A multi-chamber wiring method for gas turbine guide vane segment inspection

Abstract

The application discloses a kind of multi-chamber wiring methods of gas turbine guide vane section detection, belong to gas turbine technical field.The gas turbine guide vane section is mainly by casing assembly, turbine guide vane assembly and turbine rotor assembly is constituted, and each component cooperation forms cold gas pressurizing chamber, multiple sets of labyrinth separation chamber and guide vane outer separation chamber etc.tight chamber.This method is formulated exclusive wiring scheme to different separation chamber detection probe wire, respectively via corresponding component presetting wire hole uniformly into cold gas pressurizing chamber;Rely on original cold gas passage, guide vane internal passage and various wire holes, via guide vane outer separation chamber, guide vane passage and bolt center hole with hole lead out casing outside.The application does not need to be opened on turbine blade, only rely on original structure of equipment and supplement a small amount of processing can be completed wiring;Wiring process is simple, adapts high-low pressure turbine guide vane under multiple working conditions, can satisfy the detection needs of different types of gas turbine.

Description

Technical Field

[0001] This invention belongs to the field of gas turbine technology, specifically relating to a multi-chamber wiring method for detecting the guide section of a gas turbine. Background Technology

[0002] The turbine guide vane is one of the main components of a gas turbine. At the connection between the turbine guide vane and the turbine rotor, a turbine disk cavity structure is often formed. The turbine disk cavity structure is mainly used to draw the final stage cold air from the compressor, and then pressurize the cold air to cool the high-temperature components such as the turbine disk and rotor blades.

[0003] Patent number ZL2023115767744 discloses a turbine disk cavity structure for a gas turbine, which is located at the junction of the turbine guide vane assembly and the turbine rotor assembly. The turbine disk cavity structure includes an outer sealing channel, an inner sealing channel, and a radial return channel. This design reduces energy loss caused by the mixing of leaked cold air with the main airflow in the gas turbine's main flow path and also allows for the adjustment of the axial force and radial centrifugal force of the turbine rotor assembly.

[0004] However, when testing the gas turbine core engine test piece using the above-mentioned technology, it is necessary to obtain the component performance parameters of different components under different operating conditions in an environment close to that of the entire machine. This is to verify the design results of each high and low pressure component at each guide and the matching relationship between each component, and to verify whether each component has achieved its design goals, providing a basis for further design modifications. This also allows for the verification of the functionality and reliability of the core engine's lubrication system, fuel supply system, control system, and starting system through gas turbine core engine testing. At the same time, the core engine test can be used to explore and verify the control law, starting law, and fuel supply law, laying the foundation for the debugging and integration verification of the entire machine system.

[0005] In order to obtain as much experimental data as possible for performance analysis while ensuring safety, multi-point data acquisition is often required to determine the test parameters of the core engine test. Therefore, it is necessary to design a multi-chamber wiring method for gas turbine guide section testing to realize multi-point data acquisition of gas turbine and safe and reliable wiring in various complex cavities. Summary of the Invention

[0006] To address the aforementioned problems in existing technologies, this solution provides a multi-chamber wiring method for detecting the guide section of a gas turbine.

