CN219529158U - Vortex double-spray synergistic gas turbine capable of preventing extreme high temperature - Google Patents

Vortex double-spray synergistic gas turbine capable of preventing extreme high temperature Download PDF

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CN219529158U
CN219529158U CN202121010667.1U CN202121010667U CN219529158U CN 219529158 U CN219529158 U CN 219529158U CN 202121010667 U CN202121010667 U CN 202121010667U CN 219529158 U CN219529158 U CN 219529158U
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pipe
hole
gas turbine
main shaft
pressure turbine
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刘贽维
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    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/60Efficient propulsion technologies, e.g. for aircraft

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Abstract

The utility model provides a vortex double-injection synergistic and prevent extremely high temperature's gas turbine, includes the casing, the inside front axle body and the back axle body that is equipped with of casing; the front shaft body comprises a front main shaft, and fan blades, impeller blades and high-pressure turbine blades are arranged on the front main shaft; the rear shaft body comprises a rear main shaft, a low-pressure turbine blade is fixedly arranged on the rear main shaft, and a coupling pump is fixedly connected to the front end face of the rear main shaft; the shell is internally provided with a heat collecting tube, the heat collecting tube is communicated with one end of the flow guiding tube, and the other end of the flow guiding tube is communicated with the through hole. The utility model not only can reduce the temperature of the gas turbine material, but also can convert the collected heat into kinetic energy to act on the high-pressure turbine blade and the low-pressure turbine blade, so that the rotary spraying is generated, the energy utilization efficiency is improved, the gas turbine has the vortex double-spraying synergistic function, the gas turbine can be prevented from extremely high temperature, and the service life of the gas turbine is prolonged.

