CN110685817A - Turbofan engine and aircraft - Google Patents
Turbofan engine and aircraft Download PDFInfo
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- CN110685817A CN110685817A CN201910961284.3A CN201910961284A CN110685817A CN 110685817 A CN110685817 A CN 110685817A CN 201910961284 A CN201910961284 A CN 201910961284A CN 110685817 A CN110685817 A CN 110685817A
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- turbine
- sco
- compressor
- regenerator
- heater
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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
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- 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
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/08—Adaptations for driving, or combinations with, pumps
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- 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
- F01D25/10—Heating, e.g. warming-up before starting
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- 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
- F01D25/12—Cooling
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K23/00—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids
- F01K23/02—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled
- F01K23/06—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle
- F01K23/10—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle with exhaust fluid of one cycle heating the fluid in another cycle
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K25/00—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for
- F01K25/08—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for using special vapours
- F01K25/10—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for using special vapours the vapours being cold, e.g. ammonia, carbon dioxide, ether
- F01K25/103—Carbon dioxide
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K7/00—Steam engine plants characterised by the use of specific types of engine; Plants or engines characterised by their use of special steam systems, cycles or processes; Control means specially adapted for such systems, cycles or processes; Use of withdrawn or exhaust steam for feed-water heating
- F01K7/32—Steam engine plants characterised by the use of specific types of engine; Plants or engines characterised by their use of special steam systems, cycles or processes; Control means specially adapted for such systems, cycles or processes; Use of withdrawn or exhaust steam for feed-water heating the engines using steam of critical or overcritical pressure
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- 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
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- 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
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
- F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
Abstract
The invention provides a turbofan engine and an aircraft, the turbofan engine comprises: cooler, compressor, heat regenerator, heater, turbine, speed reducer, fanThe turbine is connected with the compressor through a rigid shaft, the turbine is connected with the fan through the speed reducer, the fan is used for supercharging sucked air and discharging the supercharged air through the tail nozzle to generate the thrust of the turbofan engine, and SCO is used for increasing the pressure of the sucked air2The Brayton cycle is combined with the structure of the turbofan engine, so that the size of the turbofan engine is more compact, the heat efficiency is higher, namely the oil consumption rate of the engine is lower, the service life of the turbofan engine is longer, and the requirement on the fuel heat value is reduced.
Description
Technical Field
The invention relates to the field of aviation, in particular to a turbofan engine and an aircraft.
Background
Aircraft engines are important components of aircraft and currently in use include turbojet engines, turbofan engines, turboshaft engines, turboprop engines, and the like. Among them, the turbofan engine is also called a turbofan engine, which is a gas turbine engine in which gas ejected from a nozzle and air discharged from a fan generate a reaction thrust together.
In the prior art, a turbofan engine mainly comprises a fan, a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine and an exhaust system, wherein air compressed by the high-speed rotating fan is divided into two parts by a flow dividing device, one part of the air enters an inner duct, the other part of the air is subjected to an outer duct, the air entering the inner duct is continuously compressed in the compressor and then enters the combustion chamber to be rapidly mixed with fuel, high-temperature and high-pressure gas is formed after the air is ignited, the gas drives the compressor to rotate through the high-pressure turbine, the gas leaving the high-pressure turbine continues to expand and work in the low-pressure turbine to drive the fan to rotate, and the gas passing through the low-pressure turbine is discharged out of the engine.
However, the outlet temperature of the combustion chamber of the prior turbofan engine is about 1400 ℃, the bypass ratio is large, and the temperature born by the high-pressure turbine is 1100-1300 ℃, so that the size of the turbofan engine is relatively large, the service life is relatively short, the thermal efficiency is low (namely, the fuel consumption rate is high), and the requirement on the calorific value of fuel is high.
Disclosure of Invention
The invention provides a turbofan engine and an aircraft, which are used for solving the problems of low thermal efficiency, short service life and high requirement on the heat value of fuel of the turbofan engine in the prior art.
In a first aspect, the present invention provides a turbofan engine comprising:
a cooler, a compressor, a regenerator, a heater, a turbine, a speed reducer, a fan, a tailpipe, and a casing;
the turbine is connected with the compressor through a rigid shaft; the turbine is connected with the fan through the speed reducer; the speed reducer is used for adjusting the rotating speed ratio between the turbine and the fan; the fan is used for pressurizing sucked air and discharging the pressurized air through the tail nozzle to generate thrust of the turbofan engine;
the cooler is arranged on the surface of the casing, the output end of the cooler is connected with the input end of the compressor through a pipeline, the output end of the compressor is connected with the first input end of the heat regenerator through a pipeline, the first output end of the heat regenerator is connected with the input end of the heater through a pipeline, the output end of the heater is connected with the input end of the turbine through a pipeline, the output end of the turbine is connected with the second input end of the heat regenerator through a pipeline, and the second output end of the heat regenerator is connected with the input end of the cooler through a pipeline;
the cooler couples supercritical carbon dioxide (SCO) during operation of the turbofan engine2) SCO cooled and brought to the compressor inlet conditions2Feeding into the compressor;
the compressor couples the cooled SCO2Pressurizing, and adding the pressurized SCO2Conveying the waste heat into the regenerator;
the heat regenerator pairSCO after pressurization2Preheating and adding the preheated SCO2Is delivered to the heater;
the heater pair SCO2Heating, and mixing the heated SCO2Feeding into the turbine;
the turbine utilizes SCO at high temperature and pressure2Doing work, driving the compressor and the fan to rotate, and the turbine will do work on the SCO2Flowing out into the regenerator;
the regenerator is paired with used SCO2Pre-cooling, and pre-cooling SCO2Flows back into the cooler.
Optionally, the regenerator and the heater are both ring-shaped, each being fixed on a rigid shaft between the compressor and the turbine.
