Gas turbine rotor

Abstract

The utility model relates to the technical field of gas turbine rotors, and particularly discloses a gas turbine rotor which comprises a base, supporting frames are fixedly connected to the left side and the right side of the top of the base, and the surfaces of a front-end blade and a rear-end blade are coated with thermal insulation coatings so as to improve the thermal insulation performance of the front-end blade and the rear-end blade, so that stable operation of the front-end blade and the rear-end blade is guaranteed. Meanwhile, an air guide pipe is arranged on the outer side of the main shaft, when front-end blades operate and suck cold air from air inlet holes, part of the cold air is transmitted to a rear-end blade area in a turbine area through the air guide pipe, so that heat on the surfaces of the rear-end blades is taken away through air circulation, meanwhile, a suction pump is used for pumping cold water in a water tank, and the cold water is pumped into the turbine area; meanwhile, the rear-end blades rotate to strike the sprayed water flow, the water flow is scattered, the water flow is scattered in a turbine area, the temperature of the rear-end blades is reduced, the cooling effect of a rotor impeller is improved, and therefore stable operation of a rotor is guaranteed.

Description

Technical Field

[0001] The utility model relates to the technical field of gas turbine rotors, in particular to a gas turbine rotor. 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, converting the energy of the fuel into useful work. It is a rotating impeller type heat engine. The gas turbine rotor is a combination of rotating parts such as a main shaft and an impeller. The existing gas turbine rotor will be affected by high temperature and high pressure gas during operation, causing the impeller to melt due to excessive temperature, affecting the normal operation of the gas turbine. Therefore, measures need to be taken to reduce its temperature to ensure its performance and life. To this end, we propose a gas turbine rotor. Utility Model Content

[0003] The purpose of the utility model is to provide a gas turbine rotor to solve the problems raised in the above background technology.

[0004] In order to achieve the above purpose, the utility model provides the following technical solutions:

[0005] A gas turbine rotor comprises: a base, support frames are fixedly connected to the left and right sides of the top of the base, a compressor area is fixedly connected to the top of the left support frame, a combustion chamber is fixedly connected to the right side of the compressor area, a turbine area is fixedly connected to the right side of the combustion chamber, and a cooling assembly is arranged on the left side of the top of the base and on the outer sides of the compressor area and the turbine area;

[0006] The cooling assembly includes a cooling support box, and a suction pump is fixedly connected to the right inner wall of the cooling support box. The output end of the suction pump is fixedly connected to a plurality of water outlet pipes, which penetrate the cooling support box and the plate body of the compressor area and extend inwardly. The compressor area and the turbine area are connected at the inner end through an air guide pipe; a connecting pipe is fixedly connected to the right input end of the suction pump, and the other end of the connecting pipe is fixedly connected to the left side of the water tank.

[0007] Through the above technical solution, the base is used to support the overall structure to ensure the stability of the overall structure, the support frame is used to support the main body of the gas turbine, the compressor area is the air intake port when the gas turbine is running, and uses internal components to pressurize air and discharge it into the combustion chamber, the combustion chamber is used to inject fuel inward and improve the combustion efficiency of the fuel through pressurized air, the turbine area is used to extract the energy generated by combustion and discharge the air after combustion, the cooling support box is used to connect the cooling components to cool the inside of the turbine area, and the suction pump is used to cooperate with the connecting pipe to extract clean water from the water tank.

[0008] Preferably, the inner sides of the compressor area and the turbine area are fixedly connected with a fixing seat, and the middle part of the fixing seat is provided with a plurality of air inlet holes.

[0009] Through the above technical solution, the fixing seat is used to fix the main shaft, and the air inlet holes on the surface facilitate the gas turbine to inhale air during operation.

[0010] Preferably, the middle part of the fixing seat is rotatably connected with the main shaft, and a transition ring is arranged on the outer side of the middle part of the main shaft.

[0011] Through the above technical solution, the main shaft is used to drive the various structures to rotate, and the transition ring is used to buffer the fuel in transitional combustion and stabilize the energy released by the fuel.

[0012] Preferably, a plurality of flame tubes are fixedly connected to the outer side of the transition ring at equal intervals, and the other end of the flame tube passes through the plate body of the combustion chamber and extends outward.