Description

Vortex double-spray synergistic gas turbine capable of preventing extreme high temperature
Technical Field
The utility model belongs to the technical field of gas turbines, and particularly relates to a vortex double-spray synergistic gas turbine capable of preventing extreme high temperature.
Background
The gas turbine is a heat engine with remarkable efficacy and is widely applied to space planes and ocean-going warships in various forms such as turbofan, turboprop, turbojet, vortex shaft and the like. The front end fan and the multistage air compression impeller are driven by the mechanical kinetic energy fed back by the turbine to compress air at a high ratio and input into the combustion reaction chamber, a large amount of high-temperature and high-pressure fuel gas is generated by mixing and burning the air and fuel, the high-temperature and high-pressure fuel gas acts on the high-pressure turbine and the low-pressure turbine at a high speed to enable the high-speed rotation and the high-speed ejection of the high-pressure turbine to generate corresponding reverse thrust, and energy conversion is realized and continuous normal operation of the machine is maintained. However, the existing gas turbine is rotated by singly utilizing the high-temperature and high-pressure gas generated by fuel combustion to impact the turbine in the working mode, and the gas is ejected out of the tail nozzle at a high speed to realize energy conversion, so that the core component of the machine is necessarily operated in a high-temperature severe environment, and the service life and the power of the machine are seriously endangered. Even if high temperature resistant materials such as expensive tungsten, rhenium, nickel-based alloy and the like are adopted, the temperature of the high-heating-value fuel, such as the high-heating-value fuel in the high-compression-ratio oxygen-enriched environment during deflagration, reaches 1500 ℃ to 2500 ℃, approaches to the high temperature of a blue flame zone which cannot be tolerated by the machine material, and directly jeopardizes the normal operation of the machine.
Disclosure of Invention
The utility model aims to provide a vortex double-spray synergistic gas turbine capable of preventing extremely high temperature, and solves the problems in the background technology.
In order to achieve the above purpose, the technical scheme adopted by the utility model is as follows: the utility model provides a vortex double-injection efficiency-enhanced gas turbine capable of preventing extreme high temperature, which comprises a shell, wherein the front end of the shell is an air inlet, and the rear end of the shell is a tail nozzle; a front shaft body and a rear shaft body which are coaxial are arranged in the shell;
the front shaft body comprises a front main shaft, fan blades, impeller blades and high-pressure turbine blades are sequentially and fixedly arranged on the front main shaft from front to back, and an axial through hole is formed in the front main shaft; a combustion reaction chamber is formed among the impeller blades, the high-pressure turbine blades and the shell, and a fuel nozzle is arranged in the combustion reaction chamber; the side surface of the front main shaft is provided with a branch pipe communicated with the through hole, and the branch pipe is positioned at the front end of the combustion reaction chamber; a supporting hole pipe communicated with the through hole is arranged on the high-pressure turbine blade, and an injection hole is arranged at the tail end of the supporting hole pipe;
the rear shaft body comprises a rear main shaft, a low-pressure turbine blade is fixedly arranged on the rear main shaft, a coupling pump is fixedly connected to the front end face of the rear main shaft, a spiral flow guide convex line is arranged on the coupling pump, and the coupling pump is positioned in the through hole;
the shell is internally provided with a heat collecting pipe which is positioned in the combustion reaction chamber and the tail nozzle area, the heat collecting pipe is communicated with one end of the flow guiding pipe, and the other end of the flow guiding pipe is communicated with the through hole; the honeycomb duct is connected with a water adding pipe and a liquid fuel pipe, cold water is arranged in the water adding pipe, and liquid fuel is arranged in the liquid fuel pipe.
In addition to the above, and as a preferable mode of the above, the coupling pump is located after the branch pipe.
On the basis of the scheme and as a preferable scheme of the scheme, the rear main shaft is provided with a hole pipe communicated with the through hole, the low-pressure turbine blade is provided with a branch hole pipe communicated with the hole pipe, and the tail end of the branch hole pipe is provided with an injection hole.
On the basis of the scheme and as a preferable scheme of the scheme, the high-pressure turbine blade and the low-pressure turbine blade are provided with a plurality of injection holes, and all the injection holes are communicated with the branch hole pipe.
On the basis of the above scheme and as a preferable scheme of the above scheme, the heat collecting pipe is spirally arranged.
On the basis of the scheme and as a preferable scheme of the scheme, the flow guide pipe is also connected with a nitro solution pipe, and a nitro solution is arranged in the nitro solution pipe.
