Some standard content:
National Standard of the People's Republic of China
Assembly technical specification for gas turbine assembly
Assembly technical specification for gas turbine1 Subject content and scope of application
This standard specifies the technical requirements for the compressor, combustion chamber and turbine of a gas turbine in the assembly. GB/T 14793-93
This standard is applicable to fixed or box-mounted gas turbines for power generation, and other types of gas turbines may refer to it. 2 Cylinders
For compressor cylinders or turbine cylinders connected by several cylinder sections, and cylinders in which compressor cylinders and turbine cylinders are connected together, the cylinders should be assembled using the vertical centering method. 2.1 Before assembling each cylinder section, burrs and dirt should be removed from its assembly joint surface and bolt holes. 2.2 When the cylinder sections are connected by the horizontal center plane (Figure 1a) or the vertical center plane (Figure 1b) and fastened with bolts, on the horizontal center plane, the bolts should be tightened from the middle and then alternately to both sides. On the vertical center plane, the bolts should be tightened alternately symmetrically with the center as the center. 2.3 During the assembly process, process bolts and nuts that need to be assembled and disassembled multiple times should be used. Anti-seizure agent should be applied to all threaded surfaces. 2.4 Turbine Cylinder and Turbine Exhaust Cylinder
2.4.1 Place the turbine cylinder on the installation platform with the exhaust side flange facing upward and place the turbine exhaust cylinder on the turbine cylinder. Take the inner gas seal of the turbine exhaust cylinder or the surface that can represent the center of the exhaust cylinder as the reference to find the inner surface of the last stage compound ring of the turbine exhaust cylinder (or the surface that can represent the center of the turbine cylinder). The deviation of the corresponding point is not more than 0.05mm, see Figure 2 and Figure 3. 2.4.2 For the two cylinder bodies that have passed the inspection after alignment, all bolts should be tightened in time according to the design requirements (according to the order specified in Figure 1) and the positioning pins should be driven.
hVertical center plane
Horizontal center plane
Figure 1 Tightening sequence of cylinder fastening bolts
Approved by the State Administration of Technical Supervision on December 28, 1993 and implemented on October 1, 1994
Turbine exhaust cylinder
One end flange
GB/T 14793-93
White dividing table
Flat camera red inner gas seal ring
Cylinder body center line
Figure 2 Turbine cylinder and exhaust cylinder alignment
Water sub-center plane
Figure 3 Cylinder centering measurement point position
2.4.3 Assembly requirements for turbine cylinder and its double ring 2.4.3.1 The intake side flange of the turbine cylinder faces upward, and the end face circular runout of eight points evenly distributed on the flange end face is measured to be no more than 0.05mm. 2.4.3.2 For the structure with double rings in the turbine cylinder, the radial circular runout of the six points on the inner surface of the technical double ring in the cylinder is no more than 0.25mm. The difference in runout between two points at 180 degrees symmetrical position is not more than 0.05mm. 0.05mm (see Figure 3 for the six-point position). 2.4.3.3 The difference in the runout of each level of compound ring at the corresponding entry point shall not exceed 0.13mm, see Figure 3. 2.4.3.4 According to the different initial temperatures of the gas, the gaps between the compound ring blocks and the relative positions of the compound rings at the horizontal center plane of the turbine cylinder shall meet the design requirements, see Figure 4.
Upper half boat compound ring end curve
Avoid half cylinder horizontal center plane
Sealing trace
F flat. Compound ring bounce surface
Relative position of compound ring and gas
Figure 4 Compound ring assembly source and installation position
2.5 Assembly of compressor exhaust cylinder and turbine cylinder. GB/T 14793—93
2.5.1 When the compressor exhaust cylinder is connected to the turbine cylinder, the end face circular runout of the eight points evenly distributed on the end face of the intake side flange of the compressor exhaust cylinder shall not exceed 0.10 mm.
2.5.2 When the compressor exhaust cylinder is connected to the turbine cylinder, the radial circular runout of the inner circle of the compressor exhaust cylinder relative to the inner circle of the turbine cylinder at the installation location of the last stage blade of the compressor and the radial circular runout of the inner circle near the vertical flange on the intake side shall not exceed 0.05 mm, see Figures 3 and 5. 2.5.3 For the structure with an inner cylinder in the compressor exhaust cylinder, the radial circular runout of the inner circle of the inner cylinder at six symmetrical points shall not exceed 0.05 mm, and the positions of the six points are shown in Figure 3.
