An assembly tooling for preventing deformation during welding of gas turbine flame tubes and its usage method

Abstract

This invention relates to an assembly fixture and method for preventing deformation during welding of a gas turbine flame tube. To address the difficulty in effectively controlling the concentricity and other positional requirements of the three thin-walled sections during flame tube assembly, and the resulting severe product deformation during welding, which fails to meet assembly requirements and easily increases the scrap rate, the lower end of a support mandrel is fixed to the middle of a support base plate. Lower and upper external support components are mounted on the support mandrel, and an upper pressure plate is fitted onto the upper part of the upper external support component. A large nut is located above the upper pressure plate. During gas turbine flame tube installation, the lower part of the front ring section of the flame tube is fitted onto the boss on the support base plate, and the upper part of the rear ring section is fitted onto the boss on the upper pressure plate. The turbulence section of the flame tube is located between these two. This solution can strictly control the shape and position of the flame tube during welding and prevent deformation during the welding process. Furthermore, the fixture is easy to disassemble and use.

Description

Technical Field

[0001] This invention relates to the field of gas turbine flame tube welding technology, specifically to an assembly tooling and method for preventing deformation during gas turbine flame tube welding. Background Technology

[0002] The combustion chamber of an internal combustion engine is the core component of a gas turbine unit. It mixes natural gas and air, burns the mixture, and sends the combustion products to the compressor to perform work. The flame tube is the core component of the combustion chamber. In a certain gas turbine, the flame tube consists of three sections: a front annular section, a turbulence section, and a cooling section. The front annular and cooling sections are made by rolling thin plates into cylindrical shapes and then welding them into a cylindrical shape. The turbulence section is made by rolling thin plates into conical shapes and then welding them into a conical cylinder, which are then welded together using argon arc welding to form the flame tube. The flame tube is assembled from large-sized thin-walled components, with a diameter greater than 500mm and a thickness not exceeding 3.5mm, and is made of high-temperature alloy materials. During the assembly of the flame tube, it is difficult to effectively control the concentricity and other positional requirements of the three thin-walled components. Furthermore, the product deforms severely during the welding process, failing to meet assembly requirements and easily increasing the scrap rate. Summary of the Invention

[0003] The purpose of this invention is to solve the problem that it is difficult to effectively control the concentricity and other positional requirements of the three thin-walled parts when assembling the flame tube, and that the product is severely deformed during the welding process, which fails to meet the assembly requirements and easily increases the scrap rate. This invention provides an assembly tooling and method for preventing deformation during the welding of gas turbine flame tubes.

[0004] The objective of this invention is achieved as follows: an assembly fixture for preventing deformation during welding of a gas turbine flame tube, characterized in that it includes an upper pressure plate, a large nut, a support mandrel, a support base plate, a lower external support assembly, and an upper external support assembly;

[0005] The lower end of the support mandrel is fixed to the middle of the support base plate. The lower outer support assembly and the upper outer support assembly are installed sequentially from bottom to top on the support mandrel and are arranged coaxially with the support mandrel. The upper pressure plate is fitted onto the upper part of the upper outer support assembly. The large nut is located above the upper pressure plate and is threadedly connected to the support mandrel. When the gas turbine flame tube is installed, the lower part of the front ring section of the gas turbine flame tube is fitted onto the boss of the support base plate. The upper part of the front ring section and the lower part of the turbulence section of the gas turbine flame tube are fitted onto the outer support section of the lower outer support assembly. The upper part of the turbulence section and the lower part of the rear ring section of the gas turbine flame tube are fitted onto the outer support section of the upper outer support assembly. The upper part of the rear ring section of the gas turbine flame tube is fitted onto the boss of the upper pressure plate.

[0006] Furthermore, a washer is provided between the upper pressure plate and the large nut.

[0007] Furthermore, the lower external support assembly includes a nut, a tapered sleeve, a front ring section cover plate, a front ring section positioning disc, a pad, and a front ring section support plate;

[0008] The conical sleeve, front ring section cover plate, front ring section positioning disc, pad block, and front ring section support plate are all arranged coaxially with the support mandrel;

[0009] The pads are arranged on the support base plate, and the front ring section positioning plate is set on the pads. Multiple concentrically arranged front ring section guide ridges are integrally formed on the top of the front ring section positioning plate. The front ring section support plate includes multiple front ring section fan-shaped support plates. The inner ring of each front ring section fan-shaped support plate has a ramp that slopes from top to bottom towards the center. The multiple front ring section fan-shaped support plates are arranged above the front ring section positioning plate, and each front ring section fan-shaped support plate is positioned between two adjacent front ring section guide ridges. The front ring section cover plate is positioned above the multiple front ring section guide ridges, and the front ring section cover plate is connected to each front ring section guide ridge through multiple sets of... The positioning components are connected and fixed. The bottom of the cone sleeve is inverted cone-shaped. The cone sleeve is fitted onto the support mandrel. Nut 1 is located above the cone sleeve and is threadedly connected to the support mandrel. In the initial state, the cone sleeve is located above the inner ring of the front ring section support plate. The upper part of the front ring section of the gas turbine flame tube and the lower part of the turbulence section of the gas turbine flame tube are fitted onto the outer wall of the front ring section support plate. During the tightening of nut 1, the cone sleeve presses against the slope of multiple front ring section fan-shaped support plates, causing multiple front ring section fan-shaped support plates to move outward. The multiple front ring section fan-shaped support plates open up the upper part of the front ring section of the gas turbine flame tube and the lower part of the turbulence section of the gas turbine flame tube.

