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CN113175392A - Vortex double-spraying synergistic gas turbine capable of preventing extreme high temperature - Google Patents

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

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Publication number
CN113175392A
CN113175392A CN202110518402.0A CN202110518402A CN113175392A CN 113175392 A CN113175392 A CN 113175392A CN 202110518402 A CN202110518402 A CN 202110518402A CN 113175392 A CN113175392 A CN 113175392A
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CN
China
Prior art keywords
pipe
hole
gas turbine
main shaft
pressure turbine
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Pending
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CN202110518402.0A
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Chinese (zh)
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刘贽维
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Individual
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Priority to CN202110518402.0A priority Critical patent/CN113175392A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/32—Non-positive-displacement machines or engines, e.g. steam turbines with pressure velocity transformation exclusively in rotor, e.g. the rotor rotating under the influence of jets issuing from the rotor, e.g. Heron turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D19/00—Starting of machines or engines; Regulating, controlling, or safety means in connection therewith
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
    • F02C3/30—Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases
    • F02C3/305—Increasing the power, speed, torque or efficiency of a gas turbine or the thrust of a turbojet engine by injecting or adding water, steam or other fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A gas turbine with vortex double-spraying synergy and extreme high temperature prevention comprises a shell, wherein 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, 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, the rear main shaft is fixedly provided with low-pressure turbine blades, and the front end face of the rear main shaft is fixedly connected with a coupling pump; and a heat collecting pipe is arranged in the shell and is communicated with one end of the flow guide pipe, and the other end of the flow guide pipe is communicated with the through hole. The invention can not only reduce the temperature of the gas turbine material, but also convert the collected heat into kinetic energy to act on the high-pressure turbine blade and the low-pressure turbine blade to generate the rotary spraying, thereby improving the utilization efficiency of the energy, enabling the gas turbine to have the function of improving the efficiency of the vortex double-spraying, preventing the gas turbine from generating the extremely high temperature condition, and prolonging the service life of the gas turbine.