Optionally, the regenerator is two symmetrical blocks symmetrically arranged on two sides of a rigid shaft between the compressor and the turbine;
optionally, the heater is two symmetrical pieces, symmetrically disposed on either side of a rigid shaft between the compressor and the turbine.
In a second aspect, the present invention provides a turbofan engine comprising:
the system comprises a cooler, a compressor, a heat regenerator, a first heater, a second heater, a first turbine, a second turbine, a speed reducer, a fan, a tail pipe and a casing;
the first turbine is connected with the fan through the speed reducer; the speed reducer is used for adjusting a rotating speed ratio between the first turbine and the fan; the fan is used for pressurizing sucked air and discharging the pressurized air through the tail nozzle to generate thrust of the turbofan engine;
the second turbine is connected with the compressor through a rigid shaft;
the cooler is arranged on the surface of the casing, the output end of the cooler is connected with the input end of the compressor through a pipeline, the output end of the compressor is connected with the first input end of the heat regenerator through a pipeline, the first output end of the heat regenerator is connected with the input end of the first heater through a pipeline, the output end of the first heater is connected with the input end of the second turbine through a pipeline, the output end of the second turbine is connected with the input end of the second heater through a pipeline, the output end of the second heater is connected with the input end of the first turbine through a pipeline, the output end of the first turbine is connected with the second input end of the heat regenerator through a pipeline, and the second output end of the heat regenerator is connected with the input end of the cooler through a pipeline;
when the turbofan engine works, the cooler is paired with SCO2SCO cooled and brought to the compressor inlet conditions2Feeding into the compressor;
the compressor couples the cooled SCO2Pressurizing, and adding the pressurized SCO2Conveying the waste heat into the regenerator;
the regenerator couples the pressurized SCO2Preheating and adding the preheated SCO2Feeding to the first heater;
the first heater pair SCO2Heating, and mixing the heated SCO2Feeding into the second turbine;
the second turbine utilizes SCO at high temperature and high pressure2Doing work, driving the compressor to rotate and enabling the SCO after doing work to be used2Flowing out into the second heater;
the second heater couples SCO flowing from the second turbine2Heating, and mixing the heated SCO2Feeding into the first turbine;
the first turbine utilizes SCO at high temperature and high pressure2Doing work, driving the fan to rotate, and enabling the first turbine to do work and obtain SCO2Out into the regenerator, wherein SCO entering the first turbine2Is higher than the SCO entering the second turbine2The temperature of (a);
the heat regenerationFor SCO flowing from the first turbine2Pre-cooling, and pre-cooling SCO2And flows back into the cooler.
Optionally, the regenerator and the first heater are both ring-shaped, each being fixed on a rigid shaft between the compressor and the second turbine.
Optionally, the regenerator is a symmetrical two-piece regenerator symmetrically disposed on either side of a rigid shaft between the compressor and the second turbine.
Optionally, the first heater is symmetrically two pieces, symmetrically disposed on both sides of a rigid shaft between the compressor and the second turbine.
Optionally, the second heater is annular or symmetrical two pieces, the second heater being disposed between the first turbine and the second turbine.
Optionally, the cooler is a printed circuit board air cooler.
Optionally, the fan comprises: duct fan and Flade fan, the Flade fan is connected on the duct fan.
In a third aspect, the present invention provides a turbofan engine comprising:
the system comprises a cooler, a first compressor, a second compressor, a first regenerator, a second regenerator, a first heater, a second heater, a first turbine, a second turbine, a speed reducer, a fan, a tail pipe and a casing;
the first turbine is connected with the fan through the speed reducer; the speed reducer is used for adjusting a rotating speed ratio between the first turbine and the fan; the fan is used for pressurizing sucked air and discharging the pressurized air through the tail nozzle to generate thrust of the turbofan engine;
the second compressor is connected with the second turbine and the first compressor through rigid shafts respectively;
the cooler is arranged on the surface of the casing, the output end of the cooler is connected with the input end of the first compressor through a pipeline, the output end of the first compressor is connected with the first input end of the first regenerator through a pipeline, the first output end of the first regenerator is connected with the first input end of the second regenerator through a pipeline, the first output end of the second regenerator is connected with the input end of the first heater through a pipeline, the output end of the first heater is connected with the input end of the second turbine through a pipeline, the output end of the second turbine is connected with the input end of the second heater through a pipeline, the output end of the second heater is connected with the input end of the first turbine through a pipeline, and the output end of the first turbine is connected with the second input end of the second regenerator through a pipeline, a second output end of the second heat regenerator is connected with a second input end of the first heat regenerator through a pipeline, a second output end of the first heat regenerator is connected with an input end of the cooler through a pipeline, a third output end of the first heat regenerator is connected with an input end of the second compressor through a pipeline, and an output end of the second compressor is connected with a second input end of the second heat regenerator through a pipeline;
when the turbofan engine works, the cooler is paired with SCO2Cooling and bringing the cooling temperature to SCO of the first compressor inlet condition2Feeding into the first compressor;
the first compressor is used for cooling SCO2Pressurizing, and adding the pressurized SCO2Conveying to the first heat regenerator;
the first regenerator is used for pressurizing SCO2Preheating and adding the preheated SCO2Feeding to the second regenerator;
SCO input by the second regenerator to the first regenerator and the second compressor2Re-preheating is carried out, and the re-preheated SCO is2Feeding to the first heater;
the first heater pair SCO2Heating, and mixing the heated SCO2Feeding into the second turbine;
the second turbine wheelUsing SCO at high temperature and pressure2Doing work, driving the first compressor and the second compressor to rotate, and enabling the second turbine to do work on the SCO2Flowing out into the second heater;
the second heater couples SCO flowing from the second turbine2Heating, and mixing the heated SCO2Feeding into the first turbine;
the first turbine utilizes SCO at high temperature and high pressure2Doing work, driving the fan to rotate, and enabling the first turbine to do work and obtain SCO2Flow out into the second regenerator, wherein SCO entering the first turbine2Is higher than the SCO entering the second turbine2The temperature of (a);
the second regenerator couples SCO flowing from the first turbine2Pre-cooling, and mixing the pre-cooled SCO2Conveying to the first heat regenerator;
SCO pre-cooled by the first heat regenerator to the second heat regenerator2Precooling the SCO and precooling the SCO2One part flows back to the cooler and the other part flows into the second compressor; SCO flowing into the second compressor2Recompressed and then fed into the second regenerator.