[0010] Furthermore, a washer is provided between the nut and the tapered sleeve.

[0011] Furthermore, the front annular sector support plate has a front annular sector support plate groove in the middle of its side wall, and a front annular flow ring is embedded in the front annular sector support plate groove. The front annular flow ring has multiple front annular flow ring air holes arranged radially thereon. The front annular sector support plate has front annular sector support plate air holes that connect its bottom end face to the front annular sector support plate groove. The front annular positioning plate has multiple front annular positioning plate air holes arranged axially thereon. The base plate has multiple base plate air holes arranged axially thereon. When welding shielding gas is input, it passes through the base plate air holes, the front annular positioning plate air holes, the front annular sector support plate air holes, and the front annular sector flow ring air holes in sequence.

[0012] Furthermore, the upper external support assembly includes a second nut, a positioning cone sleeve, a spoiler section cover plate, a spoiler section support plate, a spoiler section positioning disc, and a third gasket;

[0013] The positioning cone sleeve, the spoiler section cover plate, the spoiler section support plate, the spoiler section positioning disc, and the gasket are all arranged coaxially with the support mandrel;

[0014] The third gasket is located above the stepped support mandrel. The spoiler section positioning plate is mounted on the third gasket. Multiple concentrically arranged spoiler section guide ridges are integrally formed on the top of the spoiler section positioning plate. The spoiler section support plate includes multiple spoiler section fan-shaped support plates. The inner ring of each spoiler section fan-shaped support plate has a slope that slopes from top to bottom towards the center. The multiple spoiler section fan-shaped support plates are arranged above the spoiler section positioning plate, and each spoiler section fan-shaped support plate is positioned between two adjacent spoiler section guide ridges. The spoiler section cover plate is positioned above the multiple spoiler section guide ridges, and the spoiler section cover plate is also connected to each spoiler section guide ridge via multiple sets of positioning... The positioning components are connected and fixed. The bottom of the positioning cone sleeve is inverted cone-shaped. The positioning cone sleeve is fitted onto the support mandrel. Nut 2 is located on the positioning cone sleeve and is threadedly connected to the support mandrel. In the initial state, the positioning cone sleeve is located above the inner ring of the turbulence section support plate. The upper part of the turbulence section and the lower part of the cooling section of the gas turbine flame tube are fitted onto the outer wall of the turbulence section support plate. During the tightening of nut 2, the positioning cone sleeve presses against the slope of multiple turbulence section fan-shaped support plates, causing the multiple turbulence section fan-shaped support plates to move outward. The multiple turbulence section fan-shaped support plates open up the upper part of the turbulence section and the lower part of the cooling section of the gas turbine flame tube.

[0015] Furthermore, a washer four is provided between nut two and the positioning cone sleeve.

[0016] Furthermore, the positioning component includes a cylindrical pin and a plurality of positioning bolts;

[0017] The front ring section cover plate and each front ring section guide protrusion are limited by a cylindrical pin, and the two are connected and fixed by multiple positioning bolts. A gasket is installed between the positioning bolt and the top surface of the front ring section cover plate.

[0018] The spoiler section cover plate and each spoiler section guide protrusion are limited by a cylindrical pin, and the two are connected and fixed by multiple positioning bolts. A gasket is installed between the positioning bolt and the top surface of the spoiler section cover plate.

[0019] Furthermore, the side wall of the turbulence section fan-shaped support plate is provided with a turbulence section fan-shaped support plate annular groove. The turbulence section fan-shaped support plate is embedded with a turbulence section flow ring, and the turbulence section flow ring is provided with a plurality of turbulence section flow ring air holes arranged radially thereon. The turbulence section fan-shaped support plate is provided with turbulence section fan-shaped support plate air holes that connect its top surface and the turbulence section fan-shaped support plate annular groove. The turbulence section cover plate is provided with a plurality of turbulence section cover plate air holes arranged axially thereon. The upper pressure plate is provided with a plurality of upper pressure plate air holes arranged axially thereon. When welding shielding gas is input, it passes through the upper pressure plate air holes, the turbulence section cover plate air holes, the turbulence section fan-shaped support plate air holes and the turbulence section flow ring air holes in sequence.

[0020] A method for using an assembly fixture to prevent deformation during welding of a gas turbine flame tube includes the following steps:

[0021] Step 1: Place the support base plate on the support platform, then fit the front ring section of the gas turbine flame tube onto the chamfered boss of the support base plate. Distribute multiple spacers evenly on the upper surface of the support base plate. Place the front ring section positioning plate on the spacers, and then place multiple front ring section fan-shaped support plates onto the positioning plate. Install the front ring section cover plate. Place the conical sleeve onto the support mandrel of the support base plate, ensuring the sleeve just barely inserts into the circular hole formed by the multiple front ring section support plates. Next, place the turbulence-inducing section of the gas turbine flame tube onto the front ring section. Assemble nut one and washer one, and use socket wrench II to tighten nut one, moving the conical sleeve downwards until the front ring section and turbulence-inducing section of the gas turbine flame tube are formed into a circle. Install and tighten the positioning bolts. After the front ring section cover plate and the front ring section guide ridge are securely connected, the positions of the multiple front ring section support plates are determined.