2.5.4 The radial circular runout of the six symmetrical points of the inner circle of the support ring installed on the compressor exhaust cylinder for supporting the turbine nozzle shall not exceed 0.10 mm.
Dial indicator
Compressor exhaust
Figure 5 Vertical centering of turbine cylinder and compressor exhaust cylinder2.6 Assembly of compressor cylinder middle section and compressor exhaust cylinder2.6.1 When compressor cylinder and compressor exhaust cylinder are connected, the circular runout of the vertical flange end face of the compressor cylinder on the intake side shall not exceed 10mm.
2.6.2 The radial circular runout of the six symmetrical points of the inner circle of the compressor cylinder shall not exceed 0.05mm. The positions of the six points are shown in Figures 3 and 6.2.6.3 For compressor cylinders with exhaust grooves, the width of the exhaust grooves shall be measured and must meet the design requirements. Compressor cylinder
Dial indicator
Gas probe
Eastern gas machine support cylinder
Figure 6 Compressor cylinder and compressor exhaust chain vertical alignment GB/T 14793-93
2.7 When connecting each section of the cylinder body, sealant should be applied to the vertical center plane (a section about 25tmml close to the horizontal center plane). 2.8 After assembling and connecting each section of the cylinder, the bolts should be tightened in time according to the design requirements and the positioning pins should be installed. The threads should be coated with anti-seizure agent. 2.9 When tightening the bolts, there should be no jamming. 2.10 When tightening the cylinder bolts, according to the specifications and materials of the bolts, the bolt torque should meet the design requirements. 2.11 The sealing inspection of the center plane of each section of the cylinder should meet the design requirements. 3 Bearings
3.1 All bearing parts should be deburred before assembly, and the surface impurities and dirt of the housing should be completely removed. 3.2 Check the dimensions of the bearing shell and the journal. Measure and record the roundness. 3.3 The thickness difference of the vertical or horizontal adjustment plate should not exceed 0.025mm. 3.4 The clearance between the lug of the radial bearing seat installed on the turbine cylinder and its pressure plate should not exceed 0.025mm, see Figure 7. S00
Bearing seat lug
Adjustment piece
Figure 7 Turbine side radial bearing seat lug fixing clearance 3.5 The clearance on both sides between the bearing seat guide key of the radial bearing and the keyway on the cylinder body, that is, a + b shall not be greater than 0.03mm, see Figure 8. Bearing seat guide chain
Adjustment piece
Red body chain groove
Figure 8 Assembly of bearing seat guide key and cylinder body
3.6 For gas turbines with flexible rotors, the shaft neck needs to be appropriately raised, and the height of (one end or the other end) relative to the center line of the unit should meet the design requirements.
3.7 After all the bearings are installed, the main thrust surface must be pressed against the main thrust pad, and the rotor must be rotated to check the radial distance of the first-stage moving blade tip. Three points should be checked in the upper and lower halves, of which two points are close to the horizontal center plane. The reading difference between the upper and lower points and the reading difference between the left and right points should meet the design requirements, as shown in Figure 3.
3.8 Rotate the flexible rotor to check the runout of the turbine's last-stage moving blade relative to the cylinder inner diameter. The reading difference between the upper and lower points should meet the design requirements.
3.9 For rotors with requirements for raising the rotor journal, the inclination of the journal in the bearing should meet the design requirements. 3.10 Check that the contact length between the bearing and the journal in the bearing without raising the rotor journal should not be less than 80% of the bearing length. 4 Stationary blades
GB/T14793—93
4.1 Before assembling the stationary blades, the part code must be checked and the spectrum must be checked, and the stationary blades must be checked according to the design requirements. 4.2 Check the blade surface. There must be no surface defects such as scratches and abrasions. 4.3 Before assembling the static blades, the installation grooves of the static blades must be strictly cleaned, but the blade roots are not allowed to be repaired by filing. 4.4 During assembly, identify the inlet and outlet directions of the blades. 4.5 Assembly of compressor static blades
4.5.1 After the static blades are assembled, the root (including the static blade assembly with static blade root ring) should be no higher (lower) than the inner surface of the cylinder by no more than 0.25 mm.