[0013] Through the above technical solution, the combustion chamber is used to mix the fuel with the pressurized air to perform combustion work, and the flame tube is used to spray flames to ignite the fuel.

[0014] Preferably, the outer side of the flame tube is fixedly connected with an air supply port, and the output end of the air supply port is offset to the right.

[0015] Through the above technical solution, the air supply port is used to introduce a portion of pressurized air to further assist the combustion of the flame ejected from the flame tube.

[0016] Preferably, the right end of the transition ring is fixedly connected with a plurality of nozzles, and the input end of the nozzles is connected to the output end of the flame tube.

[0017] Through the above technical solution, the nozzle is used to guide out the energy released by the fully burned fuel.

[0018] Preferably, a plurality of front blades are fixedly connected to the outer left end of the main shaft at equal distances, and a plurality of rear blades are fixedly connected to the outer right end of the main shaft at equal distances.

[0019] Through the above technical solution, the front blades are used to rotate to generate suction, inhale and pressurize air, and the rear blades are used to discharge the energy generated by the work.

[0020] Preferably, the surfaces of the front blade and the rear blade are sprayed with a thermal isolation coating.

[0021] Through the above technical solution, by spraying a thermal isolation coating on the surface of the front blade and the rear blade, heat conduction can be reduced and the surface temperature can be lowered. This coating usually has high reflectivity and low thermal conductivity, which can effectively reduce the thermal load of the rotor.

[0022] The utility model has the following beneficial effects:

[0023] In the utility model, firstly, a thermal isolation coating is sprayed on the surface of the front blade and the rear blade to improve the thermal insulation performance thereof, thereby ensuring the stable operation of the front blade and the rear blade, and at the same time, an air duct is arranged on the outside of the main shaft. When the front blade runs and inhales cold air from the air inlet, a part of the cold air is transmitted to the rear blade area inside the turbine area through the air duct, thereby utilizing air circulation to take away the heat on the surface of the rear blade, and at the same time, a suction pump is utilized to extract cold water from the water tank, pump it into the turbine area, and spray it on the surface of the rear blade, and at the same time, the rear blade rotates and hits the sprayed water flow, thereby dispersing the water flow and making the water flow fully dispersed inside the turbine area, thereby reducing the temperature of the rear blade and improving the cooling effect of the rotor impeller, thereby ensuring the stable operation of the rotor. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a three-dimensional diagram of the utility model;

[0025] Figure 2 This is a rear view of the utility model;

[0026] Figure 3 This is the first schematic diagram of the internal structure of the utility model;

[0027] Figure 4 This is the second schematic diagram of the internal structure of the utility model;

[0028] Figure 5 This is a schematic diagram of the blade structure of the utility model.

[0029] Legend:

[0030] 1. Base; 2. Support frame; 3. Main shaft; 4. Compressor area; 5. Flame tube; 6. Combustion chamber; 7. Turbine area; 8. Cooling components: 801. Water tank; 802. Air guide pipe; 803. Cooling support box; 804. Connecting pipe; 805. Front blade; 806. Rear blade; 807. Suction pump; 808. Water outlet pipe; 809. Thermal isolation coating; 9. Fixed seat; 10. Air supply port; 11. Transition ring; 12. Nozzle. DETAILED DESCRIPTION

[0031] 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.

[0032] See also Figures 1 to 5 :

[0033] Embodiment 1

[0034] The utility model provides a technical solution: a gas turbine rotor, comprising a base 1, support frames 2 are fixedly arranged on both sides of the upper end of the base 1, and arc grooves are opened on the upper ends of the support frames 2 on both sides, the arc grooves on the upper ends of the two support frames 2 are respectively fixed to the bottom mounting ends of the compressor area 4 and the turbine area 7, the inner input and output ends of the compressor area 4 and the turbine area 7 are fixedly connected to the mounting ends on both sides of the combustion chamber 6, and a cooling component 8 is arranged on the left side of the top of the base 1 and the side of the compressor area 4 and the turbine area 7 close to the combustion chamber 6.