[0022] Step 2: Place shim 3, place the turbulence section positioning plate on shim 3, place multiple turbulence section fan-shaped support plates on the turbulence section positioning plate, and install the turbulence section cover plate. Then place the cooling section of the gas turbine flame tube on the turbulence section of the gas turbine flame tube, put the positioning cone sleeve on the support mandrel, and install the upper pressure plate at the same time. First, use socket wrench 1 to tighten nut 2 until the turbulence section and cooling section of the gas turbine flame tube are stretched into a circle. Then tighten the large nut to make the contact end faces of the front ring section, the turbulence section, and the cooling section of the gas turbine flame tube fit tightly.

[0023] Step 3: Inject argon gas into the tooling through the air holes in the upper pressure plate and the supporting base plate.

[0024] Argon gas enters the cavity at the welded joint of the gas turbine flame tube by passing through the air holes of the upper pressure plate, the air holes of the turbulence section cover plate, the air holes of the turbulence section fan-shaped support plate, and the air holes of the turbulence section flow ring in sequence, thus isolating the air.

[0025] Argon gas enters the cavity at the welded joint of the gas turbine flame tube by passing through the air holes of the support base plate, the air holes of the front ring section positioning plate, the air holes of the front ring section fan-shaped support plate, and the air holes of the front ring section flow ring in sequence, thus isolating the air.

[0026] Step 4: After the welding has completely cooled, remove the large nut and the upper pressure plate, then remove the second nut and remove all the components of the upper external support assembly, then remove the first nut and remove all the components of the lower external support assembly, and finally remove the welded gas turbine flame tube.

[0027] Beneficial effects:

[0028] The assembly fixtures in this solution can strictly control the shape and position of the flame tube during welding and prevent its deformation. The fixtures are also easy to disassemble, ensuring that the product meets design and usage requirements, greatly improving the product qualification rate and providing a guarantee for subsequent overall assembly. Attached Figure Description

[0029] Figure 1 This is a schematic diagram of an assembly fixture used to prevent deformation during the welding of gas turbine flame tubes;

[0030] Figure 2 yes Figure 1 AA view;

[0031] Figure 3 This is a schematic diagram of the gas turbine's flame tube;

[0032] Figure 4 This is a partial schematic diagram of the upper pressure plate;

[0033] Figure 5 This is a schematic diagram of the positioning cone sleeve;

[0034] Figure 6 This is a schematic diagram of the spoiler section cover;

[0035] Figure 7 This is a schematic diagram of the flow loop in the turbulence section;

[0036] Figure 8 This is a schematic diagram of the front loop section;

[0037] Figure 9 This is a schematic diagram of the fan-shaped support plate of the spoiler section;

[0038] Figure 10 yes Figure 9 Top view;

[0039] Figure 11 This is a schematic diagram of the positioning disc for the spoiler section;

[0040] Figure 12 yes Figure 11 Top view;

[0041] Figure 13 This is a schematic diagram of a conical sleeve;

[0042] Figure 14 This is a schematic diagram of the front ring section cover plate;

[0043] Figure 15 This is a schematic diagram of the front ring section fan-shaped support plate;

[0044] Figure 16 yes Figure 15 Top view;

[0045] Figure 17 This is a schematic diagram of the front ring section positioning disc;

[0046] Figure 18 yes Figure 17 Top view;

[0047] Figure 19 This is a schematic diagram of the supporting spindle and the supporting base plate;

[0048] Figure 20 This is a schematic diagram of socket wrench I;

[0049] Figure 21 This is a schematic diagram of socket wrench II. Detailed Implementation

[0050] Specific implementation method one: An assembly tool for preventing deformation during welding of gas turbine flame tubes, which includes an upper pressure plate 1, a large nut 4, a support mandrel 3, a support base plate 21, a lower external support assembly and an upper external support assembly;

[0051] The lower end of the support spindle 3 is fixed to the middle of the support base plate 21. The lower outer support assembly and the upper outer support assembly are sequentially installed on the support spindle 3 from bottom to top and are arranged coaxially with the support spindle 3. The upper pressure plate 1 is fitted onto the upper part of the upper outer support assembly. The large nut 4 is located above the upper pressure plate 1 and is threadedly connected to the support spindle 3. When the gas turbine flame tube is installed, the lower part of the front ring section of the gas turbine flame tube is fitted onto the boss of the support base plate 21. The upper part of the front ring section and the lower part of the turbulence section of the gas turbine flame tube are fitted onto the outer support section of the lower outer support assembly. The upper part of the turbulence section and the lower part of the rear ring section of the gas turbine flame tube are fitted onto the outer support section of the upper outer support assembly. The upper part of the rear ring section of the gas turbine flame tube is fitted onto the boss of the upper pressure plate 1.