[0007] The technical solution adopted in this invention is as follows: A multi-chamber wiring method for detecting the guide section of a gas turbine, wherein the guide section of the gas turbine includes a casing assembly, a turbine guide assembly, and a turbine rotor assembly; The turbine rotor assembly includes rotor blades, a front grate disk, and a turbine disk; the front grate disk is disposed on the front side of the turbine disk, and several rotor blades are connected to the outer ring side of the turbine disk; the front grate disk is provided with a fourth grate section, a first grate section, and a second grate section in sequence from the outside to the inside. The turbine guide assembly includes an inner mounting ring, an inner cone ring, and a pre-swirling nozzle ring; The inner mounting ring includes a front ring portion, a first outer ring portion, an inner ring portion, a rear ring portion, and a second outer ring portion. The front ring portion is located in front of the rear ring portion, the first outer ring portion is located outside the connection between the front and rear ring portions, the inner ring portion is located behind the connection between the front and rear ring portions, and the second outer ring portion is located outside the rear end of the rear ring portion. A cold air passage is provided on the outer side of the front ring portion, and the front ring portion is located outside the inner conical ring, forming a cold air pressurization chamber between the two. The rear end of the second outer ring portion is sealed with the fourth grate tooth portion, and the outer side of the fourth grate tooth portion forms a fourth grate tooth partition cavity. Both the first and second outer ring portions are connected to the inner end of the guide vane. The pre-rotating nozzle ring is connected to the rear end of the inner conical ring and includes an annular face and a first sealing part and a second sealing part respectively provided on the outer and middle parts of the annular face. The front grate plate is provided with a first grate part and a second grate part. The first sealing part seals with the first grate part and forms a first grate cavity on the inner side of the first grate part. The second sealing part seals with the second grate part and forms a second grate cavity on the inner side of the second grate part. The casing assembly includes a turbine guide ring, a turbine casing, a combustion chamber rear casing, guide vanes, and perforated bolts; the turbine guide ring is located outside the guide vanes; the turbine guide ring is located inside the rear end of the combustion chamber rear casing, and the two form a guide outer cavity; the turbine casing is fixed to the inner rear end of the combustion chamber rear casing and is sealed with the rotor blade grates; the inner end of the guide vanes is connected to the turbine casing, and the outer end is connected to the outer rear end of the combustion chamber rear casing through perforated bolts; Multi-chamber wiring methods include: S1: The wire connected to the detection probe in the fourth sieve cavity is introduced into the cold air pressurization chamber through the third wire hole opened on the second outer ring and the first wire hole opened at the connection between the front ring and the rear ring. S2: The wire connected to the detection probe in the first toothed cavity is introduced into the cold air pressurization cavity through the fifth wire hole on the annular part and the second wire hole on the inner ring. S3: The wire connected to the detection probe in the second sieve cavity is introduced into the cold air pressurization cavity through the sixth wire hole on the annular part and the second wire hole on the inner ring. S4: The wire introduced into the cold air booster chamber in steps S1-S3 passes through the cold air inlet on the front ring, the cold air passage, the fourth wire hole opened on the first outer ring, the internal passage of the guide vane, the seventh wire hole opened on the outer end plate of the guide vane, the through hole on the outer ring of the turbine guide vane, the outer cavity of the guide vane, the eighth wire hole opened on the turbine casing, the passage inside the guide vane, and the center hole of the bolt with holes, and is led out to the outside of the combustion chamber rear casing.

[0008] Optionally: The inner ring side of the pre-swirl nozzle ring is provided with a nozzle ring cavity; a rear flange is provided at the rear of the inner cone ring, and an axial air hole is provided on the rear flange; the wire connected to the detection probe in the nozzle ring cavity is introduced into the cold air boosting chamber through the axial air hole; and led out to the outside of the combustion chamber rear casing according to step S4.

[0009] Optional: Four detection probes are evenly distributed inside the nozzle annular cavity.

[0010] Optional: The wire connected to the detection probe in the cold air booster chamber is led out to the outside of the combustion chamber rear casing according to step S4.

[0011] Optional: The wire connected to the detection probe in the outer cavity of the guide vane is led out to the outside of the combustion chamber rear casing through the eighth wire hole opened on the turbine casing, the channel inside the guide vane, and the center hole of the bolt with holes.

[0012] Optional: An outer cavity is formed between the outer ring of the turbine guide vane and the guide vane; the wire connected to the detection probe in the outer cavity is introduced into the outer cavity of the guide vane through another through hole on the outer ring of the turbine guide vane; and then leads out to the outside of the combustion chamber casing through the eighth wire hole opened on the turbine casing, the channel in the guide vane, and the center hole of the bolt with holes.

[0013] Optional: Three detection probes are evenly distributed in the outer cavity of the guide, the fourth tooth cavity, the first tooth cavity, the second tooth cavity, the cold air pressurization cavity, and the outer cavity of the blade.

