A turbine load frame uniform temperature structure for an aeroengine

Abstract

The application belongs to the field of aero-engine design and relates to a turbine load-bearing frame equal-temperature structure of an aero-engine, which comprises a load-bearing outer ring, a load-bearing inner ring and a support plate; a first equal-temperature structure is coaxially arranged on the outer ring surface of the load-bearing outer ring, and a second equal-temperature structure is coaxially arranged on the outer ring surface of the load-bearing inner ring; due to the block of the first equal-temperature structure, the heat exchange coefficient of the outer side of the load-bearing outer ring is greatly reduced, and the temperature of the load-bearing outer ring is increased; the heat of the main channel gas can be radiated to the load-bearing inner ring only after passing through the flow channel plate and the second equal-temperature structure, so that the comprehensive heat transfer thermal resistance is increased, and the temperature of the load-bearing inner ring is reduced; the temperature of the load-bearing outer ring is increased, and the temperature of the load-bearing inner ring is reduced, so that the temperature distribution of the frame is improved, the temperature difference between the inner end and the outer end of the support plate is greatly reduced, the strength problems such as cracks can be avoided at the connection positions of the support plate of the load-bearing frame and the inner and outer rings, and the engine failure risk is reduced.

Description

Technical Field

[0001] This application belongs to the field of aero-engine design, and specifically relates to a temperature homogenization structure for aero-engine turbine load-bearing frame. Background Technology

[0002] like Figure 1 As shown, in the existing technology, due to its cooling design, the outer ring of the turbine support frame is located in an environment with a low heat transfer temperature and a high heat transfer coefficient. The outer ring is subjected to low-temperature airflow, resulting in a relatively low wall temperature. However, the inner ring, being downstream of the cooling airflow, experiences increasingly higher heat transfer temperatures due to heat exchange between the airflow and the wall surface. This results in a lower heat transfer coefficient for the inner ring and a significantly lower cooling effect compared to the outer ring. Furthermore, the lower flow channel plate generates radiant heat flow to the inner ring, causing a significant increase in the wall temperature of the inner ring. For example, in a certain engine, the temperature difference between the outer and inner rings of the turbine support frame can reach over 300K. This large temperature difference generates significant thermal stress, leading to strength problems such as cracks at the joints of the support plates, thus affecting engine operating safety.

[0003] Therefore, how to reduce the temperature difference between the inner and outer rings of the load-bearing frame and reduce the internal thermal stress of the load-bearing frame is a problem that needs to be solved. Summary of the Invention

[0004] The purpose of this application is to provide a temperature equalization structure for the turbine support frame of an aero-engine, in order to solve the strength problems in the prior art, such as large temperature difference and large thermal stress between the inner and outer rings of the support frame, which leads to easy cracking at the connection of the support plate of the support frame and affects the safety of engine operation.

[0005] The technical solution of this application is: a temperature equalization structure for a turbine bearing frame of an aero-engine, including a bearing outer ring, a bearing inner ring, and a support plate. The support plate is connected between the bearing outer ring and the bearing inner ring. A first temperature equalization structure is coaxially provided on the outer ring surface of the bearing outer ring, and a second temperature equalization structure is coaxially provided on the outer ring surface of the bearing inner ring. The temperature of the low-temperature gas located outside the bearing outer ring can only be transferred to the bearing outer ring after passing through the first temperature equalization structure, and the heat of the main channel combustion gas located outside the bearing inner ring can only be transferred to the bearing inner ring after passing through the second temperature equalization structure.

[0006] Preferably, the first temperature equalization structure includes a first heat insulation ring and first fixing rings disposed on both sides of the first heat insulation ring. The first fixing rings are detachably and fixedly connected to the load-bearing outer ring. There is a gap between the first heat insulation ring and the load-bearing outer ring, and a closed first heat insulation cavity is formed between the first heat insulation ring and the load-bearing outer ring. The second temperature equalization structure includes a second heat insulation ring and second fixing rings disposed on both sides of the second heat insulation ring. The second fixing rings are detachably and fixedly connected to the load-bearing inner ring. There is a gap between the second heat insulation ring and the load-bearing inner ring, and a closed second heat insulation cavity is formed between the second heat insulation ring and the load-bearing inner ring.

[0007] Preferably, the first fixing ring is connected to the outer load-bearing ring and the second fixing ring is connected to the inner load-bearing ring by bolts.

[0008] Preferably, the first temperature equalization structure has a first through hole that communicates with the interior of the support plate; the second temperature equalization structure has a second through hole that surrounds the outer ring surface of the support plate.