On the basis of the scheme and as a preferable scheme of the scheme, the liquid fuel is aviation kerosene, and the nitro solution is ammonium nitrate solution.
On the basis of the scheme and as a preferable scheme of the scheme, throttle pumps are arranged on the flow guide pipe, the water adding pipe, the liquid fuel pipe and the nitro solution pipe, and the throttle pumps are connected with the control unit.
On the basis of the scheme and as a preferable scheme of the scheme, a Tesla valve is arranged in the front section of the through hole and the branch pipe.
The utility model has the beneficial effects that: the utility model not only can reduce the temperature of the gas turbine material, but also can convert the collected heat into kinetic energy to act on the high-pressure turbine blade and the low-pressure turbine blade, so that the rotary spraying is generated, the energy utilization efficiency is improved, the gas turbine has the vortex double-spraying synergistic function, the gas turbine can be prevented from extremely high temperature, and the service life of the gas turbine is prolonged; the throttle pumps are arranged on the heat collecting pipe, the water adding pipe, the liquid fuel pipe and the nitro solution pipe which are communicated with the flow guide pipe, and the throttle pumps are connected with the control unit, so that the composition and the proportion of the fluid introduced into the through holes can be controlled, and the automatic control is realized.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings that are needed for the description of the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present utility model, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic structural view of the present utility model.
Fig. 2 is a schematic structural view of the housing.
Fig. 3 is a schematic structural view of the front shaft body.
Fig. 4 is a schematic structural view of the rear shaft body and the coupling pump.
Fig. 5 is a schematic structural view of the rear axle body.
The reference numerals are as follows:
1. a housing; 101. an air inlet; 102. a tail nozzle; 2. a front main shaft; 201. a through hole; 3. a fan blade; 4. impeller blades; 5. high pressure turbine blades; 6. a combustion reaction chamber; 7. a fuel nozzle; 8. a branch pipe; 9. a support hole pipe; 10. an injection hole; 11. a rear main shaft; 111. a hole pipe; 12. low pressure turbine blades; 13. a coupling pump; 14. a heat collecting pipe; 15. a flow guiding pipe; 16. a water supply pipe; 17. a liquid fuel pipe; 18. a nitro solution tube; 19. a throttle pump.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present utility model more apparent, the technical solutions of the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model, and it is apparent that the described embodiments are some embodiments of the present utility model, but not all embodiments of the present utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
In the description of the present utility model, it should be understood that the directions or positional relationships indicated by the terms "upper", "lower", "front", "rear", "left", "right", etc., are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present utility model and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present utility model.
As shown in fig. 1 to 5, a gas turbine with double vortex spray synergy and extreme high temperature prevention comprises a shell 1, wherein the front end of the shell 1 is an air inlet 101, and the rear end of the shell 1 is a tail nozzle 102; a front shaft body and a rear shaft body which are coaxial are arranged in the shell 1;
the front shaft body comprises a front main shaft 2, a fan blade 3, an impeller blade 4 and a high-pressure turbine blade 5 are sequentially and fixedly arranged on the front main shaft 2 from front to back, and an axial through hole 201 is formed in the front main shaft 2; a combustion reaction chamber 6 is formed among the impeller blades 4, the high-pressure turbine blades 5 and the shell 1, and a fuel nozzle 7 is arranged in the combustion reaction chamber 6; a branch pipe 8 communicated with the through hole 201 is arranged on the side surface of the front main shaft 2, and the branch pipe 8 is positioned at the front end position of the combustion reaction chamber 6; a supporting hole pipe 9 communicated with the through hole 201 is arranged on the high-pressure turbine blade 5, and an injection hole 10 is arranged at the tail end of the supporting hole pipe 9;
the rear shaft body comprises a rear main shaft 11, a low-pressure turbine blade 12 is fixedly arranged on the rear main shaft 11, a coupling pump 13 is fixedly connected to the front end surface of the rear main shaft 11, a spiral flow guide convex line is arranged on the coupling pump 13, and the coupling pump 13 is positioned in the through hole 201;
the heat collecting tube 14 is arranged in the shell 1, the heat collecting tube 14 is positioned in the area of the combustion reaction chamber 6 and the tail nozzle 102, the heat collecting tube 14 is communicated with one end of the flow guiding tube 15, and the other end of the flow guiding tube 15 is communicated with the through hole 201; the honeycomb duct 15 is connected with a water adding pipe 16 and a liquid fuel pipe 17, cold water is arranged in the water adding pipe 16, liquid fuel is arranged in the liquid fuel pipe 17, and the liquid fuel is aviation kerosene.