[0052] In this embodiment: When installing the gas turbine flame tube, the lower part of the front ring section of the gas turbine flame tube is fitted onto the boss of the support base plate, the upper part of the front ring section and the lower part of the turbulence section of the gas turbine flame tube are fitted onto the outer support section of the lower outer support assembly, the upper part of the turbulence section and the lower part of the rear ring section of the gas turbine flame tube are fitted onto the outer support section of the upper outer support assembly, and the upper part of the rear ring section of the gas turbine flame tube is fitted onto the boss of the upper pressure plate. This installation method is simple and easy to operate.

[0053] Specific implementation method 2: An assembly fixture for preventing deformation during welding of gas turbine flame tubes, wherein a washer 2 is provided between the upper pressure plate 1 and the large nut 4.

[0054] Other implementation methods are the same as those in Specific Implementation Method 1.

[0055] Specific implementation method three: An assembly tool for preventing deformation during welding of gas turbine flame tube, wherein the lower external support assembly includes a nut 13, a conical sleeve 15, a front ring section cover plate 16, a front ring section positioning plate 19, a pad block 20 and a front ring section support plate;

[0056] The conical sleeve 15, the front ring section cover plate 16, the front ring section positioning plate 19, the pad block 20 and the front ring section support plate are all arranged coaxially with the support mandrel 3;

[0057] A pad 20 is arranged on the support base plate 21. A front ring section positioning plate 19 is set on the pad 20. The top of the front ring section positioning plate 19 is integrally provided with multiple concentrically arranged front ring section guide protrusions 19-1. The front ring section support plate includes multiple front ring section fan-shaped support plates 18. The inner ring of each front ring section fan-shaped support plate 18 is provided with a slope that slopes from top to bottom towards the center. The multiple front ring section fan-shaped support plates 18 are arranged above the front ring section positioning plate 19. Each front ring section fan-shaped support plate 18 is positioned between two adjacent front ring section guide protrusions 19-1. The front ring section cover plate 16 is positioned above the multiple front ring section guide protrusions 19-1 and is connected to each front ring section guide protrusion. Ridge 19-1 is connected and fixed by multiple sets of positioning components. The bottom of the cone sleeve 15 is inverted cone-shaped. The cone sleeve 15 is fitted on the support mandrel 3. Nut 13 is located above the cone sleeve 15 and is threadedly connected to the support mandrel 3. In the initial state, the cone sleeve 15 is located above the inner ring of the front ring section support plate. The upper part of the front ring section of the gas turbine flame tube and the lower part of the turbulence section of the gas turbine flame tube are fitted on the outer wall of the front ring section support plate. During the tightening of nut 13, the cone sleeve 15 presses against the slope of multiple front ring section fan-shaped support plates 18, causing multiple front ring section fan-shaped support plates 18 to move outward. The multiple front ring section fan-shaped support plates 18 open up the upper part of the front ring section of the gas turbine flame tube and the lower part of the turbulence section of the gas turbine flame tube.

[0058] In this embodiment: during the tightening of the nut, the tapered sleeve presses against the slope of the multiple front annular sector support plates, causing the multiple front annular sector support plates to move outward. The multiple front annular sector support plates spread out the upper part of the front annular section of the gas turbine flame tube and the lower part of the turbulence section of the gas turbine flame tube to form a circle.

[0059] Other implementation methods are the same as those in Specific Implementation Method 1.

[0060] Specific implementation method four: An assembly tool for preventing deformation during welding of gas turbine flame tubes, wherein a washer 14 is provided between the nut 13 and the tapered sleeve 15.

[0061] Other implementation methods are the same as those in Specific Implementation Method 3.

[0062] Specific Embodiment Five: An assembly fixture for preventing deformation during welding of a gas turbine flame tube, wherein the side wall of the front annular sector support plate 18 is provided with a front annular sector support plate groove 18-1, a front annular flow ring 17 is embedded in the front annular sector support plate groove 18-1, and a plurality of front annular sector flow ring vents 17-1 are provided on the front annular sector flow ring 17 arranged radially thereon. The front annular sector support plate 18 is provided with a bottom end face and a front annular sector support plate. The annular groove 18-1 connects to the front annular section fan-shaped support plate vent 18-2. The front annular section positioning plate 19 is provided with multiple front annular section positioning plate vent 19-2 arranged along its axial direction. The support base plate 21 is provided with multiple support base plate vent 21-1 arranged along its axial direction. When welding shielding gas is input, it passes through the support base plate vent 21-1, the front annular section positioning plate vent 19-2, the front annular section fan-shaped support plate vent 18-2, and the front annular section flow ring vent 17-1 in sequence.

[0063] In this embodiment: when the welding shielding gas is input, it passes sequentially through the air holes of the support base plate, the air holes of the front ring positioning plate, the air holes of the front ring fan-shaped support plate, and the air holes of the front ring flow ring. The welding shielding gas is argon.

[0064] Other implementation methods are the same as those in Specific Implementation Method 3.

