A support structure for annular flame tube of a gas turbine

Abstract

This invention relates to a support structure for an annular flame tube of a gas turbine, comprising a hot-end mounting ring and a cold-end mounting ring. The hot-end mounting ring has a T-shaped structure, with its top connected to the outer wall of the tail section of the annular flame tube. The cold-end mounting ring is fixed inside the compressor rear cover plate by a rear clamping ring. During gas turbine operation, the temperature of the annular flame tube rises, causing thermal expansion and deformation in both the radial and axial directions. The thin-walled structure deforms accordingly, releasing the thermal stress of the annular flame tube. The beneficial effects of this invention are: the hot-end mounting ring and the cold-end mounting ring are connected by a thin-walled structure, and the support point is extended through the r-shaped thin-walled structure. When the flame tube undergoes thermal deformation, there is a longer support section, thereby reducing the thermal deformation per unit length, significantly reducing the thermal stress of the support structure, and simultaneously withstanding the thermal deformation of the flame tube in both the radial and axial directions, thus extending the service life of the flame tube.

Description

Technical Field

[0001] This invention belongs to the field of gas turbines, and particularly relates to a support structure for annular flame tubes of gas turbines. Background Technology

[0002] After fuel combustion in a gas turbine, high-temperature flue gas is produced. This high-temperature flue gas is then guided into the turbine to perform work. The flame tube is installed at room temperature, but it operates at high temperature during gas turbine operation. Thermal expansion causes significant deformation. If the installation structure is not properly designed, it can generate substantial thermal stress, affecting the lifespan of components and the gas turbine itself.

[0003] Therefore, the installation of the flame tube inevitably requires consideration of high-temperature thermal deformation in the design. Patent CN103486619A uses an inner Z-shaped support ring and an outer U-shaped support ring for dual positioning, which can ensure the release of thermal stress in the flame tube. However, both the inner and outer edges of the support ring are fastened with rivets and multiple bolts, making the installation process relatively complex. Patent CN213421175U uses guide pins installed inside circumferentially distributed guide support tubes to achieve radial centering of the combustion chamber. While releasing radial thermal stress, it can also ensure the coaxiality of the combustion chamber and the nozzle. However, since the combustion chamber and the cooling cylinder are directly welded together, a certain amount of thermal stress will still be generated in the axial direction. Summary of the Invention

[0004] The purpose of this invention is to overcome the shortcomings of the prior art and provide a support structure for the annular flame tube of a gas turbine.

[0005] This gas turbine annular flame tube support structure is used to fix the annular flame tube and the tail end of the compressor rear cover plate. The support structure includes a hot end mounting ring and a cold end mounting ring. The hot end mounting ring has a T-shaped structure. The top of the T-shaped structure is connected to the outer wall of the tail of the annular flame tube. The cold end mounting ring is fixed inside the compressor rear cover plate by a rear clamping ring.

[0006] The hot end mounting ring and the cold end mounting ring are connected by a thin-walled structure; the thin-walled structure is an R-shaped thin-walled structure or a reverse-folded thin-walled ring, and the R-shaped thin-walled structure includes a cylindrical thin-walled ring and a bent thin-walled ring.

[0007] A cylindrical thin-walled ring is installed at the end of the hot-end mounting ring facing the cold-end mounting ring; in cross-section, the cylindrical thin-walled ring is perpendicular to the bottom of the T-shaped structure of the hot-end mounting ring, and the cold-end mounting ring is perpendicular to the cylindrical thin-walled ring.

[0008] The cold end mounting ring is fixedly connected to the cylindrical thin-walled ring by a bent thin-walled ring; one end of the bent thin-walled ring extends vertically from the cold end mounting ring to the cylindrical thin-walled ring, and after being bent at 90°, the other end is welded to the surface of the cylindrical thin-walled ring.

[0009] Preferably, the end where the bent thin-walled ring and the cylindrical thin-walled ring are attached is away from the axis of the annular flame tube.

[0010] Preferably, the thin-walled structure is a reverse-folded thin-walled ring with a U-shaped bend in the middle. The protrusion of the U-shaped bend is away from the axis of the annular flame tube. One end of the U-shaped bend extends to the bottom end of the T-shaped structure of the hot end mounting ring, and the other end of the U-shaped bend is bent and connected to the end of the cold end mounting ring.

[0011] Preferably, welding is used to connect the hot-end mounting ring and the cylindrical thin-walled ring, the cylindrical thin-walled ring and the bent thin-walled ring, and the bent thin-walled ring and the cold-end mounting ring. The end of the hot-end mounting ring is welded to the annular flame tube.

