Combustion chamber transition section structure capable of being directly connected with turbine

Abstract

The invention discloses a combustion chamber transition section structure capable of being directly connected with a turbine. The problems that a combustion chamber transition section is large in cooling difficulty, complex in shape, large in machining difficulty, complex in turbine connecting structure and the like are solved. The transition section comprises a transition section front ring, a transition section body and a transition section seat ring, the transition section front ring is welded to the transition section body, the transition section body is welded to the seat ring, and the shape of the section of the transition section body is gradually transited to be in a sector shape from a round shape in the airflow direction; the bottom of the transition section front ring is connected with an n-shaped supporting structure, a cylindrical stretching structure is arranged on the rear portion of the transition section of the transition section body, and the cylindrical stretching structure is connected with the transition section connecting structure through a plug pin. The method is applied to combustion chamber transition directly connected with a turbine.

Description

Technical Field

[0001] The present invention relates to a combustion chamber transition section structure which can be directly connected to a turbine. Background Art

[0002] The combustor, one of the three major components of a gas turbine, performs two basic functions: First, from a design perspective, the combustor converts the chemical energy contained in the fuel into the internal energy of the working fluid through chemical reactions. This increases the working fluid's temperature, thereby enhancing its ability to expand and produce work within the turbine. Second, from an operational perspective, the combustor is the primary regulating component of the gas turbine. By adjusting the fuel supply to the combustor during load fluctuations, the combustor ensures smooth and efficient operation of itself and the turbine. Therefore, the performance of the combustor has a significant impact on the performance, lifespan, dimensions, and weight of the entire gas turbine. The transition section is a crucial structure in the combustor, serving as the aerodynamic bridge between the flame liner and the turbine. It transforms the circular shape of the flame liner into a fan-shaped turbine inlet, ensuring uniform mixing of the high-temperature gas. Due to the complex shape of the flame liner and its considerable cooling challenges, its machining, cooling, and mechanical connection to the turbine are complex, increasing its design complexity and manufacturing costs.

[0003] In response to the problems of the combustion chamber transition section being difficult to cool, having a complex shape and difficult machining, and having a complex connection structure with the turbine, the present invention provides a transition section structure with high cooling efficiency, simple machining, and the ability to be directly connected to the turbine, greatly reducing its design difficulty and machining and manufacturing costs. Summary of the Invention

[0004] The object of the present invention is to solve the above-mentioned problems and thereby provide a combustion chamber transition section structure that can be directly connected to a turbine.

[0005] The above purpose is achieved through the following technical solutions: A combustion chamber transition section structure capable of being directly connected to a turbine, comprising a transition section front ring, a transition section body, and a transition section seat ring. The transition section front ring is welded to the transition section body, which is welded to the seat ring. The cross-sectional shape of the transition section body gradually transitions from a circular shape to a fan shape along the airflow direction. The bottom of the front ring of the transition section is connected with a cross-shaped support structure, and the rear part of the transition section of the transition section body is provided with a cylindrical tensile structure, and the cylindrical tensile structure is connected to the transition section connection structure through a pin.

[0006] The combustion chamber transition section structure that can be directly connected to the turbine has multiple rows of inclined cooling holes on the transition section body. The cooling holes have a diameter of 0.6mm-1mm and an angle of 20°~45° with the cross-sectional profile.

[0007] The combustion chamber transition section structure can be directly connected to the turbine, the closed surface of the cylindrical tensile structure and the transition section share the same profile, and several rows of oblique cooling holes are arranged inside the cylindrical tensile structure, and the cooling holes have a diameter of 0.6~2mm.

[0008] The combustion chamber transition section structure that can be directly connected to the turbine, the transition section front ring includes a circular seat ring body, a support plate is welded on the circular seat ring body, a square hole is opened on the support plate, the I-shaped support block is fixed in the square hole, and the X-shaped support structure is connected to the support plate of the transition section front ring in a plug-in manner through the I-shaped support block.

[0009] The combustion chamber transition section structure that can be directly connected to the turbine is characterized in that the transition section seat ring is a fan-shaped structure for connecting to the turbine inlet. Beneficial effects

[0010] 1. The present invention employs dual-point support to ensure the structural stability of the transition section. An I-shaped support structure is provided at the front ring of the transition section, and a rotating pin-lift structure is employed at the rear of the transition section. When the transition section expands axially due to heat, the latch serves as the "dead point" for expansion and remains stationary. The transition section structure in front of the latch expands forward due to heat. At this time, the transition section can slide forward via the I-shaped support block, ensuring that the transition section eliminates axial thermal stress. When the transition section expands radially due to heat, the transition section can rotate around the latch. At the same time, the I-shaped support structure can deform appropriately through angular expansion to eliminate radial thermal stress. By designing appropriate degrees of freedom for deformation, this structure ensures that the transition section structure can effectively release thermal deformation when heated, reducing thermal stress and thus increasing the service life of the transition section. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 It is a structural schematic diagram of the present invention; Figure 2 is an isometric view of the present invention; Figure 3 It is a bottom view of the present invention; Figure 4 is a top view of the present invention; In the figure: 1. Transition section front ring; 2. Transition section body; 3. Pin; 4. Flame tube transition section plug-in structure; 5. Transition section seat ring; 6. I-shaped support structure; 7. I-shaped support block; 8. Support plate; 9. Cylindrical tensile structure; 10. Oblique cooling hole. DETAILED DESCRIPTION