Description

Vortex double-spraying synergistic gas turbine capable of preventing extreme high temperature
Technical Field
The invention belongs to the technical field of gas turbines, and particularly relates to a gas turbine with vortex double-spraying synergistic effect and capability of preventing extreme high temperature.
Background
The gas turbine is a heat engine with remarkable effect, and is widely applied to space shuttles and ocean warships in various forms such as turbofan, turboprop, turbojet and turboshaft. The mechanical kinetic energy fed back by the turbine is used for driving a front-end fan and a multi-stage air compression impeller to compress air at a high ratio and input the compressed air into a combustion reaction chamber, the compressed air is mixed with fuel to be combusted to generate a large amount of high-temperature and high-pressure gas, the high-temperature and high-pressure gas acts on a high-pressure turbine and a low-pressure turbine at a high speed to generate high-speed rotation and high-speed ejection of the gas out of a tail nozzle to generate corresponding reverse thrust, and therefore energy conversion is achieved and continuous normal operation of the machine is maintained. However, the existing gas turbine uses the high-temperature and high-pressure gas generated by the combustion of fuel to impact the turbine to generate rotation and the gas is ejected out of the tail nozzle at high speed to realize energy conversion, so that the core components of the gas turbine are inevitably operated in a high-temperature severe environment, and the service life of the gas turbine and the improvement of power are seriously jeopardized. Even if expensive high-temperature resistant materials such as tungsten, rhenium, nickel-based alloy and the like are adopted, in the face of continuous ignition, for example, the temperature of high-heat value fuel during deflagration in an oxygen-enriched environment with high compression ratio is as high as 1500 ℃ to 2500 ℃, and the temperature approaches the high temperature of a blue flame zone which cannot be endured by machine materials, so that the normal operation of the machine is directly damaged.
Disclosure of Invention
The invention aims to provide a gas turbine with vortex double-spraying effect and extreme high temperature prevention, and solves the problems in the background technology.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows: a gas turbine with vortex double-spraying for increasing efficiency and preventing extreme high temperature 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, the front main shaft is fixedly provided with fan blades, impeller blades and high-pressure turbine blades from front to back in sequence, 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; a branch guide pipe communicated with the through hole is arranged on the side surface of the front main shaft and is positioned at the front end of the combustion reaction chamber; a branch hole pipe communicated with the through hole is arranged on the high-pressure turbine blade, and a jet hole is formed in the tail end of the branch 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 pattern is arranged on the coupling pump, and the coupling pump is located in the through hole;
the shell is internally provided with a heat collecting pipe, the heat collecting pipe is positioned in the combustion reaction chamber and the tail nozzle area, the heat collecting pipe is communicated with one end of a flow guide pipe, and the other end of the flow guide pipe is communicated with the through hole; the honeycomb duct is connected with a water feeding pipe and a liquid fuel pipe, cold water is arranged in the water feeding pipe, and liquid fuel is arranged in the liquid fuel pipe.
On the basis of and as a preferred version of the above solution, the coupling pump is located after the branch duct.
On the basis of the scheme, and as a preferable scheme of the scheme, a hole pipe communicated with the through hole is arranged on the rear main shaft, a branch hole pipe communicated with the hole pipe is arranged on the low-pressure turbine blade, and a jet hole is formed in the tail end of the branch hole pipe.
On the basis of the scheme, and as a preferable scheme of the scheme, a plurality of injection holes are formed in the high-pressure turbine blade and the low-pressure turbine blade, and all the injection holes are communicated with the branch hole pipe.
On the basis of the scheme and as a preferable scheme of the scheme, the heat collecting pipes are spirally arranged.
On the basis of the above scheme and as a preferable scheme of the above scheme, the guide pipe is further connected with a nitro solution pipe, and a nitro solution is arranged in the nitro solution pipe.
On the basis of the scheme, the preferable scheme is that the liquid fuel is aviation kerosene, and the nitro solution is ammonium nitrate solution.
On the basis of the above scheme and as a preferable scheme of the above scheme, the flow guide pipe, the water feeding pipe, the liquid fuel pipe and the nitro-group solution pipe are all provided with flow regulating pumps, and the flow regulating pumps are connected with the control unit.
On the basis of the above scheme and as a preferable scheme of the above scheme, tesla valves are arranged in the front section of the through hole and the branch conduit.
The invention has the following beneficial effects: the invention not only can reduce the temperature of the material of the gas turbine, but also can convert the collected heat into kinetic energy to act on the high-pressure turbine blade and the low-pressure turbine blade to generate the rotary spraying, thereby improving the utilization efficiency of the energy, so that the gas turbine has the function of improving the efficiency of the vortex double-spraying, and the gas turbine can be prevented from generating the extremely high temperature condition, thereby prolonging the service life of the gas turbine; the heat collecting pipe, the water adding pipe, the liquid fuel pipe and the nitro-solvent pipe which are communicated with the flow guide pipe are all provided with flow-saving pumps, and the flow-saving pumps are connected with the control unit, so that the components 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 invention, the drawings used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a schematic structural diagram of the housing.
FIG. 3 is a schematic view of the front axle body.
Fig. 4 is a schematic view of the structure of the rear shaft body and the coupling pump.
Fig. 5 is a schematic structural view of the rear axle body.
The reference numbers are as follows:
1. a housing; 101. an air inlet; 102. a tail spout; 2. a front main shaft; 201. a through hole; 3. a fan blade; 4. an impeller blade; 5. a high pressure turbine blade; 6. a combustion reaction chamber; 7. a fuel nozzle; 8. a branch conduit; 9. a branched pipe; 10. an injection hole; 11. a rear main shaft; 111. a perforated pipe; 12. a low pressure turbine blade; 13. a coupling pump; 14. a heat collecting pipe; 15. a flow guide pipe; 16. a water feeding pipe; 17. a liquid fuel pipe; 18. a nitro solution tube; 19. a flow-saving pump.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.
As shown in fig. 1 to 5, a gas turbine with vortex double-injection for enhancing efficiency and preventing extreme high temperature includes a casing 1, an air inlet 101 is arranged at the front end of the casing 1, and a tail nozzle 102 is arranged at the rear end of the casing 1; 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 conduit 8 communicated with the through hole 201 is arranged on the side surface of the front main shaft 2, and the branch conduit 8 is positioned at the front end of the combustion reaction chamber 6; a branch hole pipe 9 communicated with the through hole 201 is arranged on the high-pressure turbine blade 5, and a jet hole 10 is arranged at the tail end of the branch hole pipe 9;
the rear shaft body comprises a rear main shaft 11, low-pressure turbine blades 12 are 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, spiral flow guide ribs are arranged on the coupling pump 13, and the coupling pump 13 is located in a through hole 201;