[0012] Preferably, one end of the rear clamping ring is inserted into the inner surface of the rear end of the compressor rear cover plate, and together with the compressor rear cover plate, they press against the cold end mounting ring. The other end of the rear clamping ring is fixed to the rear end of the compressor rear cover plate by a locking screw.

[0013] The method of using this gas turbine annular flame tube support structure includes the following steps:

[0014] Step 1: Weld the hot-end mounting ring, thin-walled structure, and cold-end mounting ring together in sequence to form a support structure;

[0015] Step 2: Weld the hot end mounting ring on the support structure to the tail of the annular flame tube, and push the annular flame tube and the support structure as a whole into the tail end of the compressor rear cover plate.

[0016] Step 3: Install the rear clamping ring. Use the rear clamping ring to fix the cold end mounting ring of the support structure to the inside of the compressor rear cover plate.

[0017] Step 4: When the gas turbine is running, the temperature of the annular flame tube rises, and the annular flame tube undergoes thermal expansion and deformation in both the radial and axial directions. The thin-walled structure deforms accordingly, releasing the thermal stress of the annular flame tube.

[0018] Preferably, when the thin-walled structure is an R-shaped thin-walled structure, the ends of the cylindrical thin-walled ring and the bent thin-walled ring in the support structure are bent to release the thermal stress of the annular flame tube.

[0019] Preferably, when the thin-walled structure is a reverse-folded thin-walled ring, the deformation of the reverse-folded thin-walled ring releases the thermal stress of the annular flame tube.

[0020] The beneficial effects of this invention are:

[0021] 1) The present invention fixes the two ends of the support structure to the annular flame tube and the tail of the compressor rear cover plate, respectively. The support structure has a simple processing technology and is easy to install. The hot end mounting ring and the cold end mounting ring are connected by a thin-walled structure. The support point is extended by the r-shaped thin-walled structure. When the flame tube undergoes thermal deformation, there is a longer support section, thereby reducing the thermal deformation per unit length and greatly reducing the thermal stress of the support structure. The support structure can simultaneously withstand the thermal deformation of the flame tube in the radial and axial directions. While supporting the flame tube, it ensures its relative free deformation in the hot state, reduces the thermal stress of the flame tube parts, and extends the service life of the flame tube.

[0022] 2) It is also proposed that the thin-walled structure can be a reverse-folded thin-walled ring with a U-shaped bend in the middle, which further simplifies the processing technology and can also extend the support point, so that the support structure can simultaneously withstand the thermal deformation generated by the flame tube in the radial and axial directions, thus extending the service life of the flame tube. Attached Figure Description

[0023] Figure 1 A schematic diagram of a half-section structure supporting the annular flame tube of a gas turbine.

[0024] Figure 2 This is a schematic diagram of the half-section structure of the annular flame tube and its supporting structure after thermal expansion and deformation.

[0025] Figure 3 This is a half-section diagram of the structure of a cylindrical thin-walled ring and a bent thin-walled ring combined into a reverse-folded thin-walled ring.

[0026] Explanation of reference numerals in the attached drawings: 1. Annular flame tube; 2. Hot end mounting ring; 3. Cylindrical thin-walled ring; 4. Bending thin-walled ring; 5. Cold end mounting ring; 6. Compressor rear cover plate; 7. Rear clamping ring; 8. Anti-loosening gasket; 9. Locking screw; 10. Reverse folded thin-walled ring. Detailed Implementation

[0027] The present invention will be further described below with reference to embodiments. The description of the embodiments below is only for the purpose of helping to understand the present invention. It should be noted that those skilled in the art can make several modifications to the present invention without departing from the principle of the present invention, and these improvements and modifications also fall within the protection scope of the claims of the present invention.

[0028] Example 1

[0029] As one example, such as Figure 1 and Figure 2As shown, this gas turbine annular flame tube support structure is used to fix the annular flame tube 1 and the tail end of the compressor rear cover plate 6. The support structure includes a hot end mounting ring 2 and a cold end mounting ring 5. From a half-section view, the hot end mounting ring 2 has a T-shaped structure. The top of the T-shaped structure is connected to the outer wall of the tail of the annular flame tube 1, that is, the outer circle of the hot end mounting ring 2 smoothly transitions with the annular flame tube 1.

[0030] The cold end mounting ring 5 is fixed inside the compressor rear cover plate 6 by the rear clamping ring 7; one end of the rear clamping ring 7 is inserted into the inner surface of the tail of the compressor rear cover plate 6, and together with the compressor rear cover plate 6, it squeezes the cold end mounting ring 5; the other end of the rear clamping ring 7 is fixed to the tail of the compressor rear cover plate 6 by the locking screw 9, and is used with the anti-loosening gasket 8 to prevent loosening.