When the turbine is used, the machine is started, the fan blades, the impeller blades and the high-pressure turbine blades rotate together, air is fanned between the impeller blades and compressed step by step, the temperature of the compressed air can be correspondingly increased until the temperature exceeds the ignition temperature of fuel, the air can be finally compressed into a combustion reaction chamber, at the moment, the fuel is sprayed out of a fuel nozzle and combusted to generate a large amount of high-temperature and high-pressure gas, the high-pressure gas is rapidly sprayed onto the high-pressure turbine blades and the low-pressure turbine blades, the upper high-pressure turbine blades and the low-pressure turbine blades generate opposite rotation, and the opposite thrust generated by spraying from a tail nozzle at a higher speed is realized, so that the basic turbojet work of the gas turbine is realized. Meanwhile, the water in the heat collecting pipe collects the surplus heat transferred to the shell, so that the temperature of the heat collecting pipe is greatly increased, the heat is close to a critical state, and then the heat and liquid fuel and cold water flow into the through holes through the diversion pipe, wherein part of compressed air after being compressed flows into the through holes from the diversion pipe, and the compressed air and mixed liquid entering into the diversion pipe are conveyed into the hole pipe and the branch hole pipe through the coupling pump, under the action of high temperature, the water is quickly vaporized, the fuel and the air are combusted to form high-pressure air flow, and finally the high-pressure air flow is sprayed out from the spray hole, so that the high-pressure turbine rotates, and the effect of rotary spraying and the effect of controlling the temperature are achieved.
The utility model not only can reduce the temperature of the gas turbine material, but also can convert the collected heat into kinetic energy to act on the high-pressure turbine blade and the low-pressure turbine blade, so that the rotary spraying is generated, the energy utilization efficiency is improved, the gas turbine has the vortex double-spraying synergistic function, the gas turbine can be prevented from extremely high temperature, and the service life of the gas turbine is prolonged.
The coupling pump 13 is located behind the branch pipe 8 to facilitate the transportation of the mixed liquid and air into the branch pipe.
The rear main shaft 11 is provided with a hole pipe 111 communicated with the through hole 201, the low-pressure turbine blade 12 is provided with a branch hole pipe 9 communicated with the hole pipe 111, and the tail end of the branch hole pipe 9 is provided with an injection hole 10. Spin-spraying can also be produced on the low-pressure turbine.
The high-pressure turbine blade 5 and the low-pressure turbine blade 12 are provided with a plurality of injection holes 10, and all the injection holes 10 are communicated with the branch hole pipe 9. The high-pressure turbine blade and the low-pressure turbine blade can be stressed more uniformly, and the plurality of injection holes are more beneficial to exhausting the fuel gas.
The heat collecting tube 14 is spirally arranged, so that the length of the heat collector is increased, the contact area between the heat collecting tube and the high-pressure turbine area and the contact area between the heat collecting tube and the low-pressure turbine area are increased, and more heat can be absorbed.
The honeycomb duct 15 is further connected with a nitro-solution tube 18, and a nitro-solution is arranged in the nitro-solution tube 18, and the nitro-solution is ammonium nitrate solution. The ammonium nitrate solution and other fluids are conveyed into the hole pipe and the branch hole pipe of the high temperature area by the coupling pump, and are gasified under the action of high temperature, so that the nitro solute separated from the water can be decomposed violently under the high temperature environment of more than 400 ℃ to generate gas with the volume of thousands times more than the volume of the nitro solute per se, and the gas forms larger air pressure. Wherein each ammonium nitrate molecule is decomposed to produce gas which contains nitrogen, nitrogen dioxide and water, wherein the nitrogen dioxide is taken as an oxidant to promote the combustion of fuel, thereby improving the rotary spraying effect.
The flow guide pipe 15, the water adding pipe 16, the liquid fuel pipe 17 and the nitro solution pipe 18 are all provided with throttle pumps 19, and the throttle pumps 19 are connected with a control unit, so that automatic control is convenient to realize.
A tesla valve is arranged in the front section of the through hole 201 and the branch pipe 8, and the tesla valve can enable air and water vapor to flow only in one direction and not flow reversely.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present utility model. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the utility model. Thus, the present utility model is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims (9)