[0014] Optional: The detection probes in each compartment are fixed by anchor plates spot-welded to the compartment wall.

[0015] Optional: In each compartment, the wires are fixed by anchor plates welded to the compartment wall.

[0016] The beneficial effects of this invention are as follows: The wiring is simple, the monitoring range is wide, the monitoring accuracy is high, the operation is simple, manual intervention is reduced, and safety is ensured. It can achieve real-time and accurate measurement of the temperature and pressure of each chamber of the turbine, helping operators to understand the operating status of the gas turbine. Furthermore, it avoids drilling holes in the turbine blades; the wiring modification work can be completed using only the original structure and some additional machined parts. It is suitable for high-pressure / low-pressure turbine guide vanes under various operating conditions and environments. The parameters of the temperature and pressure measuring tubes can be selected according to the actual temperature and pressure to meet the measurement needs of different gas turbines. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of this scheme or the prior art, the accompanying drawings used in the description of the embodiments or the prior art will be briefly introduced below.

[0018] Figure 1 This is a schematic diagram of the turbine guide assembly; Figure 2 This is a schematic diagram of the flow of cold air in each compartment; Figure 3 This is a schematic diagram of each compartment in the gas turbine guide section; Figure 4 This is a wiring diagram of each compartment in the gas turbine guide section; Figure 5 This is a schematic diagram of the turbine sealing ring; Figure 6 This is a schematic diagram of the guide vane structure; Figure 7 This is a schematic diagram of the turbine casing; Figure 8 This is a wiring diagram between the turbine casing and the combustion chamber rear casing; Figure 9 This is a schematic diagram of the pre-rotating nozzle ring; Figure 10 This is a schematic diagram of the inner conical ring structure.

[0019] In the diagram: 1-Inner mounting ring; 101-Cold air inlet; 102-First wire guide hole; 103-Second wire guide hole; 104-Third wire guide hole; 105-Fourth wire guide hole; 106-Front ring section; 107-First outer ring section; 108-Inner ring section; 109-Rear ring section; 1010-Second outer ring section; 2-Inner conical ring; 21-Conical section; 22-Front flange section; 23-Rear flange section; 231-Axial vent; 232-Radial vent; 3-Pre-rotating nozzle ring; 31-Ring section; 32-First sealing section; 33-Second sealing section; 34-Nozzle section; 341-Spray hole; 36-Fifth wire guide hole; 37-Sixth wire guide hole; 4-Inner grate sealing ring; 5-Front grate disc; 51-Disc surface 52-Inlet port; 53-First grate tooth section; 55-Fourth grate tooth section; 6-Turbine disk; 7-Guide vane; 701-Outer end plate; 702-Seventh wire guide hole; 8-Rotor blade; 9-Turbine guide outer ring; 10-Turbine sealing ring; 11-Sealing casing; 12-Turbine casing; 121-Outer ring groove; 122-Eighth wire guide hole; 123-Front side groove; 13-Rear casing of combustion chamber; 14-Guide vane; 15-Bolt with hole; Phpt1-Nozzle annular cavity; Phpt5-Guide outer cavity; PQ61-Fourth grate tooth cavity; PQ62-First grate tooth cavity; PQ63-Second grate tooth cavity; PQ68-Cooled air booster cavity; PQ69-Blade outer cavity. Detailed Implementation

[0020] The technical solutions in this embodiment will be clearly and completely described below with reference to the accompanying drawings. The described embodiments are only some embodiments, not all of them. All other embodiments obtained by those skilled in the art based on the embodiments in this solution without creative effort are within the protection scope of this solution.

[0021] Example like Figures 1 to 10 As shown, this embodiment designs a multi-chamber wiring method for detecting the guide section of a gas turbine. The guide section of the gas turbine includes a casing assembly, a turbine guide assembly, and a turbine rotor assembly.

