Gas turbine runner temperature cooling system capable of effectively reducing temperature

Abstract

The utility model discloses a gas turbine runner temperature cooling system capable of effectively cooling, which comprises a gas turbine insulating layer and a stabilizing mechanism, a runner temperature element is mounted in the gas turbine insulating layer, a cooling groove is formed in the gas turbine insulating layer, and the gas turbine runner temperature cooling system further comprises a newly added cooling surface and a compressed air mother pipe, a cooling air valve is rotatably mounted on the front surface of the compressed air mother pipe, a stainless steel instrument pipe is mounted at the right end of the compressed air mother pipe, pressing mechanisms are mounted on the upper side and the lower side of the compressed air mother pipe, a telescopic rod is slidably mounted in the supporting rod, and a rotating rod is rotatably mounted at the upper end of the telescopic rod. According to the gas turbine runner temperature cooling system capable of effectively reducing the temperature, the effect of increasing the element cooling area can be achieved by arranging the newly-added cooling face, the heat dissipation condition of the runner temperature element is improved, forced element cooling is achieved, and the sealing performance of connection of the compressed air mother pipe and the stainless steel instrument pipe can be guaranteed by arranging the sealing and stabilizing mechanism.

Description

Technical Field

[0001] The utility model relates to the technical field of combustion engines, in particular to a combustion engine flow channel temperature cooling system capable of effectively reducing temperature. Background Art

[0002] A gas turbine is an internal combustion power machine that uses a continuously flowing gas as a working fluid to drive the impeller to rotate at high speed, thereby converting the energy of the fuel into useful work. It is a complex product of multidisciplinary coupling. Blade flow path temperature is an important monitoring parameter of gas turbines, and the arrangement of its measuring points on H-class gas turbines is more mature. The relevant protections set around the blade flow path temperature are not only an effective means to monitor the working status of the burner, but also a strong line of defense to ensure the safety of operating personnel and equipment. At present, the lead wires of the components are partially cooled by natural ventilation. However, because the installation position of the flow path temperature components No. 4 and No. 13 is close to the flange surface of the outer cylinder of the gas turbine, the insulation layer is thicker, which makes the components unable to be cooled by natural ventilation.

[0003] During the startup of the entire unit, the flow channel temperature element has experienced multiple abnormal incidents in which the lead part was burned by high temperature, resulting in the unit not being able to shut down. As the power grid has increasingly higher requirements for the stability of the power generation side, it also puts higher requirements on the working reliability of the components. This cooling method urgently needs to be improved.

[0004] The existing gas turbine flow channel cooling system has the problem that the insulation layer is too thick, the flow channel temperature components are easily burned by high temperature and cause failures, increase the maintenance cost, and the cooling effect is poor. Therefore, we propose a gas turbine flow channel temperature cooling system that can effectively reduce the temperature in order to solve the above problems. Utility Model Content

[0005] The purpose of the utility model is to provide a gas turbine flow path temperature cooling system that can effectively reduce the temperature, so as to solve the problems mentioned in the above background technology that the existing gas turbine flow path cooling system has a thick insulation layer, the flow path temperature elements are easily burned by high temperature and cause failures, increase maintenance costs, and have poor cooling effect.

[0006] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a gas turbine flow passage temperature cooling system capable of effectively reducing temperature, comprising a gas turbine insulation layer and a stabilizing mechanism, a flow passage temperature element is installed inside the gas turbine insulation layer, a cooling groove is provided inside the gas turbine insulation layer, and a newly added cooling surface and a compressed air main pipe are also included, a cooling air valve is rotatably installed on the front surface of the compressed air main pipe, a stainless steel instrument pipe is installed on the right end of the compressed air main pipe, a threaded cylinder is fixedly installed on the left end of the stainless steel instrument pipe, an instrument valve is installed on the surface of the stainless steel instrument pipe, a sealing ring is installed on the right end of the compressed air main pipe, and a clamping mechanism is installed on both the upper and lower sides of the compressed air main pipe;

[0007] The stabilizing mechanism includes a holder, a support rod, a telescopic rod and a rotating rod. The upper and lower sides of the stainless steel instrument tube are fixedly installed with holders, the inner side of the holder is rotatably installed with a support rod, the inner side of the support rod is slidably installed with a telescopic rod, and the upper end of the telescopic rod is rotatably installed with a rotating rod.

[0008] Preferably, the stainless steel instrument tube is connected to the compressed air main pipe through a threaded barrel by a threaded connection.

[0009] Preferably, the clamping mechanism comprises a pillar, a screw and a pressure plate, pillars are fixedly installed on both the upper and lower sides of the compressed air main pipe, a screw is installed on the internal thread of the pillar, and a pressure plate is installed at the end of the screw.