[0012] Reference Figure 1-Figure 4A combustion chamber transition section structure capable of being directly connected to a turbine comprises a transition section front ring 1, a transition section body 2, and a transition section seat ring 5. The transition section front ring is welded to the transition section body, and the transition section body 2 is welded to the seat ring 5. The cross-sectional shape of the transition section body 2 gradually transitions from a circular shape to a fan shape along the airflow direction. The bottom of the front ring of the transition section is connected to a cross-shaped support structure, and the rear part of the transition section of the transition section body is provided with a cylindrical tensile structure, and the cylindrical tensile structure is connected to the transition section connection structure 4 through a pin 3; The latch 3 is a stud with a nut structure, used to connect the transition section body and the flame tube transition section plug-in structure 4. The transition section seat ring 5 is a fan-shaped structure, used to connect to the turbine inlet. The cross-shaped support structure 6 is used to support the flame tube. The transition section front ring is welded to the support plate, and the transition section front ring 1 is welded to the transition section body 2, resulting in a simple structure and easy welding. The transition section body 2 is integrally formed using 3D printing, despite its complex structure and shape. This 3D printing process significantly reduces mold processing costs, shortens processing cycles, and reduces processing expenses. The transition section is connected to the transition section connection structure 4 via a latch 3, a simple structure that ensures rotational freedom between the flame tube and the transition section. The transition section body 2 is welded to the seat ring 5. The "X"-shaped support structure 6 is plugged into the transition section front ring support plate via an I-shaped support block.

[0013] The transition section body is provided with a plurality of rows of oblique cooling holes, the diameter of the cooling holes is 0.6mm-1mm, and the angle between the cooling holes and the cross-sectional profile is 20°-45°.

[0014] The closed surface of the cylindrical tensile structure and the transition section share the same profile line. A plurality of rows of oblique cooling holes are arranged inside the cylindrical tensile structure, and the diameter of the cooling holes is 0.6-2 mm.

[0015] The transition section front ring includes a circular seat ring body, a support plate is welded on the circular seat ring body, a square hole is opened on the support plate, the I-shaped support block is fixed in the square hole, and the X-shaped support structure is connected to the support plate of the transition section front ring in a plug-in manner through the I-shaped support block.

[0016] The transition section seat ring 5 is a fan-shaped structure for connecting with the turbine inlet.

[0017] This transition section uses both convection cooling and radiative cooling, which have good cooling effects and simple structure. Convection cooling is used for areas with lower wall temperatures, while radiative cooling is used for areas with higher wall temperatures. This not only saves cooling gas consumption, but also ensures a relatively uniform temperature gradient in the transition section, thus giving full play to the material's optimal economic performance. The structure uses a 3D printed transition section body and a cylindrical tensile structure to connect the transition section and the turbine through a plug-in structure. It has a simple structure and is easy to process.

Claims

1. A combustion chamber transition section structure capable of being directly connected to a turbine, characterized by: The transition section comprises a front ring, a main body and a seat ring. The front ring is welded to the main body, and the main body is welded to the seat ring. The cross-section of the main body gradually transitions from a circle to a sector along the airflow direction. The bottom of the front ring of the transition section is connected with a cross-shaped support structure, and the rear part of the transition section of the transition section body is provided with a cylindrical tensile structure, and the cylindrical tensile structure is connected to the transition section connection structure through a pin.

2. A combustion chamber transition section structure capable of being directly connected to a turbine according to claim 1, characterized in that: The transition section body is provided with a plurality of rows of oblique cooling holes, the diameter of the cooling holes is 0.6mm-1mm, and the angle between the cooling holes and the cross-sectional profile is 20°-45°.

3. The combustion chamber transition section structure capable of being directly connected to a turbine according to claim 2, characterized in that: The closed surface of the cylindrical tensile structure and the transition section share the same profile line. A plurality of rows of oblique cooling holes are arranged inside the cylindrical tensile structure, and the diameter of the cooling holes is 0.6-2 mm.

4. A combustion chamber transition section structure capable of being directly connected to a turbine according to claim 3, characterized in that: The transition section front ring includes a circular seat ring body, a support plate is welded on the circular seat ring body, a square hole is opened on the support plate, the I-shaped support block is fixed in the square hole, and the X-shaped support structure is connected to the support plate of the transition section front ring in a plug-in manner through the I-shaped support block.

5. The combustion chamber transition section structure capable of being directly connected to a turbine according to claim 4, characterized in that: The transition section seat ring is a fan-shaped structure and is used to connect with the turbine inlet.

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