[0031] The hot-end mounting ring 2 and the cold-end mounting ring 5 are relatively thick and are machined to ensure assembly reliability and meet the mating area requirements for part positioning. The hot-end mounting ring 2 and the cold-end mounting ring 5 are connected by a thin-walled structure.

[0032] The thin-walled structure is an r-shaped thin-walled structure, which includes a cylindrical thin-walled ring 3 and a bent thin-walled ring 4. The cylindrical thin-walled ring 3 and the bent thin-walled ring 4 can be formed by sheet metal to reduce the processing cost of the parts and make them less rigid and easier to deform under thermal stress.

[0033] The cylindrical thin-walled ring 3 is installed at the end of the hot-end mounting ring 2 facing the cold-end mounting ring 5; in cross-section, the cylindrical thin-walled ring 3 is perpendicular to the bottom of the T-shaped structure of the hot-end mounting ring 2, and the cold-end mounting ring 5 is perpendicular to the cylindrical thin-walled ring 3.

[0034] The cold-end mounting ring 5 is fixedly connected to the cylindrical thin-walled ring 3 via a bent thin-walled ring 4. One end of the bent thin-walled ring 4 extends vertically from the cold-end mounting ring 5 to the cylindrical thin-walled ring 3, bends at 90°, and the other end is welded to the surface of the cylindrical thin-walled ring 3. Welded connections are used between the hot-end mounting ring 2 and the cylindrical thin-walled ring 3, between the cylindrical thin-walled ring 3 and the bent thin-walled ring 4, and between the bent thin-walled ring 4 and the cold-end mounting ring 5, so that the four parts of the support structure form a whole. The end of the hot-end mounting ring 2 is welded to the annular flame tube 1, while the cold-end mounting ring 5 is detachably connected to the cold-end components.

[0035] The end of the bent thin-walled ring 4 and the cylindrical thin-walled ring 3 that are in contact with each other is away from the axis of the annular flame tube 1. That is, the root of the r-shape faces the side away from the axis of the annular flame tube 1. The support point is extended through the r-shaped thin-walled structure. When the flame tube undergoes thermal deformation, there is a longer support section, which guides the r-shaped thin-walled structure to move in this direction during deformation. Under the same temperature difference, the thermal deformation length is longer, so the thermal deformation per unit length is reduced, which reduces the thermal stress of the r-shaped thin-walled structure itself.

[0036] Example 2

[0037] As another embodiment, based on the first embodiment, this second embodiment proposes that the thin-walled structure of the gas turbine annular flame tube support structure can also be a reverse-folded thin-walled ring 10, that is, the reverse-folded thin-walled ring 10 replaces the r-shaped thin-walled structure formed by the bent thin-walled ring 4 and the cylindrical thin-walled ring 3.

[0038] like Figure 2 As shown, the thin-walled structure is a reverse-folded thin-walled ring 10. The reverse-folded thin-walled ring 10 has a U-shaped bend in the middle. One end of the U-shaped bend extends to the bottom end of the T-shaped structure of the hot end mounting ring 2, and the other end of the U-shaped bend is bent and connected to the end of the cold end mounting ring 5.

[0039] The U-shaped bend protrudes away from the axis of the annular flame tube 1, which is equivalent to replacing the part where the bent thin-walled ring 4 and the cylindrical thin-walled ring 3 fit together. The U-shaped bend does not bend all the way down, but leaves an arc, which is convenient for subsequent deformation as the thermal stress of the annular flame tube 1 is released.

[0040] It should be noted that the parts in this embodiment that are the same as or similar to those in Embodiment 1 can be referred to each other, and will not be repeated in this application.

[0041] Example 3

[0042] As another embodiment, this third embodiment, based on embodiments one and two, proposes a method for using this gas turbine annular flame tube support structure, wherein the installation of this gas turbine annular flame tube support structure includes the following steps:

[0043] Step 1: Weld the hot-end mounting ring 2, the thin-walled structure, and the cold-end mounting ring 5 together in sequence to form a support structure. When the thin-walled structure is an R-shaped thin-walled structure, weld the hot-end mounting ring 2, the cylindrical thin-walled ring 3, the bent thin-walled ring 4, and the cold-end mounting ring 5 together in sequence. When the thin-walled structure is a reverse-folded thin-walled ring 10, weld the hot-end mounting ring 2, the reverse-folded thin-walled ring 10, and the cold-end mounting ring 5 together in sequence to form a support structure.

[0044] Step 2: Weld the hot end mounting ring 2 on the support structure to the tail of the annular flame tube 1, and push the annular flame tube 1 and the support structure as a whole axially into the tail end of the compressor rear cover plate 6.