Optionally, the first recuperator is annular and is fixed on a rigid shaft between the first compressor and the second compressor.
Optionally, the first heat regenerator is symmetrically arranged on two sides of the rigid shaft between the first compressor and the second compressor.
Optionally, the second regenerator and the first heater are both ring-shaped, and are fixed on a rigid shaft between the second compressor and the second turbine, respectively.
Optionally, the second regenerator is a symmetrical two-piece regenerator symmetrically disposed on both sides of the rigid shaft between the second compressor and the second turbine.
Optionally, the first heater is symmetrically two pieces, symmetrically disposed on both sides of a rigid shaft between the second compressor and the second turbine.
Optionally, the second heater is annular or symmetrical two pieces, the second heater being disposed between the first turbine and the second turbine.
Optionally, the cooler is a printed circuit board air cooler.
Optionally, the fan comprises: duct fan and Flade fan, the Flade fan is connected on the duct fan.
In a fourth aspect, the invention provides an aircraft comprising a turbofan engine as described above.
The invention provides a turbofan engine and an aircraft, the turbofan engine comprises: cooler, compressor, regenerator, heater, turbine, speed reducer, fan, nozzle and casing, low temperature and low pressure SCO2After the pressure of the compressor is increased, the heat regenerator is preheated to a certain temperature, the heat regenerator is further heated by a heater, then the heat regenerator enters a turbine to expand and do work to drive the compressor and a fan to rotate, the fan sucks air through rotation and pressurizes the sucked air, the pressurized air is discharged through a tail nozzle to generate the thrust of a turbofan engine, and the SCO doing work generates the thrust of the turbofan engine2Injection regenerator to SCO after use2Pre-cooling, and mixing the pre-cooled SCO2Transferring to cooler for further cooling, and cooling SCO2Re-entering the compressor for the next cycle by recycling SCO2The Brayton cycle is combined with the structure of the turbofan engine, so that the service life of the turbofan engine is prolonged, and the requirement of the turbofan engine on the heat value of fuel is reduced.
Drawings
In order to more clearly illustrate the technical solutions of the present invention or the prior art, the following briefly introduces the drawings needed to be used in the description of the embodiments or the prior art, and obviously, the drawings in the following description are some embodiments of the present invention, and those skilled in the art can obtain other drawings according to the drawings without inventive labor.
FIG. 1 is a schematic diagram of a prior art turbofan engine according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a first turbofan engine according to an embodiment of the present invention;
FIG. 3 is a schematic structural diagram of a second turbofan engine according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a turbofan engine according to a third embodiment of the present invention.
Description of reference numerals:
10-turbofan engine;
11-a cooler;
12-a compressor;
121-a first compressor;
122-a second compressor;
13-a heat regenerator;
131-a first heat regenerator;
132-a second regenerator;
14-a heater;
141-a first heater;
142-a second heater;
15-a turbine;
151-a first turbine;
152-a second turbine;
16-a reducer;
17-a fan;
171-ducted fan;
172-Flade fan;
18-a jet nozzle;
19-a casing;
20-stator blade.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings, 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.
Any one substance exists in three phases: solid, liquid and gaseous states, and at a certain temperature and pressure, the phase state of a substance changes, thereby exhibiting different phase states. The point at which the two phases of the gas and the liquid are in an equilibrium state is called a critical point, the temperature and the pressure corresponding to the critical point are respectively called a critical temperature and a critical pressure, the state of the substance at the critical point is called a critical state, and if the temperature and the pressure of the substance in the critical state are continuously increased, the substance enters a supercritical state when the temperature and the pressure are increased to exceed the critical temperature and the critical pressure.
The brayton cycle is a typical thermodynamic cycle which is firstly proposed by brayton, an american scientist and takes gas as a working medium. The simple Brayton cycle gas working medium realizes high-efficiency energy conversion through four processes of isentropic compression, isobaric heat absorption, isentropic expansion and isobaric cooling. When the working medium is in a supercritical state, the change of the phase state of the working medium is avoided, the consumption of compression work is reduced, and the cycle efficiency of the working medium can be greatly improved.
When CO is present2When the temperature and the pressure of the reaction solution reach the critical temperature of 31.1 ℃ and the critical pressure of 7.38Mpa respectively, CO2The liquid is in a supercritical state, is between liquid and gas, has the special physical characteristics of small gas viscosity and large liquid density, has the typical advantages of good fluidity, high heat transfer efficiency, small compressibility and the like, and uses SCO2As the circulating working medium, the method also has the advantages of good engineering realizability, high circulating efficiency, small occupied area of components and systems, good economic benefit and the like, so that the SCO2Is considered to be one of the most promising brayton cycle working fluids.