[0065] Specific implementation method six: An assembly tool for preventing deformation during welding of gas turbine flame tube, wherein the upper external support assembly includes nut two 5, positioning cone sleeve 7, turbulence section cover plate 8, turbulence section support plate, turbulence section positioning disc 11, and gasket three 12.

[0066] The positioning cone sleeve 7, the spoiler section cover plate 8, the spoiler section support plate, the spoiler section positioning disc 11, and the gasket 3 12 are all arranged coaxially with the support mandrel 3;

[0067] The gasket 3 12 is located above the step of the support mandrel 3. The spoiler section positioning plate 11 is set on the gasket 3 12. The top of the spoiler section positioning plate 11 is integrally provided with multiple concentrically arranged spoiler section guide protrusions 11-1. The spoiler section support plate includes multiple spoiler section fan-shaped support plates 10. The inner ring of each spoiler section fan-shaped support plate 10 is provided with a slope that slopes from top to bottom towards the center. The multiple spoiler section fan-shaped support plates 10 are arranged above the spoiler section positioning plate 11. Each spoiler section fan-shaped support plate 10 is set between two adjacent spoiler section guide protrusions 11-1. The spoiler section cover plate 8 is set above the multiple spoiler section guide protrusions 11-1 and the spoiler section cover plate 8 is connected to each spoiler section guide protrusion. Ridge 11-1 is also connected and fixed by multiple sets of positioning components. The bottom of the positioning cone sleeve 7 is inverted cone-shaped. The positioning cone sleeve 7 is fitted on the support mandrel 3. Nut 2 5 is located on the positioning cone sleeve 7 and is threadedly connected to the support mandrel 3. In the initial state, the positioning cone sleeve 7 is located above the inner ring of the turbulence section support plate. The upper part of the turbulence section of the gas turbine flame tube and the lower part of the cooling section of the gas turbine flame tube are fitted on the outer wall of the turbulence section support plate. During the tightening of nut 2 5, the positioning cone sleeve 7 presses against the slope of multiple turbulence section fan-shaped support plates 10, causing multiple turbulence section fan-shaped support plates 10 to move outward. The multiple turbulence section fan-shaped support plates 10 open up the upper part of the turbulence section of the gas turbine flame tube and the lower part of the cooling section of the gas turbine flame tube.

[0068] In this embodiment: during the tightening of the second nut, the positioning cone sleeve presses against the slope of the multiple turbulence section fan-shaped support plates, causing the multiple turbulence section fan-shaped support plates to move outward. The multiple turbulence section fan-shaped support plates open up the upper part of the turbulence section and the lower part of the cooling section of the gas turbine flame tube to form a circle.

[0069] Other implementation methods are the same as those in Specific Implementation Method 3.

[0070] Specific implementation method seven: An assembly tool for preventing deformation during welding of gas turbine flame tubes, wherein a washer four six is ​​provided between nut two 5 and positioning cone sleeve 7.

[0071] Other implementation methods are the same as those in Specific Implementation Method 1.

[0072] Specific implementation method eight: An assembly tool for preventing deformation during welding of gas turbine flame tubes, wherein the positioning component includes a cylindrical pin 24 and a plurality of positioning bolts 23;

[0073] The front ring section cover plate 16 and each front ring section guide protrusion 19-1 are limited by a cylindrical pin 24, and the two are connected and fixed by multiple positioning bolts 23. A gasket 22 is installed between the positioning bolt 23 and the top surface of the front ring section cover plate 16.

[0074] The spoiler section cover plate 8 and each spoiler section guide protrusion 11-1 are limited by a cylindrical pin 24, and the two are connected and fixed by multiple positioning bolts 23. A gasket 22 is installed between the positioning bolt 23 and the top surface of the spoiler section cover plate 8.

[0075] Other implementation methods are the same as those in Specific Implementation Method Six.

[0076] Specific Embodiment Nine: An assembly fixture for preventing deformation during welding of a gas turbine flame tube, wherein the side wall of the turbulence section fan-shaped support plate 10 is provided with a turbulence section fan-shaped support plate annular groove 10-1. A turbulence section flow ring 9 is embedded in the turbulence section fan-shaped support plate 10, and the turbulence section flow ring 9 is provided with multiple turbulence section flow ring vents 9-1 arranged radially thereon. The turbulence section fan-shaped support plate 10 is provided with turbulence section fan-shaped support plate vents 10-2 connecting its top surface to the turbulence section fan-shaped support plate annular groove 10-1. The turbulence section cover plate 8 is provided with multiple turbulence section cover plate vents 8-1 arranged axially thereon. The upper pressure plate 1 is provided with multiple upper pressure plate vents 1-1 arranged axially thereon. When welding shielding gas is input, it passes sequentially through the upper pressure plate vents 1-1, the turbulence section cover plate vents 8-1, the turbulence section fan-shaped support plate vents 10-2, and the turbulence section flow ring vents 9-1.

[0077] In this embodiment: when the welding shielding gas is input, it passes through the upper pressure plate vent, the turbulence section cover plate vent, the turbulence section fan-shaped support plate vent, and the turbulence section flow ring vent in sequence. The welding shielding gas is argon.

[0078] Other implementation methods are the same as those in Specific Implementation Method Six.