[0010] Preferably, the rotating rod forms an up and down sliding structure with the stainless steel instrument tube through the supporting rod, the telescopic rod, the positioning hole and the screw.

[0011] Preferably, a limiting hole is provided on the surface of the rotating rod, and the size of the rotating rod passing through the limiting hole is larger than the size of the pillar.

[0012] Preferably, the rotating rod is connected to the supporting column by means of a snap-fit ​​connection via a screw rod and a pressing plate.

[0013] Compared with the prior art, the utility model has the following beneficial effects: the gas turbine flow passage temperature cooling system capable of effectively reducing the temperature;

[0014] 1. Setting up a new cooling surface can increase the cooling area of ​​the component, solve the problem that the insulation layer is too thick and the flow channel temperature component is easily scalded by high temperature and causes failure, improve the heat dissipation conditions of the flow channel temperature component, realize forced cooling of the component, and promptly take away the heat generated by high temperature thermal radiation, thereby improving the cooling effect;

[0015] 2. The optimized cooling system also provides strong hardware support for the long-term reliable and economical operation of the unit. The optimized system can be widely shared at the equipment level, with a high degree of compatibility. Whether it is a new design or a renovation, whether it is a one-time investment or operation and maintenance cost, it has economic advantages;

[0016] 3. A sealing and stabilizing mechanism is provided to ensure the sealing of the connection between the compressed air main pipe and the stainless steel instrument pipe, thereby preventing cooling air from leaking and affecting the cooling effect. The present invention systematically optimizes the cooling method of the simple flow channel temperature element, and keeps the element in good working conditions under different working conditions, thereby effectively preventing element failure, ensuring measurement accuracy and providing equipment reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the front view structure of the utility model;

[0018] Figure 2This is a schematic diagram of the front view cutaway structure of the utility model;

[0019] Figure 3 It is a side view cutaway structural schematic diagram of the utility model;

[0020] Figure 4 It is a schematic diagram of the structure of the utility model from top view.

[0021] In the figure: 1. Insulation layer of gas turbine; 2. Flow channel temperature element; 3. Cooling groove; 4. New cooling surface; 5. Compressed air main pipe; 6. Cooling air valve; 7. Stainless steel instrument pipe; 8. Instrument valve; 9. Sealing ring; 10. Threaded cylinder; 11. Clamping seat; 12. Support rod; 13. Telescopic rod; 14. Rotating rod; 15. Limiting hole; 16. Support; 17. Screw; 18. Pressure plate. DETAILED DESCRIPTION

[0022] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0023] See also Figure 1-4 The utility model provides a technical solution: a gas turbine flow channel temperature cooling system capable of effectively reducing temperature, comprising a gas turbine insulation layer 1, a flow channel temperature element 2, a cooling groove 3, a newly added cooling surface 4, a compressed air main pipe 5, a cooling air valve 6, a stainless steel instrument pipe 7, an instrument valve 8, a sealing ring 9, a threaded cylinder 10, a holder 11, a support rod 12, a telescopic rod 13, a rotating rod 14, a limiting hole 15, a support 16, a screw 17 and a pressing plate 18, such as Figure 1 and Figure 3 As shown, a flow channel temperature element 2 is installed inside the thermal insulation layer 1 of the gas turbine, a cooling groove 3 is opened on the surface of the thermal insulation layer 1 of the gas turbine, and the newly added cooling surface 4 is realized by expanding the hole of the thermal insulation layer at the original flow channel temperature. The cold air system takes samples by opening a hole from the compressed air main pipe 5. A sealing ring 9 is installed at the right end of the compressed air main pipe 5. A threaded cylinder 10 is fixedly installed at the left end of the stainless steel instrument pipe 7. The threaded cylinder 10 at the left end of the stainless steel instrument pipe 7 is aligned with the compressed air main pipe 5, the stainless steel instrument pipe 7 is rotated, and the threaded cylinder 10 at the left end of the stainless steel instrument pipe 7 is threadedly installed in the compressed air main pipe 5. The 8mm stainless steel instrument pipe 7 is connected to the flow channel temperature. The sealing ring 9 increases the sealing of the compressed air main pipe 5 and the stainless steel instrument pipe 7 to avoid affecting the cooling effect.