[0009] This application includes a load-bearing outer ring, a load-bearing inner ring, and a support plate. A first temperature equalization structure is coaxially provided on the outer ring surface of the load-bearing outer ring, and a second temperature equalization structure is coaxially provided on the outer ring surface of the load-bearing inner ring. Due to the obstruction of the first temperature equalization structure, the heat transfer coefficient on the outer side of the load-bearing outer ring is significantly reduced, and the temperature of the load-bearing outer ring increases. The heat of the main channel combustion gas must pass through the flow channel plate and the second temperature equalization structure before it can be radiated to the load-bearing inner ring. The overall heat transfer resistance increases, and the temperature of the load-bearing inner ring decreases. The increase in the temperature of the load-bearing outer ring and the decrease in the temperature of the load-bearing inner ring, together with the support plate, improve the temperature distribution of the load-bearing frame. The temperature difference between the inner and outer ends of the support plate is significantly reduced, which can avoid strength problems such as cracks at the connection between the support plate and the inner and outer rings of the load-bearing frame, and reduce the risk of engine failure. Attached Figure Description

[0010] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0011] Figure 1 This is a schematic diagram of a load-bearing frame structure in the background art;

[0012] Figure 2 This is a schematic diagram of the overall load-bearing frame structure of this application;

[0013] Figure 3 This is a schematic diagram of the load-bearing frame structure that highlights the first and second through holes in this application.

[0014] Figure 4 This is a schematic diagram of the load-bearing frame structure that highlights the internal structure of the inner load-bearing ring in this application.

[0015] 1. Load-bearing outer ring; 2. Load-bearing inner ring; 3. Support plate; 4. Flow channel plate; 5. First temperature equalization structure; 6. Second temperature equalization structure; 7. First heat insulation ring; 8. First fixing ring; 9. Second heat insulation ring; 10. Second fixing ring; 11. First heat insulation cavity; 12. Second heat insulation cavity; 13. First through hole; 14. Second through hole. Detailed Implementation

[0016] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0017] A temperature homogenizing structure for the turbine support frame of an aero-engine, such as Figure 2 As shown, the structure includes an outer load-bearing ring 1, an inner load-bearing ring 2, and a support plate 3. Low-temperature gas for cooling flows along the outer side of the outer load-bearing ring 1 and simultaneously enters the support plate 3, flowing radially downwards. The cooling gas inevitably exchanges heat with the main channel combustion gas, causing the temperature of the low-temperature gas to gradually increase before finally flowing out from the inner side of the inner load-bearing ring 2. The main channel combustion gas flows between two flow channel plates 4 between the outer load-bearing ring 1 and the inner load-bearing ring 2. The main channel combustion gas has a higher temperature, and its heat is radiated to the outer load-bearing ring 1 and the inner load-bearing ring 2 through the upper and lower flow channel plates 4, respectively.

[0018] A first temperature equalization structure 5 is coaxially provided on the outer ring surface of the outer ring 1, and a second temperature equalization structure 6 is coaxially provided on the outer ring surface of the inner ring 2. The cooling effect of the low-temperature gas located outside the outer ring 1 is reduced due to the presence of the first temperature equalization structure 5. The heat of the main channel gas located outside the inner ring 2 can only be transferred to the inner ring 2 after passing through the second temperature equalization structure 6.

[0019] The heat from the low-temperature gas can only be transferred to the outer supporting ring 1 after passing through the first temperature equalization structure 5. Due to the obstruction of the first temperature equalization structure 5, the cooling effect of the low-temperature gas on the outer supporting ring 1 is greatly reduced. At the same time, the heat radiated to the outer supporting ring 1 by the main channel gas is not affected, thus the temperature of the outer supporting ring 1 increases. After passing through the flow channel plate 4, the temperature of the main channel gas needs to pass through the second temperature equalization structure 6 before it can be radiated to the inner supporting ring 2. The heat from the main channel gas on the inner supporting ring 2 is greatly reduced. At the same time, the cooling effect of the low-temperature gas flowing out from the inside of the support plate 3 is not affected, thus the temperature of the inner supporting ring 2 decreases.

[0020] The temperature of the outer load-bearing ring 1 increases while the temperature of the inner load-bearing ring 2 decreases. For the load-bearing frame, the combined effect of the two improves the temperature distribution of the frame. The temperature difference between the inner and outer ends of the support plate 3 is significantly reduced, which can avoid strength problems such as cracks at the connection between the support plate 3 and the inner and outer rings of the load-bearing frame, and reduce the risk of engine failure.