[0079] Specific Implementation Method 10: A method for using an assembly fixture to prevent deformation during welding of a gas turbine flame tube, comprising the following steps:

[0080] Step 1: Place the support base plate 21 on the support platform, then place the front annular section of the gas turbine flame tube onto the chamfered boss of the support base plate 21. Distribute multiple spacer blocks 20 evenly on the upper surface of the support base plate 21. Place the front annular section positioning plate 19 onto the spacer blocks 20. Place multiple front annular section fan-shaped support plates 18 onto the front annular section positioning plate 19, and install the front annular section cover plate 16. Place the conical sleeve 15 onto the support mandrel 3 of the support base plate 21. At this point, the conical sleeve 15 should just be inserted into the support mandrel 3 of the support base plate 21. In the circular hole formed by the front annular support plate 18, the turbulence section of the gas turbine flame tube is placed on the front annular section of the gas turbine flame tube. Nut 13 and washer 14 are assembled. Using socket wrench II 26, nut 13 is tightened, causing the conical sleeve 15 to move downwards until the front annular section and the turbulence section of the gas turbine flame tube are stretched into a circle. The positioning bolt 23 is installed and tightened. After the front annular cover plate 16 and the front annular guide ridge 19-1 are firmly connected, the positions of the multiple front annular support plates 18 are determined.

[0081] Step 2: Place the gasket 3 12, place the turbulence section positioning plate 11 on the gasket 3 12, place multiple turbulence section fan-shaped support plates 10 on the turbulence section positioning plate 11, and install the turbulence section cover plate 8. Then place the cooling section of the gas turbine flame tube on the turbulence section of the gas turbine flame tube, put the positioning cone sleeve 7 on the support mandrel 3, and at the same time install the upper pressure plate 1. First, use the socket wrench I 25 to tighten the nut II 5 until the turbulence section and the cooling section of the gas turbine flame tube are stretched into a circle. Then tighten the large nut 4 to make the contact end faces of the front ring section, the turbulence section and the cooling section of the gas turbine flame tube fit tightly.

[0082] Step 3: Inject argon gas into the tooling through the upper pressure plate vent 1-1 and the support base plate vent 21-1 of the upper pressure plate 1 and the support base plate 21.

[0083] Argon gas enters the cavity at the welded joint of the gas turbine flame tube by passing sequentially through the upper pressure plate vent 1-1, the turbulence section cover plate vent 8-1, the turbulence section fan-shaped support plate vent 10-2, and the turbulence section flow ring vent 9-1, thus isolating the air.

[0084] Argon gas enters the cavity at the welded joint of the gas turbine flame tube by passing sequentially through the support base plate vent 21-1, the front ring section positioning plate vent 19-2, the front ring section fan-shaped support plate vent 18-2, and the front ring section flow ring vent 17-1, thus isolating the air.

[0085] Step 4: After the welding has completely cooled, remove the large nut 4 and the upper pressure plate 1, then remove the second nut 5 and remove all the workpieces of the upper external support assembly, then remove the first nut 13 and remove all the workpieces of the lower external support assembly, and finally remove the welded gas turbine flame tube.

[0086] Working principle:

[0087] The flame tube consists of three sections: a front annular section, a turbulence section, and a cooling section. The front annular section and the cooling section are made by rolling thin plates into cylindrical shapes and then welding them into cylindrical tubes. The turbulence section is made by rolling thin plates into conical tubes and then welding them into conical tubes. When each section is rolled and welded into a tube shape, the two end faces are not regular circles but approximately elliptical. This cannot ensure that the docking ports of the front annular section and the turbulence section, as well as the turbulence section and the cooling section, are completely aligned. Therefore, this tooling is required to correct the end faces of each section to be circular and accurately dock them, and to ensure that no deformation occurs when the joints of each section are welded with argon arc welding.