[0045] Step 3: After installation, tighten the clamping ring 7 and tighten it with the locking screw 9. Use the anti-loosening washer 8 to prevent loosening. This makes it very easy to complete the positioning and installation of the entire annular flame tube 1.

[0046] Example 4

[0047] As another embodiment, this embodiment four, based on embodiment three, proposes a method for using this gas turbine annular flame tube support structure, which includes step four after installation is completed.

[0048] Step four specifically involves the following: during the operation of the gas turbine, the entire annular flame tube 1 is in a high-temperature state, and at the same time, some heat will be transferred to the support structure, causing the temperature of the support structure to rise. Compared with the low-temperature state of the compressor rear cover plate 6, the annular flame tube 1 and the support structure deform due to thermal expansion.

[0049] When the thin-walled structure is an R-shaped thin-walled structure, the ends of the cylindrical thin-walled ring 3 and the bent thin-walled ring 4 in the supporting structure are bent, such as... Figure 2 As shown, the annular flame tube 1 expands radially. At this time, the cold-end mounting ring 5 hardly deforms, while the portion of the cylindrical thin-walled ring 3 and the bent thin-walled ring 4 welded together in the r-shaped thin-walled structure deflects, and the separated ends bend in accordance with the change at the tail end of the annular flame tube 1. When the thin-walled structure is a reverse-folded thin-walled ring 10, the reverse-folded thin-walled ring 10 also deforms, conforming to the change at the tail end of the annular flame tube 1.

[0050] Due to the flexible structure of the r-shaped thin-walled structure and the reverse-folded thin-walled ring 10, the annular flame tube 1 can expand freely in the radial direction without being constrained in the axial direction. Therefore, the thermal stress of the annular flame tube 1 is well released, thereby extending its service life.

[0051] It should be noted that the parts in this embodiment that are the same as or similar to those in Embodiment 3 can be referred to each other, and will not be repeated in this application.

[0052] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

Claims

1. A gas turbine annular flame tube support structure, characterized by, The application discloses a supporting structure for connecting a ring-shaped flame tube and a tail end of a compressor rear cover plate. The supporting structure comprises a hot end mounting ring and a cold end mounting ring. The hot end mounting ring is in a T-shaped structure, and the top of the T-shaped structure is connected with the outer wall of the tail end of the ring-shaped flame tube. The cold end mounting ring is fixed in the compressor rear cover plate through a rear pressing ring.

2. The gas turbine annular flame tube support structure as claimed in claim 1, wherein, The hot end mounting ring and the cold end mounting ring are connected through a thin wall structure.

3. The gas turbine annular flame tube support structure according to Claim 1, wherein, The thin wall structure is an r-shaped thin wall structure.

4. The gas turbine annular flame tube support structure according to Claim 1, wherein, The r-shaped thin wall structure comprises a cylindrical thin wall ring and a bent thin wall ring.

5. A method of using a gas turbine annular flame tube support structure as claimed in any one of claims 1 to 4, wherein, The cylindrical thin wall ring is installed at one end of the hot end mounting ring towards the cold end mounting ring. In a cross section, the cylindrical thin wall ring is perpendicular to the bottom of the T-shaped structure of the hot end mounting ring, and the cold end mounting ring is perpendicular to the cylindrical thin wall ring. The cold end mounting ring is fixedly connected with the cylindrical thin wall ring through the bent thin wall ring. One end of the bent thin wall ring extends perpendicularly from the cold end mounting ring to the cylindrical thin wall ring, and the other end is welded to the surface of the cylindrical thin wall ring after being bent by 90 degrees. The end of the bent thin wall ring and the cylindrical thin wall ring away from the axis of the ring-shaped flame tube.

6. The method of using a gas turbine annular flame tube support structure of claim 5, wherein, The hot end mounting ring, the cylindrical thin wall ring, the bent thin wall ring and the cold end mounting ring are connected through welding. One end of the rear pressing ring is inserted into the inner surface of the tail end of the compressor rear cover plate, and the rear pressing ring and the compressor rear cover plate jointly press the cold end mounting ring. The other end of the rear pressing ring is fixed to the tail end of the compressor rear cover plate through a locking screw. The supporting structure is formed by sequentially welding the hot end mounting ring, the thin wall structure and the cold end mounting ring. The hot end mounting ring of the supporting structure is welded to the tail end of the ring-shaped flame tube, and the ring-shaped flame tube and the supporting structure are pushed into the tail end of the compressor rear cover plate. The rear pressing ring is installed, and the cold end mounting ring of the supporting structure is fixed to the inner side of the compressor rear cover plate through the rear pressing ring. When the thin wall structure is the r-shaped thin wall structure, the end of the cylindrical thin wall ring and the bent thin wall ring in the supporting structure is bent, and the thermal stress of the ring-shaped flame tube is released.

Images