[0022] The turbine rotor assembly includes a turbine shaft, rotor blades 8, a front grate disk 5, and a turbine disk 6; the turbine shaft, front grate disk 5, and turbine disk 6 are arranged sequentially from front to back. The turbine shaft is cylindrical. The turbine disk 6 is disc-shaped and connected to the rear end of the turbine shaft, with multiple rotor blades 8 connected to the outer ring side of the turbine disk 6. The front grate disk 5 is also disc-shaped and is located on the front side of the turbine shaft. The inner ring side of the front grate disk 5 is fitted onto the forward-protruding portion in the middle of the turbine disk 6, and an air inlet 51 is provided on the front grate disk 5. The front side of the front grate disk 5 has multiple grate sections, specifically including a fourth grate section 55, a first grate section 52, and a second grate section 53 arranged sequentially from the outside to the inside.

[0023] The turbine guide vane assembly includes components such as an inner mounting ring 1, an inner conical ring 2, a pre-swirl nozzle ring 3, and an inner grate sealing ring 4. Several guide vanes 7 are circumferentially arranged on the rear outer side of the inner mounting ring 1.

[0024] The inner mounting ring 1 includes a front ring portion 106, a first outer ring portion 107, an inner ring portion 108, a rear ring portion 109, and a second outer ring portion 1010. The front ring portion 106 is located in front of the rear ring portion 109, the first outer ring portion 107 is located outside the connection between the front ring portion 106 and the rear ring portion 109, the inner ring portion 108 is located behind the connection between the front ring portion 106 and the rear ring portion 109, and the second outer ring portion 1010 is located outside the rear end of the rear ring portion 109. A cold air passage is provided outside the front ring portion 106, which is located outside the inner conical ring 2, and a cold air pressurization chamber PQ68 is formed between the two. The rear end of the second outer ring portion 1010 is sealed with the fourth grate portion 55, and the outer side of the fourth grate portion 55 forms a fourth grate cavity PQ61; both the first outer ring portion 107 and the second outer ring portion 1010 are connected to the inner end of the guide vane 7.

[0025] The inner conical ring 2 includes a conical portion 21, a front flange portion 22, and a rear flange portion 23; the diameter of the conical portion 21 decreases from front to back; the front flange portion 22 is located on the front side of the conical portion 21 and is fixedly connected to the front side of the inner mounting ring 1 by bolts; the rear flange portion 23 is located on the rear side of the conical portion 21, and a number of axial air holes 231 are arranged around the rear flange portion 23. The axial air holes 231 are used to pressurize the cold air and send it into the jet hole 341 of the pre-rotating nozzle ring 3. The cold air pressurization chamber PQ68 is constricted along the airflow direction.

[0026] The pre-rotating nozzle ring 3 is connected to the rear end of the inner conical ring 2. The pre-rotating nozzle ring 3 includes components such as annular portion 31, sealing portion, and nozzle portion 34. The annular portion 31 is circular, and has multiple sealing portions on its rear annular surface, specifically a first sealing portion 32 and a second sealing portion 33. The first sealing portion 32 and the second sealing portion 33 are located at the outer edge and middle of the rear annular surface of the pre-rotating nozzle ring 3, respectively. The first sealing portion 32 seals with the first grate portion 52, forming a first grate cavity PQ62 on the inner side of the first grate portion 52; the second sealing portion 33 seals with the second grate portion 53, forming a second grate cavity PQ63 on the inner side of the second grate portion 53. Through the sealing structure design at the first sealing portion 32 and the second sealing portion 33, the outer sealing channel between the front grate disc 5 and the pre-rotating nozzle is bent into an S-shape. The nozzle section 34 is located on the inner ring side of the annular section 31, and a plurality of jet holes 341 are provided on the nozzle section 34. When the pre-rotating nozzle ring 3 is connected to the inner conical ring 2, the alignment of the axial air hole 231 and the jet hole 341 should be ensured. The inner ring side of the pre-rotating nozzle ring 3 is provided with a nozzle ring cavity Phpt1.