Claims

1. An assembly fixture for preventing deformation during welding of gas turbine flame tubes, characterized in that: It includes an upper pressure plate (1), a large nut (4), a support mandrel (3), a support base plate (21), a lower external support assembly, and an upper external support assembly; The lower end of the support spindle (3) is fixed to the middle of the support base plate (21). The lower outer support assembly and the upper outer support assembly are installed on the support spindle (3) in sequence from bottom to top and are arranged coaxially with the support spindle (3). The upper pressure plate (1) is fitted on the upper part of the upper outer support assembly. The large nut (4) is located above the upper pressure plate (1) and is threaded to the support spindle (3). When the gas turbine flame tube is installed, the lower part of the front ring section of the gas turbine flame tube is fitted on the boss of the support base plate (21). The upper part of the front ring section of the gas turbine flame tube and the lower part of the turbulence section of the gas turbine flame tube are fitted on the outer support section of the lower outer support assembly. The upper part of the turbulence section of the gas turbine flame tube and the lower part of the rear ring section of the gas turbine flame tube are fitted on the outer support section of the upper outer support assembly. The upper part of the rear ring section of the gas turbine flame tube is fitted on the boss of the upper pressure plate (1). The lower external support assembly includes a nut (13), a tapered sleeve (15), a front ring section cover plate (16), a front ring section positioning plate (19), a pad (20), and a front ring section support plate; The conical sleeve (15), the front ring section cover plate (16), the front ring section positioning plate (19), the pad block (20) and the front ring section support plate are all arranged coaxially with the support mandrel (3); A pad (20) is arranged on a support base plate (21), and a front ring section positioning plate (19) is set on the pad (20). The top of the front ring section positioning plate (19) is integrally provided with multiple concentrically arranged front ring section guide ridges (19-1). The front ring section support plate includes multiple front ring section fan-shaped support plates (18). The inner ring of each front ring section fan-shaped support plate (18) is provided with a slope that slopes from top to bottom towards the center. The multiple front ring section fan-shaped support plates (18) are arranged above the front ring section positioning plate (19). Each front ring section fan-shaped support plate (18) is set between two adjacent front ring section guide ridges (19-1). The front ring section cover plate (16) is set above the multiple front ring section guide ridges (19-1) and the front ring section cover plate (16) is connected to each front ring section guide ridge. The convex rib (19-1) is connected and fixed by multiple sets of positioning components. The bottom of the conical sleeve (15) is inverted conical. The conical sleeve (15) is fitted on the support mandrel (3). Nut 1 (13) is located above the conical sleeve (15) and is threadedly connected to the support mandrel (3). In the initial state, the conical sleeve (15) is located above the inner ring of the front ring support plate. The upper part of the front ring section of the gas turbine flame tube and the lower part of the turbulence section of the gas turbine flame tube are fitted on the outer wall of the front ring support plate. During the tightening of nut 1 (13), the conical sleeve (15) presses against the slope of multiple front ring section fan-shaped support plates (18) to make multiple front ring section fan-shaped support plates (18) move outward. Multiple front ring section fan-shaped support plates (18) open the upper part of the front ring section of the gas turbine flame tube and the lower part of the turbulence section of the gas turbine flame tube. The upper external support assembly includes nut two (5), positioning cone sleeve (7), turbulence section cover plate (8), turbulence section support plate, turbulence section positioning disc (11), and gasket three (12). The positioning cone sleeve (7), the spoiler section cover plate (8), the spoiler section support plate, the spoiler section positioning disc (11), and the gasket three (12) are all arranged coaxially with the support mandrel (3); The gasket three (12) is located above the step of the support mandrel (3). The spoiler section positioning plate (11) is set on the gasket three (12). The top of the spoiler section positioning plate (11) is integrally provided with multiple centripetally arranged spoiler section guide ridges (11-1). The spoiler section support plate includes multiple spoiler section fan-shaped support plates (10). The inner ring of each spoiler section fan-shaped support plate (10) is provided with a slope that slopes from top to bottom towards the center. The multiple spoiler section fan-shaped support plates (10) are arranged above the spoiler section positioning plate (11). Each spoiler section fan-shaped support plate (10) is set between two adjacent spoiler section guide ridges (11-1). The spoiler section cover plate (8) is set above the multiple spoiler section guide ridges (11-1) and the spoiler section cover plate (8) is connected to each spoiler section guide ridge. The convex rib (11-1) is also connected and fixed by multiple sets of positioning components. The bottom of the positioning cone sleeve (7) is inverted cone-shaped. The positioning cone sleeve (7) is fitted on the support mandrel (3). Nut 2 (5) is located on the positioning cone sleeve (7) and threadedly connected to the support mandrel (3). In the initial state, the positioning cone sleeve (7) is located above the inner ring of the turbulence section support plate. The upper part of the turbulence section of the gas turbine flame tube and the lower part of the cooling section of the gas turbine flame tube are fitted on the outer wall of the turbulence section support plate. During the tightening of nut 2 (5), the positioning cone sleeve (7) presses against the slope of multiple turbulence section fan-shaped support plates (10) to move the multiple turbulence section fan-shaped support plates (10) outward. The multiple turbulence section fan-shaped support plates (10) open the upper part of the turbulence section of the gas turbine flame tube and the lower part of the cooling section of the gas turbine flame tube.

2. The assembly fixture for preventing deformation during welding of gas turbine flame tubes according to claim 1, characterized in that: A washer five (2) is provided between the upper pressure plate (1) and the large nut (4).

3. The assembly fixture for preventing deformation during welding of gas turbine flame tubes according to claim 1, characterized in that: A washer (14) is provided between nut (13) and tapered sleeve (15).

4. The assembly fixture for preventing deformation during welding of gas turbine flame tubes according to claim 1, characterized in that: The front annular sector support plate (18) has a front annular sector support plate groove (18-1) in the middle of its side wall. A front annular flow ring (17) is embedded in the front annular sector support plate groove (18-1). The front annular flow ring (17) has a plurality of front annular flow ring vents (17-1) arranged radially thereon. The front annular sector support plate (18) has a front annular sector support plate groove (18-1) that connects its bottom end face to the front annular sector support plate groove (18-1). The support plate has air holes (18-2), and the front ring section positioning plate (19) has multiple air holes (19-2) arranged along its axial direction. The support base plate (21) has multiple support base plate air holes (21-1) arranged along its axial direction. When the welding shielding gas is input, it passes through the support base plate air holes (21-1), the front ring section positioning plate air holes (19-2), the front ring section fan-shaped support plate air holes (18-2), and the front ring section flow ring air holes (17-1) in sequence.