The turbofan engine is one of the most commonly used aircraft engines, and in the prior art, the turbofan engine mainly comprises a fan, a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine and an exhaust system, as shown in fig. 1, wherein the high-pressure compressor, the combustion chamber and the high-pressure turbine form a core engine, a part of available energy in gas discharged by the core engine is transmitted to the low-pressure turbine to drive the fan, and the rest part of the available energy is used for accelerating the discharged gas in a nozzle. The fan rotor is actually a compressor with one or more stages of longer blades, air is divided into two paths after flowing through the fan, one path is a culvert air flow, the air is compressed by the compressor continuously and is mixed and combusted with fuel oil in a combustion chamber, the fuel gas is expanded by a turbine and a spray pipe, the fuel gas is discharged from a tail nozzle by regulation to generate thrust, the path of the thrust is that the fuel gas is discharged from the spray pipe through a low-pressure compressor, a high-pressure compressor, the combustion chamber, a high-pressure turbine and a low-pressure turbine, the other path is a culvert air flow, and the air after the fan is directly discharged into the atmosphere through an outer culvert or is discharged together with the culvert fuel gas in the. However, the existing turbofan engine uses fuel oil as a working medium, the outlet temperature of a combustion chamber is about 1400 ℃, so that the requirement on the combustion heat value of the fuel oil is high, the temperature borne by a high-pressure turbine is 1100-.
The invention provides a turbofan engine and an aircraft, which improve the service life of the turbofan engine, reduce the requirement on the heat value of fuel oil, and have a more compact structure compared with the turbofan engine in the prior art, thereby reducing the size of the whole engine.
Fig. 2 is a schematic structural diagram of a first turbofan engine according to an embodiment of the present invention, and as shown in fig. 2, a turbofan engine 10 according to the present embodiment includes:
The turbine 15 is connected with the compressor 12 through a rigid shaft, and the turbine 15 is connected with the fan 17 through a speed reducer 16; the speed reducer 16 is used for adjusting the rotation speed ratio between the turbine 15 and the fan 17, and the fan 17 is used for supercharging the sucked air and discharging the supercharged air through the tail nozzle 18 to generate the thrust of the turbofan engine 10;
the cooler 11 is arranged on the surface of the casing 19, the output end of the cooler 11 is connected with the input end of the compressor 12 through a pipeline, the output end of the compressor 12 is connected with the first input end of the heat regenerator 13 through a pipeline, the first output end of the heat regenerator is connected with the input end of the heater 14 through a pipeline, the output end of the heater 14 is connected with the input end of the turbine 15 through a pipeline, the output end of the turbine 15 is connected with the second input end of the heat regenerator 13 through a pipeline, and the second output end of the heat regenerator 13 is connected with the input end of the cooler 11 through a pipeline.
Wherein the cooler 11 is used for the SCO2For cooling, the cooler 11 usually uses water or air as coolant to remove heat, and for reasonable resource utilization and weight reduction of the whole aircraft engine, the cooler usually uses air as coolant.
In one possible implementation, the cooler 11 is a printed circuit board air cooler.
The cooler 11 in this embodiment may be welded to the casing 19, or may be disposed on the casing 19 in other manners, which is not limited herein.
The compressor 12 is a driven fluid machine for lifting a low-pressure working medium into a high-pressure working medium, in the embodiment of the present invention, the compressor 12 may be a screw compressor, or may also be a centrifugal compressor, an axial compressor, or a centrifugal + axial compressor, or other types of compressors, which the inventor does not limit.
The regenerator 13 is a heat exchange device, and the regenerator 13 in this application has two functions in the cycle, one is SCO for heating the outlet of the compressor 122To save fuel and improve thermal efficiency, one is turbine 15 outlet SCO2To reduce the cooler pair SCO2The power consumption in cooling is performed.
The turbine is also called a turbine, a steam turbine or an expander, and the turbine is a rotary power device, and the SCO with high temperature and high pressure in the embodiment of the invention2Expansion in turbine 15 to convert SCO2The heat energy is converted into mechanical energy, and simultaneously, work is done outwards. SCO2As the turbine 15 expands and accelerates, its pressure and temperature decrease and the speed increases.
The speed reducer 16 is used for reducing the rotating speed and increasing the torque, in the embodiment of the invention, because the rotating speed of the turbine is usually larger and can reach tens of thousands of revolutions per minute, and the rotating speed of the fan is limited by the mechanical strength, the rotating speed ratio between the turbine 15 and the fan 17 is adjusted by arranging the speed reducer 16 between the turbine 15 and the fan 17, so that the functions and the capacities of the turbine 15 and the fan 17 can be better exerted and utilized.
The fan 17 is a device for generating thrust of the turbofan engine 10, and the number of stages, mechanical strength, weight, and operating efficiency of the fan 17 are key factors affecting the performance of the fan.
In one possible implementation, the fans 17 include ducted fans 171 and Flade fans 172 (see fig. 4).
"FLADE" is an abbreviation for "fan-on-blades" (fan-on-blades) that by providing fans 17, including ducted fans and Flade fans, can draw in more air and thereby generate more power for the turbofan engine 10.
Alternatively, when the fan 17 comprises a ducted fan 171 and a Flade fan 172, the turbofan engine 10 further comprises: stator vanes 20 (see fig. 4). The stator vanes 20 are individually adjustable components that are used to regulate the amount of airflow into the Flade duct, thereby providing variable amounts of power to the turbofan engine 10.
The jet nozzle 18 is used to expand the air sufficiently and push it out at high speed, generating a reaction force.
In the embodiment of the present invention, the turbofan engine 10 is cooled when it is operatedCooler 11 to SCO2SCO cooling and bringing the cooling temperature to compressor 12 inlet conditions2Delivered to compressor 12, and compressor 12 couples the cooled SCO2Pressurizing, and adding the pressurized SCO2Is fed into the regenerator 13, and the regenerator 13 pressurizes the SCO2Preheating and adding the preheated SCO2Is delivered to a heater 14, the heater 14 is paired with SCO2Heating, and mixing the heated SCO2Into the turbine 15, the turbine 15 utilizes the SCO at high temperature and high pressure2Work is done, the compressor 12 and the fan 17 are driven to rotate, and the SCO after work is done is driven by the turbine 152Flows out into the regenerator 13, and the regenerator 13 is used for SCO2Pre-cooling, and pre-cooling SCO2And flows back to the cooler 11 to complete the cycle and prepare for entering the next cycle, and during the cycle, the turbine 15 drives the compressor 12 and the fan 17 to do work, so as to provide power for the compressor 12 and the fan 17, ensure the continuous cycle, and ensure that the fan 17 can provide thrust for the turbofan engine 10 continuously.