4.5.2 After the static blades are assembled, the root (including the static blade root ring) should be lower than the horizontal center plane of the cylinder and no more than 0.3 mm. 4.5.3 The installation angle and pitch of the static blades should be inspected according to the design requirements and recorded in detail. 4.5.4 For the static blade assembly with blade roots installed in the cylinder, the cumulative value of the gap between the end faces of each ring shall not exceed 2.0 mm. 4.5.5 The requirement that the stationary blade (including the stationary blade assembly) is lower than the horizontal center plane of the cylinder can be achieved by adding a gasket (or grinding the root end face of the blade), but the gasket shall not be added between the first and second blades close to the horizontal center plane, the thickness of the gasket shall not exceed 1.5mm, the number shall not exceed 1, and the root end face of the blade other than the first blade under the horizontal center plane shall be ground, and the grinding of both sides shall be equal and shall not exceed 1.5mm. 4.6 Assembly of adjustable stationary blades
4.6.1 When installing the adjustable stator blade into the compressor cylinder, turn the blade by hand. It should turn smoothly without any jamming. 4.6.2 The pointer reading error of the adjustable stator blade's rotation angle should be controlled within ±0.5\. 4.6.3 The limit angle position of the adjustable stator blade should meet the design requirements. 4.6.4 When measuring the radial clearance of the adjustable stator blade, the blade should be at the angle position specified in the design, see Figure 9.
Adjustable stator blade
Figure 9 Assembly of adjustable stator blade
4.7 Assembly of stator blade
4.7.1 For blades with coating, the coating should not peel off. 4.7.2 For blades with cooling measures, all cooling holes must be kept unobstructed. 4.7.3 For stator components that need to be welded during assembly, the welds must not block the gaps between the components. 4.7.4 Between each stator blade component, there must be enough gap for thermal expansion. 4.7.5 In the structure with inner cylinder or compound ring, the coaxiality between the stator and the inner cylinder or between the stator and the compound ring shall not exceed 0.25mm. 4.7.6 When the stator is installed in the cylinder, the gap between the pressure plate and the ring that fixes the stator ring shall meet the design requirements, see Figure 10 GB/T 14793-93
First-stage stator assembly upper halfbzxZ.net
First-stage stator assembly lower half
Complete block
Figure 10 Installation of stator assembly
4.7.7 The installation angle and pitch of the stator shall be tested according to the design requirements and recorded in detail. 5 Compressor rotor
5.1 Assembly of compressor moving blades
Upper half of turbine cylinder
Flat cylinder half
51.1 All compressor moving blades shall be spectrally inspected before assembly, and the static frequency shall be checked and the blade top shall be rubbed according to the design requirements. 5.1.2 All outsourced (purchased) blades should be inspected by non-destructive testing. 5.1.3 There should be no scratches or damage on the blade surface. 5.1.4 During assembly, the working surface of the blade root or impeller groove shall not be repaired. 5.1.5 A gap is allowed between the bottom surface of the blade root and the bottom surface of the impeller groove. 5.1.6 The end surface of the blade root and the end surface of the wheel rim should be flush with each other, and the error should not exceed 0.15mm. 5.1.7 For the moving blades with dovetail blade roots, the axial movement should not exceed 0.1mm. 5.1.8 The torque of each stage of the moving blades on the rotating shaft should be measured and accurately recorded according to the number. During assembly, blades with equal or similar torques should be installed in symmetrical positions.
5.1.9 During assembly, identify the inlet and outlet directions of the impeller and blades. 5.2 Assembly of compressor rotor
5.2.1 The single impeller with compressor impeller installed shall be dynamically balanced with an accuracy of G6.3. After de-weighting, the heavy (or light) parts shall be marked. The de-weighting parts and methods shall not affect the strength of the impeller. 5.2.2 For drum rotors, all parts outside the impeller shall be weighed and numbered. When assembling, parts with the same (or similar) mass shall be placed in symmetrical positions.
5.2.3 For drum rotors, the relative positions of each impeller shall be configured according to the residual unbalance of a single impeller to reduce the initial residual unbalance of the rotor assembly.