5. The assembly tooling for preventing deformation during welding of gas turbine flame tubes according to claim 1, characterized in that: A washer (6) is provided between nut two (5) and positioning cone sleeve (7).

6. The assembly fixture for preventing deformation during welding of gas turbine flame tubes according to claim 1, characterized in that: The positioning assembly includes a cylindrical pin (24) and a plurality of positioning bolts (23). The front ring section cover plate (16) and each front ring section guide protrusion (19-1) are limited by a cylindrical pin (24), and the two are connected and fixed by multiple positioning bolts (23). A gasket (22) is installed between the positioning bolt (23) and the top surface of the front ring section cover plate (16). The spoiler section cover plate (8) and each spoiler section guide protrusion (11-1) are limited by a cylindrical pin (24), and the two are connected and fixed by multiple positioning bolts (23). A gasket (22) is installed between the positioning bolt (23) and the top surface of the spoiler section cover plate (8).

7. The assembly tooling for preventing deformation during welding of gas turbine flame tubes according to claim 1, characterized in that: The side wall of the turbulence section fan-shaped support plate (10) is provided with a turbulence section fan-shaped support plate annular groove (10-1). The turbulence section fan-shaped support plate (10) is embedded with a turbulence section flow ring (9). The turbulence section flow ring (9) is provided with a plurality of turbulence section flow ring air holes (9-1) arranged radially thereon. The turbulence section fan-shaped support plate (10) is provided with a turbulence section annular groove (10-1) that connects its top surface to the turbulence section fan-shaped support plate annular groove (10-1). The fan-shaped support plate has air holes (10-2), and the turbulence section cover plate (8) has multiple turbulence section cover plate air holes (8-1) arranged along its axis. The upper pressure plate (1) has multiple upper pressure plate air holes (1-1) arranged along its axis. When the welding shielding gas is input, it passes through the upper pressure plate air holes (1-1), the turbulence section cover plate air holes (8-1), the turbulence section fan-shaped support plate air holes (10-2), and the turbulence section flow ring air holes (9-1) in sequence.

8. The method of using the assembly tooling according to any one of claims 1-7; characterized in that: It includes the following steps: Step 1: Place the support base plate (21) on the support platform, then put the front ring section of the gas turbine flame tube onto the chamfered boss of the support base plate (21). Distribute multiple pads (20) evenly on the upper surface of the support base plate (21), place the front ring section positioning plate (19) on the pads (20), place multiple front ring section fan-shaped support plates (18) on the front ring section positioning plate (19), and install the front ring section cover plate (16). Put the conical sleeve (15) onto the support mandrel (3) of the support base plate (21). At this time, the conical sleeve (15) is just inserted. The gas turbine flame tube is placed in the circular hole formed by multiple front ring support plates (18). The turbulence section of the gas turbine flame tube is then placed on the front ring section of the gas turbine flame tube. Nut 1 (13) and washer 1 (14) are assembled. The nut 1 (13) is tightened with socket wrench II (26), which drives the cone sleeve (15) to move downward until the front ring section and the turbulence section of the gas turbine flame tube are stretched into a circle. The positioning bolt (23) is installed and tightened. After the front ring cover plate (16) and the front ring guide ridge (19-1) are firmly connected, the position of the multiple front ring support plates (18) is determined. Step 2: Place the gasket three (12), place the turbulence section positioning plate (11) on the gasket three (12), place multiple turbulence section fan-shaped support plates (10) on the turbulence section positioning plate (11), and install the turbulence section cover plate (8). Then place the cooling section of the gas turbine flame tube on the turbulence section of the gas turbine flame tube, put the positioning cone sleeve (7) on the support mandrel (3), and at the same time install the upper pressure plate (1). First, use the socket wrench I (25) to tighten the nut two (5) until the turbulence section and the cooling section of the gas turbine flame tube are stretched into a circle. Then tighten the large nut (4) to make the contact end faces of the front ring section of the gas turbine flame tube, the turbulence section of the gas turbine flame tube and the cooling section of the gas turbine flame tube close together. Step 3: Inject argon gas into the tooling through the upper pressure plate vent (1-1) of the upper pressure plate (1) and the support base plate vent (21-1) of the support base plate (21). Argon gas enters the cavity at the welded joint of the gas turbine flame tube by passing sequentially through the upper pressure plate vent (1-1), the turbulence section cover plate vent (8-1), the turbulence section fan-shaped support plate vent (10-2), and the turbulence section flow ring vent (9-1), thus isolating the air. Argon gas enters the cavity at the welded joint of the gas turbine flame tube by passing through the air holes (21-1) of the support base plate, the air holes (19-2) of the front ring positioning plate, the air holes (18-2) of the front ring sector support plate, and the air holes (17-1) of the front ring flow ring in sequence, thus isolating the air. Step 4: After the welding has completely cooled down, remove the large nut (4) and the upper pressure plate (1), then remove the second nut (5), and then remove the various parts of the upper external support assembly. After removing the first nut (13), remove the various parts of the lower external support assembly, and finally remove the welded gas turbine flame tube.

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