The shapes of the regenerator 13 and the heater 14 in the embodiment of the present invention can be selected and set according to actual conditions and needs.
In one possible implementation, the regenerator 13 and the heater 14 are both annular and are fixed to a rigid shaft between the compressor and the turbine, respectively.
In another possible implementation, the regenerator 13 is a symmetrical two-piece regenerator, symmetrically disposed on both sides of a rigid shaft between the compressor and the turbine.
In yet another possible implementation, the heater 14 is two symmetrical pieces, and is symmetrically disposed on both sides of a rigid shaft between the compressor and the turbine.
In the embodiment of the invention, the SCO is utilized2A simple regenerative brayton cycle, and the cooler 11, compressor 12, regenerator 13, heater 14 and turbine 15 required to achieve the cycle are provided, and the turbine 15 is connected to the compressor 12 by a rigid shaft, the turbine 15 is connected to the fan 17 by a speed reducer 16,the fan 17 is used for supercharging the sucked air and discharging the supercharged air through the tail nozzle 18 to generate the thrust of the turbofan engine 10, the outlet temperature of the turbine is low (550-700 ℃), the service life of each part of the turbofan engine 10 is prolonged, the service life of the turbofan engine 10 is further prolonged, and the SCO is heated by the heat regenerator 13 and the heater 14 in the invention2The heating has lower requirement on the heat value of the fuel, and in addition, the structure of the embodiment of the invention is more compact compared with the prior art, thereby being beneficial to reducing the size and the weight of the whole machine.
Fig. 3 is a schematic structural diagram of a second turbofan engine according to an embodiment of the present invention, and as shown in fig. 3, in the embodiment of the present invention, a turbofan engine 10 includes:
The first turbine 151 is connected with the fan 17 through a speed reducer 16, the speed reducer 16 is used for adjusting the rotation speed ratio between the first turbine 151 and the fan 17, the fan 17 is used for supercharging sucked air and discharging the supercharged air through the tail nozzle 18 to generate the thrust of the turbofan engine 10; the second turbine 152 is connected to the compressor 12 by a rigid shaft.
The cooler 11 is disposed on the surface of the casing 19, an output end of the cooler 11 is connected to an input end of the compressor 12 through a pipeline, an output end of the compressor 12 is connected to a first input end of the regenerator 13 through a pipeline, a first output end of the regenerator 13 is connected to an input end of the first heater 141 through a pipeline, an output end of the first heater 141 is connected to an input end of the second turbine 152 through a pipeline, an output end of the second turbine 152 is connected to an input end of the second heater 142 through a pipeline, an output end of the second heater 142 is connected to an input end of the first turbine 151 through a pipeline, an output end of the first turbine 151 is connected to a second input end of the regenerator 13 through a pipeline, and a second output end of the regenerator 13 is connected to an input end of the cooler 11 through a pipeline.
The cooler 11, the compressor 12, the regenerator 13, the reducer 16, the fan 17, the exhaust nozzle 18, and the casing 19 are the same as those in the first embodiment, and are not described in detail herein.
The first and second heaters 141 and 142 are used to heat SCO entering the second and first turbines 152 and 151, respectively2The heating is performed, and in one possible implementation, the first heater 141 is a low temperature heater and the second heater 142 is a high temperature heater.
The first turbine 151 and the second turbine 152 are both used to utilize SCO of high temperature and high pressure2Performs expansion work except for SCO entering first turbine 1512Is relatively slightly higher, SCO entering the second turbine 1522Is relatively slightly higher, in one possible implementation the first turbine 151 is a high temperature turbine and the second turbine 152 is a low temperature turbine.
The shapes of the regenerator 13, the first heater 141 and the second heater 142 in the embodiment of the present invention can be selected and set according to actual conditions and needs.
In one possible implementation, regenerator 13 and first heater 141 are both annular and are fixed to a rigid shaft between compressor 12 and second turbine 152, respectively.
In another possible implementation, regenerator 13 is a symmetrical two-piece, symmetrically disposed on either side of a rigid shaft between compressor 12 and second turbine 152.
In yet another possible implementation, the first heater 141 is a symmetrical two-piece, symmetrically disposed on both sides of a rigid shaft between the compressor 12 and the second turbine 152.
In yet another possible implementation, the second heater 142 is annular or symmetrical two pieces, and the second heater 142 is disposed between the first turbine 151 and the second turbine 152.
Through the reasonable selection of the shapes of the devices and the arrangement of the positions of the devices, the turbofan engine has a compact structure and reasonable layout, so as to adapt to different use scenes and reduce the volume of the whole engine.
In the embodiment of the invention, the turbofanWhen the engine 10 is in operation, the cooler 11 is paired with SCO2SCO cooling and bringing the cooling temperature to compressor 12 inlet conditions2Delivered to compressor 12, and compressor 12 couples the cooled SCO2Pressurizing, and adding the pressurized SCO2Is fed into the regenerator 13, and the regenerator 13 pressurizes the SCO2Preheating and adding the preheated SCO2Is supplied to the first heater 141, and the first heater 141 is supplied to SCO2Heating, and mixing the heated SCO2Into the second turbine 152, the second turbine 152 utilizes the SCO at high temperature and high pressure2Doing work, driving the compressor 12 to rotate, and discharging the SCO after doing work2Flows out to the second heater 142, and the second heater 142 couples SCO flowing out from the second turbine 1522Heating, and mixing the heated SCO2Into the first turbine 151, the first turbine 151 utilizes the SCO of high temperature and high pressure2Doing work, driving the fan 17 to rotate, and the first turbine 151 will do work and SCO2Out to regenerator 13, wherein SCO entering first turbine 1512Is higher than the SCO entering the second turbine 1522Temperature of regenerator 13 to SCO flowing from first turbine 1512Pre-cooling, and pre-cooling SCO2Flows back into the cooler 11.