5.2.4 When assembling the rotor assembly, the alignment requirements between the impellers shall be ensured; for rotor assemblies with circumferential tie rod bolts, in order to make the tie rod bolts at each symmetrical position bear equal force, the order of tightening (tensioning) the tie rod bolts shall be carried out according to Figure 11. GB/T 14793—93
Figure 11 Sequence of tightening the tie rod bolts
5.2.5 The tie rod bolts should not be stuck in the holes of each impeller. 5.2.6 The pre-tightening force of the tightening bolts should meet the design requirements. The nuts on the rotor should be prevented from loosening. 5.2.7 For the disc-drum compressor rotor after assembly, the clearance between the impellers at the wheel rim should meet the design requirements, and the clearance deviation should not be less than 0.05 mm. See Figure 12
For the center stop
Rotor (impeller centerline)
Figure 12 Fit between the impellers of the compressor rotor
5.2.8 The runout inspection of the assembled compressor rotor in Figure 13 should meet the requirements of Table 1. The position is shown in Figure 13. Table 1
Radial circular motion
End circular motion
Inspection of compressor rotor runout
GB/T14793-93
Figure 13 Schematic diagram of compressor rotor runout inspection5.2.9 The dynamic balancing accuracy of the compressor rotor shall be G2.5. When the initial unbalance is too large, the rotor shall be reassembled. 6 Turbine rotor
6.1 Assembly of turbine moving blades
6.1.1 Before assembly, all turbine moving blades shall be inspected, and the static frequency shall be checked and the blade tip shall be ground according to the design requirements. 6.1.2 Non-destructive testing shall be performed on all outsourced (purchased) blades. 6.1.3 Turbine moving blades shall not have surface defects such as scratches, damage and coating shedding. 6.1.4 Turbine moving blade teeth shall not be repaired. 6.1.5 Ensure that there is a gap between the roots of each moving blade, and the gap value should meet the design requirements. 6.1.6 The moving blades should be in a loose state after assembly, and their tangential swing and radial outward displacement should meet the design requirements. 6.1.7 After the moving blades are assembled and locked, their axial motion is not greater than 0.20mm. 6.1.8 The parts used to lock the moving blades are only allowed to be used once. 6.1.9 Measure the torque of all blades on the rotating shaft and record the serial numbers. When assembling, place the blades with the same (or similar) torque in symmetrical positions.
0 When assembling, the inlet and outlet directions of the impeller and blades should be identified. 6.1.10
6.2 Assembly of the lower rotor
.6.2.1 The impeller with installed blades needs to be dynamically balanced, and its accuracy should be in accordance with G6.3 level. The weight removal parts and methods should not affect the strength of the impeller. The heavy (or light) parts should be marked, and the relative position of the impeller should be reasonably configured according to the residual imbalance. 6.2.2 The parts other than the impeller should be weighed and numbered. When assembling, the parts with the most equal (or similar) mass should be placed in symmetrical positions. 6.2.3 The impeller assembly should be based on interference fit and centering. The impeller must be heated evenly without overburning, and the blades should be protected. 6.2.4 The centering requirements between the impellers should be ensured. For the structure with bolt tensioning, the bolts should not be stuck. 6.2.5 Bolts should be used. For the tensioned structure, the nuts should be tightened in the order shown in Figure 14, and the bolt preload should meet the design requirements. Figure 14 Tightening sequence of turbine rotor bolts
6.2.6 The nuts on the rotor should be prevented from loosening. GB/T14793—93
6.2.7 The runout inspection of the assembled turbine rotor should meet the requirements of Table 2, and the position is shown in Figure 15. Table 2 Turbine rotor runout inspection
Radial circular runout
End circular runout
Figure 15 Schematic diagram of turbine rotor runout inspection6
6.2.8 Turbine rotor The dynamic balancing accuracy is G2.5. When the initial unbalance is too large, the rotor should be reassembled. 7 Assembly of gas turbine rotor assembly
7.1 Before assembly, check the runout and residual unbalance records of the compressor rotor and turbine rotor of the assembly, and the values should meet the design requirements.
7.2 The fastening parts in the rotor assembly should be weighed and numbered. During assembly, put parts of the same (or similar) mass in symmetrical positions.
7.3 When heating parts during the rotor assembly process, heat them gradually from the center to the rim. The surface must not be overburned, and the blades must be protected.
7.4 The fastening bolts of the rotor assembly must be tightened after the connection parts have cooled to room temperature. The order of tightening the bolts is as shown in Figure 14. The preload force of the bolts should meet the design requirements, and the nuts should be prevented from loosening. 7.5 After the rotor assembly is assembled, the runout can be checked only after it has cooled to room temperature, and detailed records should be made. The runout should meet the requirements of Table 3, and the position is shown in Figure 16.