[0027] The casing assembly includes a turbine guide ring 9, a turbine casing 12, a combustion chamber rear casing 13, guide vanes 14, and perforated bolts 15. The turbine guide ring 9 is located outside the guide vanes 7. The turbine guide ring 9 is located inside the rear end of the combustion chamber rear casing 13, and the two form a guide outer cavity Phpt5. The turbine casing 12 is fixed to the inner rear end of the combustion chamber rear casing 13 and is sealed with the rotor blades 8 by the toothed joint. The inner end of the guide vanes 14 is connected to the turbine casing 12, and the outer end is connected to the outer rear end of the combustion chamber rear casing 13 by the perforated bolts 15. The turbine casing 12 is annular, with an outer ring groove 121 on the outer side and a front side groove 123 on the front side. The front side groove 123 and the outer ring groove 121 are connected by an inclined eighth through hole 122. The turbine sealing ring 10 is fixed inside the turbine casing 12 and mates with the rotor blades to form a grate seal. The sealing casing 11 is connected to the rear side of the turbine casing 12 and is used for sealing the rear structure of the turbine casing.

[0028] Multi-chamber wiring methods include: S1: The wires connected to the detection probes in the fourth grating cavity PQ61 are introduced into the cold air pressurization cavity PQ68 through the third wire hole 104 opened on the second outer ring 1010 and the first wire hole 102 opened at the connection between the front ring 106 and the rear ring 109; three detection probes are evenly distributed in the circumferential direction of the fourth grating cavity PQ61.

[0029] S2: The wires connected to the detection probes in the first grating cavity PQ62 are introduced into the cold air pressurization cavity PQ68 through the fifth wire hole 36 opened on the annular part 31 and the second wire hole 103 opened on the inner ring part 108; three detection probes are evenly distributed in the circumferential direction of the first grating cavity PQ62.

[0030] S3: The wires connected to the detection probes in the second grating cavity PQ63 are introduced into the cold air pressurization cavity PQ68 through the sixth wire hole 37 opened on the annular part 31 and the second wire hole 103 opened on the inner ring part 108; three detection probes are evenly distributed in the circumferential direction of the second grating cavity PQ63.

[0031] S4: The wire introduced into the cold air booster chamber PQ68 in steps S1-S3 passes sequentially through the cold air inlet 101 on the front ring 106, the cold air passage, the fourth wire hole 105 opened on the first outer ring 107, the internal passage of the guide vane 7, the seventh wire hole 702 opened on the outer end plate 701 of the guide vane 7, the through hole on the outer ring 9 of the turbine guide vane, the guide vane outer partition Phpt5, the eighth wire hole 122 opened on the turbine casing 12, the passage inside the guide vane 14, and the center hole of the bolt with holes 15, and is led out to the outside of the combustion chamber rear casing 13.

[0032] A detection probe is also installed in the nozzle ring cavity Phpt1 on the inner ring side of the pre-swirl nozzle ring 3. Four detection probes are evenly distributed in the circumferential direction within the nozzle ring cavity Phpt1. The wires connected to the detection probes are introduced into the cold air boosting chamber PQ68 through the axial air hole 231; and led out to the outside of the combustion chamber rear casing 13 according to step S4.

[0033] A detection probe is installed in the air-cooled booster chamber PQ68, and the wire connected to the detection probe in the air-cooled booster chamber PQ68 is led out to the outside of the combustion chamber rear casing 13 according to step S4. Three detection probes are evenly distributed in the circumferential direction of the air-cooled booster chamber PQ68.

[0034] A detection probe is installed in the Phpt5 outer cavity of the guide vane between the outer ring 9 of the turbine guide vane and the rear casing 13 of the combustion chamber. The wire connected to the detection probe passes through the eighth wire hole 122 on the turbine casing 12, the channel inside the guide vane 14, and the center hole of the bolt with holes 15, and is led out to the outside of the rear casing 13 of the combustion chamber. Three detection probes are evenly distributed in the circumferential direction of the outer cavity of the guide vane.