In this embodiment, SCO entering the second turbine 152 is coupled by the first heater 1412Heating occurs due to SCO after work is applied by the second turbine 1522Both the temperature and the pressure of (C) are reduced, thus, at SCO2SCO is heated by the second heater 142 before entering the first turbine 1512Again, heating is performed to meet the work requirements of first turbine 151. In addition, in the present embodiment, the second turbine 152 is rigidly connected to the compressor 12, and the first turbine 151 is connected to the fan 17 through the speed reducer 16, so that the first turbine 151 and the second turbine 152 do work to respectively provide mechanical energy for the compressor 12 and the fan 17 to drive the compressor 12 and the fan 17 to rotateThis example uses SCO twice2Work is done, and the utilization rate of energy is higher.
Fig. 4 is a schematic structural diagram of a third turbofan engine according to an embodiment of the present invention, and as shown in fig. 4, in this embodiment, the turbofan engine 10 includes:
the cooler 11, the first compressor 121, the second compressor 122, the first regenerator 131, the second regenerator 132, the first heater 141, the second heater 142, the first turbine 151, the second turbine 152, the speed reducer 16, the fan 17, the nozzle 18, and the casing 19.
The first turbine 151 is connected to the fan 17 through a speed reducer 16, the speed reducer 16 is used to adjust a rotation speed ratio between the first turbine 151 and the fan 17, and the fan 17 is used to pressurize the intake air and discharge the pressurized air through the jet nozzle 18, thereby generating thrust of the turbofan engine 10.
The second compressor 122 is connected to the second turbine 152 and the first compressor 121 via rigid shafts, respectively.
The cooler 11 is disposed on the surface of the casing 19, an output end of the cooler 11 is connected to an input end of the first compressor 121 through a pipeline, an output end of the first compressor 121 is connected to a first input end of the first regenerator 131 through a pipeline, a first output end of the first regenerator 131 is connected to a first input end of the second regenerator 132 through a pipeline, a first output end of the second regenerator 132 is connected to an input end of the first heater 141 through a pipeline, an output end of the first heater 141 is connected to an input end of the second turbine 152 through a pipeline, an output end of the second turbine 152 is connected to an input end of the second heater 142 through a pipeline, an output end of the second heater 142 is connected to an input end of the first turbine 151 through a pipeline, an output end of the first turbine 151 is connected to a second input end of the second regenerator 132 through a pipeline, a second output end of the second regenerator 132 is connected to a second input end of the first regenerator 131 through a pipeline, a second output end of the first heat regenerator 131 is connected to an input end of the cooler 11 through a pipeline, a third output end of the first heat regenerator 131 is connected to an input end of the second compressor 122 through a pipeline, and an output end of the second compressor 122 is connected to a second input end of the second heat regenerator 132 through a pipeline.
The cooler 11, the first heater 141, the second heater 142, the first turbine 151, the second turbine 152, the speed reducer 16, the fan 17, the exhaust nozzle 18, and the casing 19 are the same as those in the second embodiment, and therefore, detailed description thereof is omitted.
The SCO entering the first heater 141 is coupled by providing the first regenerator 131 and the second regenerator 1322The preheating is performed, and in one possible implementation, the first regenerator 131 is a low-temperature regenerator, and the second regenerator 132 is a high-temperature regenerator. Wherein the first heat regenerator 131 is provided with two input terminals and three output terminals, and the first heat regenerator 131 has a pre-cooled SCO2The function of dividing the flow in proportion is carried out, so that the precooled SCO2One portion enters the cooler 11 and one portion proceeds to the second compressor 122. The second regenerator 132 is provided with two inputs for SCO in the second compressor 122 and the first regenerator 131, respectively, and two outputs2Into the flow of (a).
By setting the first compressor 121 to SCO2Performing primary compression, and setting the second compressor 122 to SCO2Recompression helps to make better use of SCO2Work is done, and therefore the energy utilization rate is improved.
The shapes of the first regenerator 131, the second regenerator 132, the first heater 141 and the second heater 142 according to the embodiment of the present invention may also be selected and configured according to actual situations and needs.
In one possible implementation, the first heat regenerator 131 is ring-shaped, and the first heat regenerator 131 is fixed on a rigid shaft between the first compressor 121 and the second compressor 122.
In another possible implementation, the first heat regenerator 131 is two symmetrical blocks, symmetrically disposed on both sides of the rigid shaft between the first compressor 121 and the second compressor 122.
In yet another possible implementation, the second regenerator 132 and the first heater 141 are both ring-shaped and fixed on a rigid shaft between the second compressor 122 and the second turbine 152, respectively.
In yet another possible implementation, the second regenerator 132 is a symmetrical two-piece, symmetrically disposed on both sides of the rigid shaft between the second compressor 122 and the second turbine 152.
In yet another possible implementation, the first heater 141 is a symmetrical two-piece, symmetrically disposed on both sides of the rigid shaft between the second compressors 122 and 152 and the second turbine.
In yet another possible implementation, the second heater 142 is annular or symmetrical two pieces, and the second heater 142 is disposed between the first turbine 151 and the second turbine 152.
By reasonably selecting the shape of each device and the position of each device, the turbofan engine 10 can be compact in structure and reasonable in layout to adapt to different use scenes, so that the size of the turbofan engine 10 is reduced.