Rotor assembly runout check
Radial runout
End face runout
0. 01 0. 025
GB/T14793—93
Figure 16 Schematic diagram of dynamic balance inspection of gas turbine rotor assembly 7.6 The joint between the compressor rotor and the turbine rotor should be marked. 7.7 Dynamic balancing of gas turbine rotor assembly
7.7.1 The dynamic balancing accuracy of the rotor core shall be G2.5. If the initial imbalance is too large, the rotor assembly must be disassembled and reassembled. 7.7.2 For long combustion rotors, multi-plane dynamic balancing should be checked. 7.7.3 The dynamic balancing blocks of the compressor rotor, turbine rotor and rotor parts should be marked with different marks. 7.7.4 Parts rigidly connected to the gas turbine rotor assembly should be dynamically balanced together with the rotor assembly. 8 Assembly of combustion transition section
8.1 The center of the transition section connected to the combustion chamber flame tube should deviate from the center line of the combustion chamber by no more than 1.50mm, see Figure 17. Transmission section
Unit vertical center line
Flame quotient
Outside combustion chamber
Single combustion chamber
Transmission section
[Unit horizontal center line
B combustion chamber
B branch combustion chamber
Figure 17 Schematic diagram of the distribution of combustion chambers and the position of the center line of the transition section 8.2 When installing the transition section, one end must not be in a cantilever state. 8.3 There should be a gap between the inlet and outlet end faces of the transition section (single or branch) and the flame tube and the turbine blade ring, and the gap value should meet the design requirements, Figure 18,
8.4 All fastening screws and nuts must be coated with anti-absorption agent and must be prevented from loosening after expansion. First stage stationary blade assembly
Sealing piece
Transition section
Figure 18 Schematic diagram of the gap between the transition section and the stationary blade assembly 9 Assembly of the combustion chamber
GB/T 14793—93
9.1 The deviation between the center line of the fuel nozzle and the center line of the flame tube in the combustion chamber shall meet the design requirements. 9.2 The assembly gap of the cross-flame tube between two combustion cases shall meet the design requirements, see Figure 19. Interval
Figure 15 Assembly of the cross-flame tube
Flame tube
Cross-flame tube
9.3 A gap for thermal expansion shall be left between the flame tube of each combustion case and its cross-flame tube. 9.4 The centering deviation of the center line of the spark plug and the flame detector in the combustion chamber shall meet the design requirements. 9.5 The sealing gasket in the combustion chamber assembly is only allowed to be used once. 10 Requirements before gas turbine rotor is put into cylinder and covered Before the gas turbine rotor is put into cylinder, it must be strictly inspected. No foreign matter is allowed to exist in the cylinder body, and all parts must be clean. 10.1
10.2 Fill lubricating oil under the bearing and rotate the rotor. There should be no abnormal sound or jamming. 10.3 Measure and record the following contents. The measured values should meet the design requirements. a.
Interference (or clearance) of radial bearing pad back: clearance between radial bearing and shaft neck;
After the rotor brush thrust disk surface and the auxiliary thrust pad are in close contact, measure the clearance between the main thrust disk surface and the main thrust pad; the clearance between each gas seal and oil seal;
Radial clearance of compressor moving blade tip;
Radial clearance of compressor stator blade tip,
Radial clearance of turbine moving blade end,
Axial clearance at the root of turbine moving blade
Radial clearance of turbine stator end:
Radial clearance and axial clearance of gas seal teeth in turbine flow section; radial clearance and axial clearance of gas seal teeth in compressor flow section. 11 Support of gas turbine
11.1 The adjusting gaskets of the main support of gas turbine shall include at least 3 sets of different thickness scales, see Figure 20. Hand warmer
Support plate
Adjusting gasket group
GB/T 14793—93
Figure 20 Support of gas turbine
Turbine cylinder
Guide block
11.2 The support locating pins of the unit must be replaced after arriving at the site of use. If any abnormality such as roughening or deformation occurs, the locating pins should be re-matched with the holes.
11.3 When the compressor cylinder is installed on the chassis with a guide key, the clearance between the inlet and outlet cylinder guide key and the chassis is 0.0250.05 mm, see Figure 21.
Compressor cylinder guide key
Figure 21 Compressor guide key assembly
11.4 When the compressor adopts a sliding pin structure, the clearance between the sliding pin and the pin hole should not be less than 0.04 mm, see Figure 22. Cylinder block
Adjusting gasket
Air disc support
Figure 22 Compressor cylinder support
Tightening screw
Compressor cylinder lower flange
Adjusting gasket
Disc support
Adjusting sleeve
11.5 After the tightening screw is pressed on the adjusting bushing, the clearance between the adjusting bushing and the lower surface of the cylinder should meet the design requirements, see Figure 22. 11.6 The radial clearance (41 + 42) between the adjusting bushing and the cylinder support flange should meet the design requirements, see Figure 22.
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