[0021] Preferably, the first temperature equalization structure 5 includes a first heat insulation ring 7 and a first fixing ring 8 disposed on both sides of the first heat insulation ring 7. The first fixing ring 8 is detachably and fixedly connected to the load-bearing outer ring 1. There is a gap between the first heat insulation ring 7 and the load-bearing outer ring 1, and a closed first heat insulation cavity 11 is formed between the first heat insulation ring 7 and the load-bearing outer ring 1. The second temperature equalization structure 6 includes a second heat insulation ring 9 and a second fixing ring 10 disposed on both sides of the second heat insulation ring 9. The second fixing ring 10 is detachably and fixedly connected to the load-bearing inner ring 2. There is a gap between the second heat insulation ring 9 and the load-bearing inner ring 2, and a closed second heat insulation cavity 12 is formed between the second heat insulation ring 9 and the load-bearing inner ring 2.

[0022] Both the first insulation cavity 11 and the second insulation cavity 12 are filled with air. Since air has a relatively high thermal resistance, it provides strong insulation. Thus, the first insulation cavity 11 effectively blocks the low-temperature air, changing the flow heat transfer characteristics on the outer surface of the outer ring 1 from forced convection to weak convection. According to theoretical calculations, this measure can reduce the heat transfer coefficient of the outer ring 1 by more than five times. Due to the reduced heat transfer coefficient, the cooling effect of the outer ring 1 is decreased, resulting in a significant increase in the outer ring wall temperature. The second insulation cavity 12 effectively blocks the temperature of the combustion gas in the main channel, preventing the heat flow from the flow channel plate 4 to the inner ring 2 from reaching it. In principle, the uniform temperature structure increases the overall heat transfer resistance, leading to a decrease in the heat flow from the main channel to the inner ring 2, and a significant reduction in the inner ring temperature.

[0023] Preferably, the first fixing ring 8 is connected to the outer load-bearing ring 1 and the second fixing ring 10 is connected to the inner load-bearing ring 2 by bolts, which facilitates installation, disassembly and maintenance.

[0024] like Figure 3 , Figure 4 As shown, preferably, the first temperature equalization structure 5 is provided with a first through hole 13, which is connected to the inside of the support plate 3. By providing the first through hole 13, it can be ensured that the low temperature gas can flow smoothly into the support plate 3. The second temperature equalization structure 6 is provided with a second through hole 14, which is arranged around the outer ring surface of the support plate 3. The second through hole 14 can adapt to the structural characteristics of the support plate 3 so that the installation structure of the support plate 3 will not be changed. On the other hand, it can block the radiative heat flow of the flow channel plate 4 to the load-bearing inner ring 2.

[0025] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A temperature equalization structure for a turbine bearing frame of an aero-engine, comprising an outer bearing ring (1), an inner bearing ring (2), and a support plate (3), wherein the support plate (3) is connected between the outer bearing ring (1) and the inner bearing ring (2), characterized in that: The outer ring of the load-bearing outer ring (1) is coaxially provided with a first temperature equalization structure (5), and the outer ring of the load-bearing inner ring (2) is coaxially provided with a second temperature equalization structure (6). The temperature of the low-temperature gas located outside the load-bearing outer ring (1) can only be transferred to the load-bearing outer ring (1) after passing through the first temperature equalization structure (5), and the heat of the main channel gas located outside the load-bearing inner ring (2) can only be transferred to the load-bearing inner ring (2) after passing through the second temperature equalization structure (6). The first temperature equalization structure (5) includes a first heat insulation ring (7) and a first fixing ring (8) disposed on both sides of the first heat insulation ring (7). The first fixing ring (8) is detachably fixedly connected to the load-bearing outer ring (1). There is a gap between the first heat insulation ring (7) and the load-bearing outer ring (1), and a closed first heat insulation cavity (11) is formed between the first heat insulation ring (7) and the load-bearing outer ring (1). The second temperature equalization structure (6) includes a second heat insulation ring (9) and a second fixing ring (10) disposed on both sides of the second heat insulation ring (9). The second fixing ring (10) is detachably fixedly connected to the load-bearing inner ring (2). There is a gap between the second heat insulation ring (9) and the load-bearing inner ring (2), and a closed second heat insulation cavity (12) is formed between the second heat insulation ring (9) and the load-bearing inner ring (2).

2. The temperature homogenization structure of the turbine load-bearing frame of an aero-engine as described in claim 1, characterized in that: The first fixing ring (8) is connected to the outer load-bearing ring (1) and the second fixing ring (10) is connected to the inner load-bearing ring (2) by bolts.

3. The temperature homogenization structure of the turbine load-bearing frame of an aero-engine as described in claim 1, characterized in that: The first temperature equalization structure (5) has a first through hole (13) which is connected to the inside of the support plate (3); the second temperature equalization structure (6) has a second through hole (14) which surrounds the outer ring surface of the support plate (3).

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