1. A gas turbine engine with double vortex spray synergy and extreme high temperature prevention, characterized in that: the device comprises a shell (1), wherein the front end of the shell (1) is provided with an air inlet (101), and the rear end of the shell (1) is provided with a tail nozzle (102); a front shaft body and a rear shaft body which are coaxial are arranged in the shell (1);
the front shaft body comprises a front main shaft (2), a fan blade (3), an impeller blade (4) and a high-pressure turbine blade (5) are sequentially and fixedly arranged on the front main shaft (2) from front to back, and an axial through hole (201) is formed in the front main shaft (2); a combustion reaction chamber (6) is formed among the impeller blades (4), the high-pressure turbine blades (5) and the shell (1), and a fuel nozzle (7) is arranged in the combustion reaction chamber (6); the side surface of the front main shaft (2) is provided with a branch pipe (8) communicated with the through hole (201), and the branch pipe (8) is positioned at the front end position of the combustion reaction chamber (6); a supporting hole pipe (9) communicated with the through hole (201) is arranged on the high-pressure turbine blade (5), and an injection hole (10) is arranged at the tail end of the supporting hole pipe (9);
the rear shaft body comprises a rear main shaft (11), a low-pressure turbine blade (12) is fixedly arranged on the rear main shaft (11), a coupling pump (13) is fixedly connected to the front end face of the rear main shaft (11), a spiral flow guide convex pattern is arranged on the coupling pump (13), and the coupling pump (13) is positioned in the through hole (201);
a heat collecting pipe (14) is arranged in the shell (1), the heat collecting pipe (14) is positioned in the area of the combustion reaction chamber (6) and the tail nozzle (102), the heat collecting pipe (14) is communicated with one end of a flow guiding pipe (15), and the other end of the flow guiding pipe (15) is communicated with a through hole (201); the guide pipe (15) is connected with a water adding pipe (16) and a liquid fuel pipe (17), cold water is arranged in the water adding pipe (16), and liquid fuel is arranged in the liquid fuel pipe (17).
2. A gas turbine for swirl double-injection efficiency enhancement and extreme high temperature prevention as in claim 1, wherein: the coupling pump (13) is positioned behind the branch pipe (8).
3. A gas turbine for swirl double-injection efficiency enhancement and extreme high temperature prevention as in claim 1, wherein: the rear main shaft (11) is provided with a hole pipe (111) communicated with the through hole (201), the low-pressure turbine blade (12) is provided with a branch hole pipe (9) communicated with the hole pipe (111), and the tail end of the branch hole pipe (9) is provided with an injection hole (10).
4. A gas turbine for swirl double-injection efficiency enhancement and extreme high temperature prevention as in claim 3 wherein: a plurality of injection holes (10) are formed in the high-pressure turbine blade (5) and the low-pressure turbine blade (12), and all the injection holes (10) are communicated with the branch hole pipe (9).
5. A gas turbine for swirl double-injection efficiency enhancement and extreme high temperature prevention as in claim 1, wherein: the heat collecting pipes (14) are spirally arranged.
6. A gas turbine for swirl double-injection efficiency enhancement and extreme high temperature prevention as in claim 1, wherein: the honeycomb duct (15) is also connected with a nitro solution tube (18), and a nitro solution is arranged in the nitro solution tube (18).
7. A gas turbine for enhanced dual swirl injection and protection against extreme high temperatures in accordance with claim 6 wherein: the liquid fuel is aviation kerosene, and the nitro solution is ammonium nitrate solution.
8. A gas turbine for enhanced dual swirl injection and protection against extreme high temperatures in accordance with claim 6 wherein: throttle pumps (19) are arranged on the guide pipe (15), the water adding pipe (16), the liquid fuel pipe (17) and the nitro solution pipe (18), and the throttle pumps (19) are connected with a control unit.
9. A gas turbine for swirl double-injection efficiency enhancement and extreme high temperature prevention as in claim 1, wherein: tesla valves are arranged in the front section of the through hole (201) and the branch pipe (8).
CN202121010667.1U 2021-05-12 2021-05-12 Vortex double-spray synergistic gas turbine capable of preventing extreme high temperature Active CN219529158U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202121010667.1U CN219529158U (en) 2021-05-12 2021-05-12 Vortex double-spray synergistic gas turbine capable of preventing extreme high temperature

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Application Number Priority Date Filing Date Title
CN202121010667.1U CN219529158U (en) 2021-05-12 2021-05-12 Vortex double-spray synergistic gas turbine capable of preventing extreme high temperature

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113175392A (en) * 2021-05-12 2021-07-27 刘贽维 Vortex double-spraying synergistic gas turbine capable of preventing extreme high temperature

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113175392A (en) * 2021-05-12 2021-07-27 刘贽维 Vortex double-spraying synergistic gas turbine capable of preventing extreme high temperature

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