[0035] A blade outer cavity PQ69 is formed between the outer ring 9 of the turbine guide vane and the guide vane 7. The wires connected to the detection probes in the blade outer cavity PQ69 are introduced into the outer cavity Phpt5 through another through hole on the outer ring 9 of the turbine guide vane; then, sequentially, they pass through the eighth wire hole 122 on the turbine casing 12, the channel inside the guide vane 14, and the center hole of the bolt with holes 15, leading out to the outside of the combustion chamber rear casing 13. Three detection probes are evenly distributed in the circumferential direction of the blade outer cavity PQ69.

[0036] The detection probes in each compartment are fixed by anchor plates spot-welded to the compartment walls. Similarly, the wires in each compartment are fixed by anchor plates welded to the compartment walls.

[0037] The above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation; it is neither necessary nor possible to exhaustively list all possible implementations. However, obvious variations or modifications derived therefrom remain within the scope of this technology.

Claims

1. A multi-chamber wiring method for detecting the guide section of a gas turbine, characterized in that: The guide section of a gas turbine includes the casing assembly, the turbine guide assembly, and the turbine rotor assembly; The turbine rotor assembly includes rotor blades (8), a front grating disk (5), and a turbine disk (6); the front grating disk (5) is disposed on the front side of the turbine disk (6), and a plurality of rotor blades (8) are connected to the outer ring side of the turbine disk (6); the front grating disk (5) is provided with a fourth grating portion (55), a first grating portion (52), and a second grating portion (53) in sequence from the outside to the inside; The turbine guide assembly includes an inner mounting ring (1), an inner cone ring (2), and a pre-swirl nozzle ring (3). The inner mounting ring (1) includes a front ring portion (106), a first outer ring portion (107), an inner ring portion (108), a rear ring portion (109), and a second outer ring portion (1010); the front ring portion (106) is located on the front side of the rear ring portion (109), the first outer ring portion (107) is located on the outer side of the connection between the front ring portion (106) and the rear ring portion (109), the inner ring portion (108) is located on the rear side of the connection between the front ring portion (106) and the rear ring portion (109), and the second outer ring portion (1010) is located on the rear side of the connection between the front ring portion (106) and the rear ring portion (109). A cold air passage is provided on the outer side of the rear ring (109); the front ring (106) is located on the outer side of the inner conical ring (2) and a cold air pressurization chamber (PQ68) is formed between the two; the rear end of the second outer ring (1010) is sealed with the fourth toothed part (55), and a fourth toothed cavity (PQ61) is formed on the outer side of the fourth toothed part (55); the first outer ring (107) and the second outer ring (1010) are both connected to the inner end of the guide vane (7); The pre-rotating nozzle ring (3) is connected to the rear end of the inner conical ring (2) and includes an annular face (31) and a first sealing part (32) and a second sealing part (33) respectively provided on the outer and middle parts of the annular face (31). The front toothed disc (5) is provided with a first toothed part (52) and a second toothed part (53). The first sealing part (32) seals with the teeth of the first toothed part (52) and forms a first toothed cavity (PQ62) on the inner side of the first toothed part (52). The second sealing part (33) seals with the teeth of the second toothed part (53) and forms a second toothed cavity (PQ63) on the inner side of the second toothed part (53). The casing assembly includes a turbine guide ring (9), a turbine casing (12), a combustion chamber rear casing (13), guide vanes (14), and perforated bolts (15); the turbine guide ring (9) is located on the outside of the guide vanes (7); the turbine guide ring (9) is located on the inner rear end of the combustion chamber rear casing (13), and the two form a guide outer cavity (Phpt5); the turbine casing (12) is fixed to the inner rear end of the combustion chamber rear casing (13) and is sealed with the grates of the rotor blades (8); the inner end of the guide vanes (14) is connected to the turbine casing (12), and the outer end is connected to the outer rear end of the combustion chamber rear casing (13) through perforated bolts (15); Multi-chamber wiring methods include: S1: The wire connected to the detection probe in the fourth sieve cavity (PQ61) is introduced into the cold air pressurization cavity (PQ68) through the third wire hole (104) opened on the second outer ring (1010) and the first wire hole (102) opened at the connection between the front ring (106) and the rear ring (109). S2: The wire connected to the detection probe in the first toothed cavity (PQ62) is introduced into the cold air pressurization cavity (PQ68) through the fifth wire hole (36) opened on the annular part (31) and the second wire hole (103) opened on the inner ring part (108). S3: The wire connected to the detection probe in the second sieve cavity (PQ63) is introduced into the cold air pressurization cavity (PQ68) through the sixth wire hole (37) opened on the annular part (31) and the second wire hole (103) opened on the inner ring part (108). S4: The wire introduced into the cold air booster chamber (PQ68) in steps S1-S3 passes through the cold air inlet (101) on the front ring (106), the cold air passage, the fourth wire hole (105) opened on the first outer ring (107), the internal passage of the guide vane (7), the seventh wire hole (702) opened on the outer end plate (701) of the guide vane (7), the through hole on the outer ring (9) of the turbine guide vane, the outer partition cavity (Phpt5) of the guide vane, the eighth wire hole (122) opened on the turbine casing (12), the passage in the guide vane (14), and the center hole of the bolt with hole (15), and is led out to the outside of the combustion chamber rear casing (13).