[0035] Through the above arrangement, the main shaft 3 is driven to rotate by the driving source, and then the main shaft 3 rotates, thereby driving the front end blades 805 on the left to rotate, thereby generating suction, and sucking the external air into the compressor area 4 through the air inlet hole opened on the surface of the left fixed seat 9, and using multiple groups of front end blades 805 to gradually pressurize the sucked air, and then discharge it into the combustion chamber 6 on the right. At this time, the flame tube 5 inside the combustion chamber 6 introduces fuel and ignites it, and then sprays it out through the nozzle 12. The flame sprayed through the nozzle 12 cooperates with the pressurized air transported to the right to increase the combustion efficiency of the fuel and improve the energy released by combustion. In addition, the air supply port 10 set on the surface of the flame tube 5 can introduce a part of the pressurized air, and cooperate with the pressurized air transmitted to the right by the compressor area 4. The combination of inside and outside can further improve the combustion efficiency of the fuel and reduce energy loss. The energy generated after combustion is discharged outward through the rotation of the rear end blades 806 on the outside of the main shaft 3 in the turbine area 7, which is convenient for energy utilization.

[0036] See also Figures 1 to 5 The cooling assembly 8 includes a cooling support box 803, which is located at the bottom of the turbine area 7, and two water outlet pipes 808 extend upward from the interior of the cooling support box 803. The output end of the water outlet pipe 808 passes through the bottom plate of the turbine area 7, and the input end of the water outlet pipe 808 is connected to the output end of the suction pump 807. The mounting end of the suction pump 807 is fixed on the right inner wall of the cooling support box 803. The suction pump 807 is connected to the water tank 801 through a connecting pipe 804. Several connecting ports are opened on the outer side of the end of the compressor area 4 and the turbine area 7 close to the combustion chamber 6, and the two ends of the air guide pipe 802 are respectively connected to the connecting ports of the compressor area 4 and the turbine area 7.

[0037] Through the above arrangement, when the gas turbine is running, the suction pump 807 is operated, and then the input end generates suction, and the clean water inside the water tank 801 is pumped out through the connecting pipe 804, and then introduced into the water outlet pipe 808 through the output end. Then the water outlet pipe 808 sprays the clean water inside the turbine area 7, and the clean water is used to absorb the heat accumulated on the surface of the rear end blades 806 due to the discharge of energy, thereby reducing the surface temperature of the rear end blades 806. In addition, at the connection between the compressor area 4 and the turbine area 7 through the air duct 802, a part of the air inhaled by the front end blades 805 inside the compressor area 4 is diverted and introduced into the air duct 802, and then introduced into the turbine area 7 through the air duct 802. The heat accumulated on the surface of the rear end blades 806 is further discharged by air circulation. Through the mutual cooperation of the two, the stable operation of the rear end blades 806 can be guaranteed.

[0038] Embodiment 2

[0039] See also Figures 1 to 5 A fixing seat 9 is fixedly provided on a section of the inner wall of the compressor area 4 and the turbine area 7 away from the combustion chamber 6, and a plurality of air inlet holes are opened on the surface of the fixing seat 9. The middle part of the fixing seat 9 is rotatably connected with the main shaft 3. A transition ring 11 is fixed to the outer mounting end of the main shaft 3 located in the combustion chamber 6 area. A plurality of flame tubes 5 are equidistantly arranged on the outside of the transition ring 11, and the output end of the flame tube 5 extends outward through the plate body of the combustion chamber 6. An air supply port 10 is fixed at the same position on the outside of the internal flame tube 5. The opening of the air supply port 10 is at the same angle as the nozzle 12 fixed at the output end on the right side of the transition ring 11, and the input end of the nozzle 12 is connected to the output end of the flame tube 5.

[0040] Through the above arrangement, the main shaft 3 is fixed by the support of the fixed seat 9 to ensure stable operation, which is convenient for driving other structures to operate. In addition, when the flame tube 5 ignites the fuel and discharges it, the fuel burning inside the flame tube 5 is buffered and integrated by the transition ring 11, and then discharged through the nozzle 12 to prevent pressurized air from blowing out the fuel ignited at the output end of a single flame tube 5.

[0041] See also Figures 1 to 5 : The main shaft 3 is located at the outside of one end inside the compressor area 4, and is fixedly connected to a plurality of front blades 805 in an equidistant ring shape, and the front blades 805 are arranged in multiple groups from left to right, and are arranged in sequence from large to small in size. The main shaft 3 is located at the outside of one end inside the turbine area 7, and is fixedly connected to a plurality of rear blades 806 in an equidistant ring shape, and the front blades 805 and the rear blades 806 are arranged in the same position, and are arranged in multiple groups from left to right, and are arranged in sequence from large to small in size. The surfaces of the front blades 805 and the rear blades 806 are sprayed with a thermal isolation coating 809.