[0024] A cooling air valve 6 is rotatably installed on the front surface of the compressed air main pipe 5, and an instrument valve 8 is installed on the surface of the stainless steel instrument pipe 7. When the cooling air valve 6 and the instrument valve 8 are opened, the cooling air is transported to the thermal insulation layer 1 of the gas turbine through the compressed air main pipe 5 and the stainless steel instrument pipe 7. The cooling groove 3 and the newly added cooling surface 4 arranged at the thermal insulation layer 1 of the gas turbine increase the cooling area of ​​the component, improve the heat dissipation condition of the flow channel temperature component 2, realize forced cooling of the component, and promptly take away the heat generated by high-temperature thermal radiation, thereby improving the cooling effect;

[0025] like Figure 2 and Figure 4 As shown, the upper and lower sides of the stainless steel instrument tube 7 are fixedly installed with a holder 11, the inner side of the holder 11 is rotatably installed with a support rod 12, the inner side of the support rod 12 is slidably installed with a telescopic rod 13, and the upper end of the telescopic rod 13 is rotatably installed with a rotating rod 14. After the stainless steel instrument tube 7 is threadedly connected to the compressed air mother pipe 5, the rotating rod 14 is rotated to rotate the rotating rod 14 to the top of the compressed air mother pipe 5, the screws on the surface of the support rod 12 are unscrewed, and the telescopic rod 13 is moved up and down. The telescopic rod 13 drives the rotating rod 14 to rise and fall, and the rotating rod 14 is adjusted to align with the pillar 16. A limiting hole 15 is provided on the surface of the rotating rod 14, and the size of the limiting hole 15 is the size of the pillar 16. The rotating rod 14 is lowered until its lower surface fits the upper surface of the compressed air mother pipe 5, and then the screws on the surface of the support rod 12 are tightened to fix the support rod 12 and the telescopic rod 13;

[0026] A screw rod 17 is installed on the internal thread of the support 16, and a pressure plate 18 is installed on the end of the screw rod 17. After the rotating rod 14 is covered on the support 16, the pressure plate 18 is rotated, and the pressure plate 18 moves toward the rotating rod 14 along with the screw rod 17. The pressure plate 18 is lowered to press on the upper surface of the rotating rod 14, and the rotating rod 14 is pressed and fixed, which plays a stabilizing role for the compressed air main pipe 5 and the stainless steel instrument pipe 7, and prevents the threaded tube 10 at the left end of the stainless steel instrument pipe 7 from loosening and affecting the cooling effect.

[0027] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A gas turbine flow channel temperature cooling system capable of effectively reducing temperature, comprising a gas turbine thermal insulation layer (1) and a stabilizing mechanism, wherein a flow channel temperature element (2) is installed inside the gas turbine thermal insulation layer (1), and a cooling groove (3) is provided inside the gas turbine thermal insulation layer (1), characterized in that: It also includes a newly added cooling surface (4) and a compressed air main pipe (5), the front surface of the compressed air main pipe (5) is rotatably mounted with a cooling air valve (6), the right end of the compressed air main pipe (5) is mounted with a stainless steel instrument pipe (7), the left end of the stainless steel instrument pipe (7) is fixedly mounted with a threaded cylinder (10), the surface of the stainless steel instrument pipe (7) is mounted with an instrument valve (8), the right end of the compressed air main pipe (5) is mounted with a sealing ring (9), and the upper and lower sides of the compressed air main pipe (5) are both mounted with a clamping mechanism; The stabilizing mechanism comprises a holder (11), a support rod (12), a telescopic rod (13) and a rotating rod (14); the holder (11) is fixedly mounted on both upper and lower sides of the stainless steel instrument tube (7); the support rod (12) is rotatably mounted on the inner side of the holder (11); the telescopic rod (13) is slidably mounted inside the support rod (12); and the rotating rod (14) is rotatably mounted on the upper end of the telescopic rod (13).

2. A gas turbine flow passage temperature cooling system capable of effectively reducing temperature according to claim 1, characterized in that: The stainless steel instrument tube (7) is connected to the compressed air main pipe (5) through a threaded tube (10) by a threaded connection.

3. A gas turbine flow passage temperature cooling system capable of effectively reducing temperature according to claim 1, characterized in that: The clamping mechanism comprises a support (16), a screw (17) and a pressure plate (18); the support (16) is fixedly mounted on both the upper and lower sides of the compressed air main pipe (5); the screw (17) is mounted on the internal thread of the support (16); and the pressure plate (18) is mounted at the end of the screw (17).

4. A gas turbine flow passage temperature cooling system capable of effectively reducing temperature according to claim 1, characterized in that: The rotating rod (14) forms an up and down sliding structure with the stainless steel instrument tube (7) through the supporting rod (12), the telescopic rod (13), the positioning holes and the screws.

5. A gas turbine flow passage temperature cooling system capable of effectively reducing temperature according to claim 1, characterized in that: A limiting hole (15) is provided on the surface of the rotating rod (14), and the size of the limiting hole (15) is larger than the size of the support column (16).

6. A gas turbine flow passage temperature cooling system capable of effectively reducing temperature according to claim 3, characterized in that: The rotating rod (14) is connected to the support (16) by means of a snap-fit ​​connection via a screw rod (17) and a pressure plate (18).

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