2. The multi-chamber wiring method for detecting the gas turbine guide section according to claim 1, characterized in that: The inner ring side of the pre-rotating nozzle ring (3) is provided with a nozzle ring cavity (Phpt1); a rear flange (23) is provided at the rear of the inner cone ring (2), and an axial air hole (231) is provided on the rear flange (23); the wire connected to the detection probe in the nozzle ring cavity (Phpt1) is introduced into the cold air boost chamber (PQ68) through the axial air hole (231); and led out to the outside of the combustion chamber rear casing (13) in accordance with step S4.

3. The multi-chamber wiring method for detecting the gas turbine guide section according to claim 2, characterized in that: Four detection probes are evenly distributed inside the nozzle annular cavity (Phpt1).

4. The multi-chamber wiring method for detecting the gas turbine guide section according to claim 1, characterized in that: The wires connected to the detection probe in the cold air booster chamber (PQ68) are led out to the outside of the combustion chamber rear casing (13) in accordance with step S4.

5. The multi-chamber wiring method for detecting the guide section of a gas turbine according to claim 1, characterized in that: The wire connected to the detection probe in the outer cavity of the guide vane (Phpt5) passes through the eighth wire hole (122) on the turbine casing (12), the channel in the guide vane (14), and the center hole of the bolt with hole (15) in sequence, and is led out to the outside of the combustion chamber rear casing (13).

6. The multi-chamber wiring method for detecting the guide section of a gas turbine according to any one of claims 1-5, characterized in that: A blade outer cavity (PQ69) is formed between the outer ring (9) of the turbine guide vane and the guide vane (7); the wire connected to the detection probe in the blade outer cavity (PQ69) is introduced into the outer cavity (Phpt5) of the guide vane through another through hole on the outer ring (9) of the turbine guide vane; then it is led out to the outside of the combustion chamber rear casing (13) through the eighth wire hole (122) opened on the turbine casing (12), the channel in the guide vane (14), and the center hole of the bolt with hole (15).

7. The multi-chamber wiring method for detecting the guide section of a gas turbine according to claim 6, characterized in that: Three detection probes are evenly distributed in the outer cavity of the guide (Phpt5), the fourth tooth cavity (PQ61), the first tooth cavity (PQ62), the second tooth cavity (PQ63), the cold air pressurization cavity (PQ68), and the outer cavity of the blade (PQ69).

8. The multi-chamber wiring method for detecting the guide section of a gas turbine according to claim 7, characterized in that: The detection probes in each compartment are fixed by anchor plates spot-welded to the compartment walls.

9. The multi-chamber wiring method for detecting the guide section of a gas turbine according to claim 8, characterized in that: In each compartment, the wires are fixed by anchor plates welded to the compartment wall.

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