[0042] Through the above-mentioned arrangement, multiple groups of front blades 805 and rear blades 806 can respectively pressurize the inhaled air step by step, pressurize the air, and increase the internal oxygen content, so as to improve the combustion-supporting effect during fuel combustion. At the same time, the rear blades 806 integrate and pressurize the energy generated by the fuel combustion step by step to prevent energy dissipation and improve energy utilization efficiency. At the same time, the surfaces of the front blades 805 and the rear blades 806 are sprayed with a thermal isolation coating 809, which further ensures the heat resistance of the front blades 805 and the rear blades 806 and improves the service life of the front blades 805 and the rear blades 806.

[0043] Working principle: The rear end blades 806 are driven to rotate through the operation of the main shaft 3, and then the rear end blades 806 operate to inhale air, and after step-by-step pressurization, discharge it into the combustion chamber 6, to assist the combustion of the burning fuel in the combustion chamber 6, and improve the combustion efficiency of the fuel, thereby ensuring that the released energy is maximized, and then the released energy is discharged through the turbine area 7 and utilized, and at the same time, the cooling component 8 is used to cool the front end blades 805 and the rear end blades 806 of the rotor to prevent the front end blades 805 and the rear end blades 806 from being melted by high temperature, thereby ensuring the service life and stability of the front end blades 805 and the rear end blades 806.

[0044] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A gas turbine rotor, comprising: A base (1), characterized in that: the left and right sides of the top of the base (1) are fixedly connected to support frames (2), the top of the left support frame (2) is fixedly connected to a compressor section (4), the right side of the compressor section (4) is fixedly connected to a combustion chamber (6), the right side of the combustion chamber (6) is fixedly connected to a turbine section (7), and a cooling assembly (8) is provided on the left side of the top of the base (1) and on the outer sides of the compressor section (4) and the turbine section (7); The cooling assembly (8) comprises a cooling support box (803), the right inner wall of the cooling support box (803) is fixedly connected to a suction pump (807), the output end of the suction pump (807) is fixedly connected to a plurality of water outlet pipes (808), the water outlet pipes (808) penetrate the cooling support box (803) and the plate body of the compressor section (4) and extend inwardly, and the compressor section (4) and the turbine section (7) are connected at one end on the inner side through an air guide pipe (802); the right input end of the suction pump (807) is fixedly connected to a connecting pipe (804), and the other end of the connecting pipe (804) is fixedly connected to the left side of the water tank (801).

2. The gas turbine rotor according to claim 1, characterized in that: The inner sides of the compressor area (4) and the turbine area (7) are fixedly connected with a fixing seat (9), and a plurality of air inlet holes are opened in the middle of the fixing seat (9).

3. The gas turbine rotor according to claim 2, characterized in that: The middle part of the fixed seat (9) is rotatably connected to the main shaft (3), and a transition ring (11) is arranged on the outer side of the middle part of the main shaft (3).

4. The gas turbine rotor according to claim 3, characterized in that: A plurality of flame tubes (5) are fixedly connected to the outer side of the transition ring (11) at equal intervals, and the other end of the flame tube (5) penetrates the plate body of the combustion chamber (6) and extends outward.

5. The gas turbine rotor according to claim 4, characterized in that: The outer side of the flame tube (5) is fixedly connected with a gas supply port (10), and the output end of the gas supply port (10) is offset to the right.

6. The gas turbine rotor according to claim 3, characterized in that: The right end of the transition ring (11) is fixedly connected to a plurality of nozzles (12), and the input end of the nozzles (12) is connected to the output end of the flame tube (5).

7. The gas turbine rotor according to claim 3, characterized in that: The outer left end of the main shaft (3) is evenly and fixedly connected to a plurality of front blades (805), and the outer right end of the main shaft (3) is evenly and fixedly connected to a plurality of rear blades (806).

8. The gas turbine rotor according to claim 7, characterized in that: The surfaces of the front blade (805) and the rear blade (806) are both sprayed with a thermal isolation coating (809).

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