a heat collecting pipe 14 is arranged in the shell 1, the heat collecting pipe 14 is positioned in the combustion reaction chamber 6 and the area of the tail nozzle 102, the heat collecting pipe 14 is communicated with one end of a flow guide pipe 15, and the other end of the flow guide pipe 15 is communicated with the through hole 201; the guide pipe 15 is connected with a water feeding pipe 16 and a liquid fuel pipe 17, cold water is arranged in the water feeding pipe 16, liquid fuel is arranged in the liquid fuel pipe 17, and the liquid fuel is aviation kerosene.
When the turbine engine is used, firstly, the machine is started, the fan blades, the impeller blades and the high-pressure turbine blades rotate together, air is blown into the space between the impeller blades and is compressed step by step, the temperature of the compressed air can be correspondingly raised until the temperature of the compressed air exceeds the ignition point temperature of fuel, the air is finally compressed into the combustion reaction chamber, at the moment, the fuel nozzle sprays out the fuel, the fuel is combusted to generate a large amount of high-temperature high-pressure fuel gas and quickly sprayed onto the high-pressure turbine blades and the low-pressure turbine blades, the high-pressure turbine blades and the low-pressure turbine blades rotate oppositely, and then the high-pressure turbine blades and the low-pressure turbine blades spray out from the tail nozzle at a higher speed to generate reverse thrust, so that the basic turbojet work of the gas turbine is realized. Meanwhile, the water in the heat collecting pipe collects the redundant heat transferred to the shell, so that the temperature of the heat collecting pipe is greatly increased, the heat collecting pipe and liquid fuel oil and cold water flow into the through hole through the flow guiding pipe after approaching a critical state, part of compressed air flows into the through hole from the branch flow guiding pipe and is conveyed to the hole pipe and the branch hole pipe together with mixed liquid entering the flow guiding pipe through the coupling pump, the water is quickly vaporized under the action of high temperature, the fuel oil and the air are combusted to form high-pressure air flow, and the high-pressure air flow is finally 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 invention can not only reduce the temperature of the gas turbine material, but also convert the collected heat into kinetic energy to act on the high-pressure turbine blade and the low-pressure turbine blade to generate the rotary spraying, thereby improving the utilization efficiency of the energy, enabling the gas turbine to have the function of improving the efficiency of the vortex double-spraying, preventing the gas turbine from generating the extremely high temperature condition, and prolonging the service life of the gas turbine.
The coupling pump 13 is located after the branch pipes 8 to facilitate the delivery of the mixed liquid and air into the branch pipes.
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 a jet hole 10. So that the low-pressure turbine can also generate rotary spraying.
The high-pressure turbine blades 5 and the low-pressure turbine blades 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 favorable for discharging fuel gas.
The heat collecting pipes 14 are spirally arranged, so that the length of the heat collector is increased, the contact areas of the heat collecting pipes with a high-pressure turbine area and a low-pressure turbine area are increased, and more heat can be absorbed.
The draft tube 15 is also connected with a nitro solution tube 18, a nitro solution is arranged in the nitro solution tube 18, and the nitro solution is an ammonium nitrate solution. The ammonium nitrate solution and other fluids are conveyed to the pore pipe and branch pore pipe in the high temperature region by a coupling pump, water is vaporized under the action of high temperature, and the dehydrated nitro solute can be violently decomposed under the high temperature environment of more than 400 ℃, so that gas with the volume being more than thousands of times of the volume of the gas is generated, and higher air pressure is formed. Wherein, the gas produced by decomposing each ammonium nitrate molecule contains nitrogen, nitrogen dioxide and water, wherein the nitrogen dioxide is taken as an oxidant and can promote the combustion of fuel, thereby improving the rotary spraying effect.
The draft tube 15, the water adding tube 16, the liquid fuel tube 17 and the nitro-group solution tube 18 are all provided with flow-saving pumps 19, and the flow-saving pumps 19 are connected with the control unit, so that automatic control is convenient to realize.
The front section of the through hole 201 and the branch conduit 8 are provided with a Tesla valve which enables air and water vapor to flow only in one direction and not in the reverse direction.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. 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 invention. Thus, the present invention 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 vortex dual-injection gas turbine for increasing efficiency and preventing extreme high temperature is characterized in that: the air inlet structure 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); a branch conduit (8) communicated with the through hole (201) is arranged on the side surface of the front main shaft (2), and the branch conduit (8) is positioned at the front end of the combustion reaction chamber (6); a branch hole pipe (9) communicated with the through hole (201) is arranged on the high-pressure turbine blade (5), and a jet hole (10) is arranged at the tail end of the branch hole pipe (9);
the rear shaft body comprises a rear main shaft (11), low-pressure turbine blades (12) are 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), spiral flow guide ribs are arranged on the coupling pump (13), and the coupling pump (13) is located in the through hole (201);
a heat collecting pipe (14) is arranged in the shell (1), the heat collecting pipe (14) is located in a combustion reaction chamber (6) and a tail nozzle (102) area, the heat collecting pipe (14) is communicated with one end of a flow guide pipe (15), and the other end of the flow guide pipe (15) is communicated with a through hole (201); the water-cooling device is characterized in that a water adding pipe (16) and a liquid fuel pipe (17) are connected to the flow guide pipe (15), 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 engine with increased efficiency and protection against extreme high temperatures by dual swirl injection as claimed in claim 1, wherein: the coupling pump (13) is located after the branch pipe (8).
3. A gas turbine engine with increased efficiency and protection against extreme high temperatures by dual swirl injection as claimed 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 a jet hole (10).
4. A gas turbine engine with increased efficiency and protection against extreme high temperatures by dual swirl injection as claimed in claim 3, wherein: the high-pressure turbine blades (5) and the low-pressure turbine blades (12) are provided with a plurality of injection holes (10), and all the injection holes (10) are communicated with the branch hole pipes (9).
5. A gas turbine engine with increased efficiency and protection against extreme high temperatures by dual swirl injection as claimed in claim 1, wherein: the heat collecting pipes (14) are spirally arranged.
6. A gas turbine engine with increased efficiency and protection against extreme high temperatures by dual swirl injection as claimed in claim 1, wherein: the guide pipe (15) is also connected with a nitro-solution pipe (18), and a nitro-solution is arranged in the nitro-solution pipe (18).
7. A gas turbine engine of claim 6 wherein said dual swirl jets increase efficiency and prevent extreme high temperatures: the liquid fuel is aviation kerosene, and the nitro solution is ammonium nitrate solution.
8. A gas turbine engine of claim 6 wherein said dual swirl jets increase efficiency and prevent extreme high temperatures: the flow guide pipe (15), the water adding pipe (16), the liquid fuel pipe (17) and the nitro-group solution pipe (18) are all provided with flow-saving pumps (19), and the flow-saving pumps (19) are connected with the control unit.
9. A gas turbine engine with increased efficiency and protection against extreme high temperatures by dual swirl injection as claimed in claim 1, wherein: tesla valves are arranged in the front section of the through hole (201) and the branch guide pipe (8).
CN202110518402.0A 2021-05-12 2021-05-12 Vortex double-spraying synergistic gas turbine capable of preventing extreme high temperature Pending CN113175392A (en)

