. The upper surface of the connecting plate 38 is welded and fixed to the abutment plate 31. The top of the telescopic rod 39 is also fixedly connected to the center position of the lower surface of the connecting plate 38. The cooperation between the guide cylinder 36 and the guide rod 37 can ensure that the telescopic rod 39 drives the abutment plate 31 to perform linear telescopic movement, and prevent the abutment plate 31 from deviating or getting stuck during the telescopic process.

[0022] like Figure 3As shown, the damping structure 4 includes a damping component bearing housing 41, a damping component receiving cavity 47, a damping cylinder 42, a damping plate 43, an arc-shaped plate 44, a damping spring 45, and a damping column 46. The damping component bearing housing 41 is welded to the inner wall of the protective half-shell A1, and the damping component receiving cavity 47 is opened on its inner side. The damping cylinder 42 is welded to the inner wall of the damping component receiving cavity 47. A cylindrical damping column 46 is slidably connected inside the damping cylinder 42. The outer end of the damping column 46 is welded and fixed to the inner side of the arc-shaped plate 44. The damping plate 43 is bonded to the outer side of the arc-shaped plate 44. The damping spring 45 is sleeved on the outer side of the damping cylinder 42 and the damping column 46. One end of the spring abuts against the inner wall of the damping component receiving cavity 47, and the other end abuts against the inner side of the arc-shaped plate 44. The damping spring 45 is always in a slightly compressed state, which can ensure that the damping plate 43 is always in contact with the outer wall of the exhaust channel.

[0023] like Figure 5 As shown, the damping plate 43 has a three-layer composite structure, consisting of a composite damping plate 433, a manganese-copper alloy plate 432, and a silicone rubber plate 431 from the inside out. The three layers are bonded and fixed together with a high-temperature resistant adhesive. The composite damping plate 433 is bonded to the outer surface of the arc plate 44. The silicone rubber plate 431 is in direct contact with the outer wall of the exhaust channel and has the characteristics of high temperature resistance, anti-slip, and cushioning. The manganese-copper alloy plate 432 can effectively absorb vibration energy. The composite damping plate 433 enhances the overall structural strength of the damping plate 43. The three-layer structure works together to achieve efficient damping.

[0024] like Figure 4 As shown, the heat dissipation structure 5 includes a nickel-based alloy block 51, a fixing frame 52, a thermally conductive silicone grease cylinder 53, and a fluororubber clamp 54. The nickel-based alloy block 51 is a high-temperature resistant and high-thermal-conductivity structure, which is embedded and fixed inside the heat dissipation groove 9. A fixing frame 52 is welded to its bottom. Fluororubber clamps 54 are symmetrically fixed on the inner side of the fixing frame 52. The outer end of the fluororubber clamp 54 is beveled to facilitate the snapping and disassembly of the thermally conductive silicone grease cylinder 53. The thermally conductive silicone grease cylinder 53 is snapped onto the inner side of the fluororubber clamp 54. The outer end of the thermally conductive silicone grease cylinder 53 is an open structure. Its interior is filled with highly thermally conductive silicone grease, and the open end of the thermally conductive silicone grease cylinder 53 is in contact with the outer wall of the exhaust channel to ensure heat transfer efficiency.

[0025] The telescopic cylinder 34 can be a high-temperature resistant pneumatic cylinder, suitable for the high-temperature working environment of the gas turbine exhaust channel; the nickel-based alloy block 51 is made of GH3030 nickel-based alloy, which has excellent high-temperature resistance and thermal conductivity; the fluororubber clamp 54 is made of fluororubber, which is resistant to high temperature and corrosion and has good elasticity, which can ensure the stability of the thermal grease sleeve 53 and facilitate the replacement of the thermal grease sleeve 53 and the replenishment of thermal grease in the future.

[0026] Operating Procedure and Working Principle: Protective half-shell A1 and protective half-shell B2 are connected by bolts passing through fixing holes 8. Then, the exhaust pipe is placed between protective half-shell A1 and protective half-shell B2. The telescopic cylinder 34 at one end is controlled to drive the telescopic rod 39 to move until the abutment plate 31 abuts against the gas turbine. Then, the telescopic cylinder 34 at the other end is controlled to drive the telescopic rod 39 to move until the abutment plate 31 abuts against the exhaust pipe, thus completing the reinforced connection between the exhaust pipe and the gas turbine. After clamping the exhaust pipe, the shock-absorbing spring 45 presses against the arc plate 44 and the shock-absorbing plate 43 to press the exhaust pipe. At this time, the shock-absorbing plate 43 plays the first role of shock absorption. Then, the shock-absorbing spring 45 contracts to absorb the vibration and plays the second role of shock absorption. The thermal grease cylinder 53 will press against the outer surface of the exhaust pipe. The heat of the exhaust pipe is transferred to the nickel-based alloy block 51 through the thermal grease cylinder 53 and then dissipated to the outside by the nickel-based alloy block 51.

[0027] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0028] The above description is only used to illustrate the technical solution of the present invention and is not intended to limit it. Any other modifications or equivalent substitutions made by those skilled in the art to the technical solution of the present invention, as long as they do not depart from the spirit and scope of the technical solution of the present invention, should be covered within the scope of the claims of the present invention.