In the embodiment of the present invention, when the turbofan engine 10 is in operation, the cooler 11 is coupled to the SCO2Cooling is performed and the cooling temperature is brought to SCO of inlet condition of the first compressor 1212Delivered to the first compressor 121, and the first compressor 121 compresses the cooled SCO2Pressurizing, and adding the pressurized SCO2Sent to the first heat regenerator 131, and the first heat regenerator 131 pressurizes the SCO2Preheating and adding the preheated SCO2SCO to the second regenerator 132, the second regenerator 132 inputs to the first regenerator 131 and the second compressor 1222Re-preheating is carried out, and the re-preheated SCO is2Is supplied to the first heater 141, and the first heater 141 is supplied to SCO2Heating the SCO after heating2Into the second turbine 152, the second turbine 152 utilizes the SCO at high temperature and high pressure2Work is applied to drive the first compressor 121 and the second compressor 122 to rotate, and the second turbine 151 performs work on the SCO2Flows out to the second heater 142, and the second heater 142 couples SCO flowing out from the second turbine 1522Heating, and mixing the heated SCO2Into the first turbine 151, the first turbine 151 utilizes the SCO of high temperature and high pressure2Doing work, driving the fan 17 to rotate, and the first turbine 151 will do workSCO2Flows out into the second regenerator 132, wherein SCO enters the first turbine 1512Is higher than the SCO entering the second turbine 1522Temperature of second regenerator 132 to SCO flowing from first turbine 1512Pre-cooling, and mixing the pre-cooled SCO2The SCO is sent to the first regenerator 131, and the first regenerator 131 precools the second regenerator 1322Precooling the SCO and precooling the SCO2One part flows back to the cooler 11 and the other part flows into the second compressor 122, SCO flowing in the second compressor 1222SCO that is recompressed and enters the second regenerator 132, flows from the second compressor 122 to the second regenerator 1322And flows into the second regenerator 132 from the first regenerator 131, is mixed in the second regenerator 132, and is preheated by the second regenerator 132 to be commonly introduced into the first heater 141. SCO into cooler 112And finishing the circulation and preparing to enter the next circulation. By using SCO2And the compression Brayton cycle is combined with the turbofan engine, so that the thermal efficiency of the turbofan engine is improved, the turbofan engine can generate larger thrust, and the application scene of the turbofan engine is expanded.
An embodiment of the present invention provides an aircraft including a turbofan engine as described above as an embodiment.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (23)
1. A turbofan engine, comprising:
a cooler, a compressor, a regenerator, a heater, a turbine, a speed reducer, a fan, a tailpipe, and a casing;
the turbine is connected with the compressor through a rigid shaft; the turbine is connected with the fan through the speed reducer; the speed reducer is used for adjusting the rotating speed ratio between the turbine and the fan; the fan is used for pressurizing sucked air and discharging the pressurized air through the tail nozzle to generate thrust of the turbofan engine;
the cooler is arranged on the surface of the casing, the output end of the cooler is connected with the input end of the compressor through a pipeline, the output end of the compressor is connected with the first input end of the heat regenerator through a pipeline, the first output end of the heat regenerator is connected with the input end of the heater through a pipeline, the output end of the heater is connected with the input end of the turbine through a pipeline, the output end of the turbine is connected with the second input end of the heat regenerator through a pipeline, and the second output end of the heat regenerator is connected with the input end of the cooler through a pipeline;
when the turbofan engine works, the cooler is used for cooling supercritical carbon dioxide SCO2SCO cooled and brought to the compressor inlet conditions2Feeding into the compressor;
the compressor couples the cooled SCO2Pressurizing, and adding the pressurized SCO2Conveying the waste heat into the regenerator;
the regenerator couples the pressurized SCO2Preheating and adding the preheated SCO2Is delivered to the heater;
the heater pair SCO2Heating, and mixing the heated SCO2Feeding into the turbine;
the turbine utilizes SCO at high temperature and pressure2Doing work, driving the compressor and the fan to rotate, and the turbine will do work on the SCO2Flowing out into the regenerator;
the regenerator is paired with used SCO2Pre-cooling, and pre-cooling SCO2Flows back into the cooler.
2. The turbofan engine of claim 1 wherein the regenerator and the heater are both annular, each fixed to a rigid shaft between the compressor and the turbine.
3. The turbofan engine of claim 1 wherein the regenerator is two symmetrical pieces symmetrically disposed on either side of a rigid shaft between the compressor and the turbine.
4. The turbofan engine of claim 1 wherein the heater is two symmetrical pieces symmetrically disposed on either side of a rigid shaft between the compressor and the turbine.
5. The turbofan engine of any one of claims 1-4 wherein the cooler is a printed circuit board air cooler.
6. The turbofan engine of any one of claims 1-4 wherein the fan comprises: duct fan and Flade fan, the Flade fan is connected on the duct fan.