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Application Number Priority Date Filing Date Title
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Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB765350A (en) * 1954-04-21 1957-01-09 Florencio Bienvenido Casale Improvements relating to continuous combustion gas turbine power units
US20110005196A1 (en) * 2009-07-10 2011-01-13 Andersen Leonard M Method and apparatus for increasing thrust or other useful energy output of a device with a rotating element
US20150135722A1 (en) * 2013-11-18 2015-05-21 Mitsubishi Hitchi Power Systems, Ltd. System and method of controlling a two-shaft gas turbine
CN104712431A (en) * 2014-11-30 2015-06-17 李启山 High-pressure flame water-cooling gasification supercharging turbine engine
CN107725192A (en) * 2017-10-18 2018-02-23 福建亿谷新能源有限公司 New energy turbogenerator
CN207437204U (en) * 2017-08-21 2018-06-01 迟多功 Hybrid gas turbine
CN112502834A (en) * 2020-12-12 2021-03-16 赵军 Rotary combustion jet engine
CN219529158U (en) * 2021-05-12 2023-08-15 刘贽维 A gas turbine with vortex double-injection boosting efficiency and preventing extreme high temperature

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB765350A (en) * 1954-04-21 1957-01-09 Florencio Bienvenido Casale Improvements relating to continuous combustion gas turbine power units
US20110005196A1 (en) * 2009-07-10 2011-01-13 Andersen Leonard M Method and apparatus for increasing thrust or other useful energy output of a device with a rotating element
US20150135722A1 (en) * 2013-11-18 2015-05-21 Mitsubishi Hitchi Power Systems, Ltd. System and method of controlling a two-shaft gas turbine
CN104712431A (en) * 2014-11-30 2015-06-17 李启山 High-pressure flame water-cooling gasification supercharging turbine engine
CN207437204U (en) * 2017-08-21 2018-06-01 迟多功 Hybrid gas turbine
CN107725192A (en) * 2017-10-18 2018-02-23 福建亿谷新能源有限公司 New energy turbogenerator
CN112502834A (en) * 2020-12-12 2021-03-16 赵军 Rotary combustion jet engine
CN219529158U (en) * 2021-05-12 2023-08-15 刘贽维 A gas turbine with vortex double-injection boosting efficiency and preventing extreme high temperature

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