Claims

1. A hot gas path protection structure for a gas turbine, comprising a protection half-shell A (1) and a protection half-shell B (2), characterized in that: The protective half-shell A (1) and the protective half-shell B (2) are each equipped with a fixing mechanism (3), a shock absorption structure (4) and a heat dissipation structure (5). The protective half-shell A (1) and the protective half-shell B (2) are each provided with a heat dissipation groove (9). The heat dissipation structure (5) is installed inside the heat dissipation groove (9). The fixing mechanism (3) includes a telescopic cylinder (34) installed inside the protective half shell A (1), a telescopic rod (39) connected to the top of the telescopic cylinder (34), a guide cylinder (36) fixed on both sides of the telescopic cylinder (34), a guide rod (37) connected inside the guide cylinder (36), a connecting plate (38) fixed to the top of the telescopic rod (39), and a retaining plate (31) fixed to the surface of the connecting plate (38). The shock-absorbing structure (4) includes a shock-absorbing cylinder (42) installed inside the protective half shell A (1), a shock-absorbing column (46) slidably connected inside the shock-absorbing cylinder (42), a shock-absorbing spring (45) sleeved on the shock-absorbing cylinder (42) and the shock-absorbing column (46), an arc plate (44) fixed to the end of the shock-absorbing column (46), and a shock-absorbing patch (43) fixed to the surface of the arc plate (44). The heat dissipation structure (5) includes a nickel-based alloy block (51) fixed inside the heat dissipation groove (9), a fixing frame (52) fixed at the bottom of the nickel-based alloy block (51), a fluororubber clamp (54) fixed inside the fixing frame (52), and a thermally conductive silicone grease cylinder (53) snapped into the inside of the fluororubber clamp (54).

2. A thermal shock resistant gas turbine exhaust passage protection structure according to claim 1, characterized by: The inner side of the protective half shell A (1) is provided with a cylinder receiving cavity (35). The inner side wall of the cylinder receiving cavity (35) is fixed with a fixed seat plate (33). The surface of the fixed seat plate (33) is fixedly connected to a telescopic cylinder (34). The telescopic cylinder (34), the guide cylinder (36) and the guide rod (37) are all installed inside the cylinder receiving cavity (35).

3. A thermal shock resistant gas turbine exhaust passage protection structure according to claim 1, characterized by: The inner side of the shock-absorbing component housing (41) is provided with a shock-absorbing component receiving cavity (47). The shock-absorbing cylinder (42) and the shock-absorbing column (46) are both installed inside the shock-absorbing component receiving cavity (47). One end of the shock-absorbing spring (45) is connected to the inner wall of the shock-absorbing component receiving cavity (47), and the other end is connected to the surface of the arc plate (44).

4. A thermal shock resistant gas turbine exhaust passage protection structure according to claim 3, characterized by: The damping plate (43) includes a silicone rubber plate (431), a manganese copper alloy plate (432), and a composite damping plate (433). The silicone rubber plate (431), the manganese copper alloy plate (432), and the composite damping plate (433) are bonded and fixed together. The manganese copper alloy plate (432) is in the middle position, and the composite damping plate (433) is fixed on the surface of the arc plate (44).

5. The thermal shock resistant gas turbine exhaust channel protection structure according to claim 1, characterized in that: The outer end of the fluororubber clamp (54) is obliquely cut, the outer end of the thermal grease cylinder (53) is open, and the interior of the thermal grease cylinder (53) is filled with thermal grease.

6. The thermal shock resistant gas turbine exhaust channel protection structure according to claim 1, characterized in that: The protective half-shell A (1) is fixed with a fixing seat A (6) at both ends, and the protective half-shell B (2) is fixed with a fixing seat B (7) at both ends corresponding to the fixing seat A (6). Fixing holes (8) are provided on both the fixing seat A (6) and the fixing seat B (7).

7. The thermal shock resistant gas turbine exhaust channel protection structure according to claim 1, characterized in that: The protective half-shell A (1) has a channel for the extension and retraction of the anti-stabilizing plate (31) and the shock-absorbing plate (43). The fixing mechanism (3) and the shock-absorbing structure (4) are both welded to the surface of the protective half-shell A (1).

8. The thermal shock resistant gas turbine exhaust channel protection structure according to claim 6, characterized in that: The protective half-shell A (1) and the protective half-shell B (2) are fixed by bolts passing through the fixing hole (8). The fixing seat A (6) is integrally formed with the protective half-shell A (1), and the fixing seat B (7) is integrally formed with the protective half-shell B (2).

9. A thermal shock resistant gas turbine exhaust channel protection structure according to claim 1, characterized in that: The guide rod (37) is welded to the surface of the connecting plate (38), and the guide rod (37) is cylindrical.

10. A thermal shock resistant gas turbine exhaust channel protection structure according to claim 1, characterized in that: The shock-absorbing column (46) is welded to the surface of the arc plate (44), and the shock-absorbing column (46) is cylindrical.

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