7. A turbofan engine, comprising:
the system comprises a cooler, a compressor, a heat regenerator, a first heater, a second heater, a first turbine, a second turbine, a speed reducer, a fan, a tail pipe and a casing;
the first turbine is connected with the fan through the speed reducer; the speed reducer is used for adjusting a rotating speed ratio between the first turbine and the fan; the fan is used for pressurizing sucked air and discharging the pressurized air through the tail nozzle to generate thrust of the turbofan engine;
the second turbine is connected with the compressor through a rigid shaft;
the cooler is arranged on the surface of the casing, the output end of the cooler is connected with the input end of the compressor through a pipeline, the output end of the compressor is connected with the first input end of the heat regenerator through a pipeline, the first output end of the heat regenerator is connected with the input end of the first heater through a pipeline, the output end of the first heater is connected with the input end of the second turbine through a pipeline, the output end of the second turbine is connected with the input end of the second heater through a pipeline, the output end of the second heater is connected with the input end of the first turbine through a pipeline, the output end of the first turbine is connected with the second input end of the heat regenerator through a pipeline, and the second output end of the heat regenerator is connected with the input end of the cooler through a pipeline;
when the turbofan engine works, the cooler is paired with SCO2SCO cooled and brought to the compressor inlet conditions2Feeding into the compressor;
the compressor couples the cooled SCO2Pressurizing, and adding the pressurized SCO2Conveying the waste heat into the regenerator;
the regenerator couples the pressurized SCO2Preheating and adding the preheated SCO2Feeding to the first heater;
the first heater pair SCO2Heating, and mixing the heated SCO2Feeding into the second turbine;
the second turbine utilizes SCO at high temperature and high pressure2Doing work, driving the compressor to rotate and enabling the SCO after doing work to be used2Flowing out into the second heater;
the second heater couples SCO flowing from the second turbine2Heating, and mixing the heated SCO2Feeding into the first turbine;
the first turbine utilizes SCO at high temperature and high pressure2Doing work, driving the fan to rotate, and enabling the first turbine to do work and obtain SCO2Flows out into the regenerator, wherein it enters the first turbineSCO in (1)2Is higher than the SCO entering the second turbine2The temperature of (a);
the regenerator couples SCO flowing from the first turbine2Pre-cooling, and mixing the pre-cooled SCO2And flows back into the cooler.
8. The turbofan engine of claim 7 wherein the regenerator and the first heater are both annular and are each secured to a rigid shaft between the compressor and the second turbine.
9. The turbofan engine of claim 7 wherein the regenerator is two symmetrical pieces symmetrically disposed on either side of a rigid shaft between the compressor and the second turbine.
10. The turbofan engine of claim 7 wherein the first heater is symmetrically two-piece, symmetrically disposed on either side of a rigid shaft between the compressor and the second turbine.
11. The turbofan engine of claim 7 wherein the second heater is annular or symmetrical two pieces, the second heater being disposed between the first turbine and the second turbine.
12. The turbofan engine of any one of claims 7-11 wherein the cooler is a printed circuit board air cooler.
13. The turbofan engine of any one of claims 7-11 wherein the fan comprises: duct fan and Flade fan, the Flade fan is connected on the duct fan.
14. A turbofan engine, comprising:
the system comprises a cooler, a first compressor, a second compressor, a first regenerator, a second regenerator, a first heater, a second heater, a first turbine, a second turbine, a speed reducer, a fan, a tail pipe and a casing;
the first turbine is connected with the fan through the speed reducer; the speed reducer is used for adjusting a rotating speed ratio between the first turbine and the fan; the fan is used for pressurizing sucked air and discharging the pressurized air through the tail nozzle to generate thrust of the turbofan engine;
the second compressor is connected with the second turbine and the first compressor through rigid shafts respectively;
the cooler is arranged on the surface of the casing, the output end of the cooler is connected with the input end of the first compressor through a pipeline, the output end of the first compressor is connected with the first input end of the first regenerator through a pipeline, the first output end of the first regenerator is connected with the first input end of the second regenerator through a pipeline, the first output end of the second regenerator is connected with the input end of the first heater through a pipeline, the output end of the first heater is connected with the input end of the second turbine through a pipeline, the output end of the second turbine is connected with the input end of the second heater through a pipeline, the output end of the second heater is connected with the input end of the first turbine through a pipeline, and the output end of the first turbine is connected with the second input end of the second regenerator through a pipeline, a second output end of the second heat regenerator is connected with a second input end of the first heat regenerator through a pipeline, a second output end of the first heat regenerator is connected with an input end of the cooler through a pipeline, a third output end of the first heat regenerator is connected with an input end of the second compressor through a pipeline, and an output end of the second compressor is connected with a second input end of the second heat regenerator through a pipeline;
when the turbofan engine works, the cooler is paired with SCO2Cooling and bringing the cooling temperature to the first compressor inletConditional SCO2Feeding into the first compressor;
the first compressor is used for cooling SCO2Pressurizing, and adding the pressurized SCO2Conveying to the first heat regenerator;
the first regenerator is used for pressurizing SCO2Preheating and adding the preheated SCO2Feeding to the second regenerator;
SCO input by the second regenerator to the first regenerator and the second compressor2Re-preheating is carried out, and the re-preheated SCO is2Feeding to the first heater;
the first heater pair SCO2Heating, and mixing the heated SCO2Feeding into the second turbine;
the second turbine utilizes SCO at high temperature and high pressure2Doing work, driving the first compressor and the second compressor to rotate, and enabling the second turbine to do work on the SCO2Flowing out into the second heater;
the second heater couples SCO flowing from the second turbine2Heating, and mixing the heated SCO2Feeding into the first turbine;
the first turbine utilizes SCO at high temperature and high pressure2Doing work, driving the fan to rotate, and enabling the first turbine to do work and obtain SCO2Flow out into the second regenerator, wherein SCO entering the first turbine2Is higher than the SCO entering the second turbine2The temperature of (a);
the second regenerator couples SCO flowing from the first turbine2Pre-cooling, and mixing the pre-cooled SCO2Conveying to the first heat regenerator;
SCO pre-cooled by the first heat regenerator to the second heat regenerator2Precooling the SCO and precooling the SCO2One part flows back to the cooler and the other part flows into the second compressor; SCO flowing into the second compressor2After being recompressedAnd enters the second regenerator.
15. The turbofan engine of claim 14 wherein the first recuperator is annular and is fixed on a rigid shaft between the first compressor and the second compressor.
16. The turbofan engine of claim 14 wherein the first recuperator is symmetrically two-piece, symmetrically disposed on either side of a rigid shaft between the first compressor and the second compressor.
17. The turbofan engine of claim 14 wherein the second recuperator and the first heater are each annular and are each secured to a rigid shaft between the second compressor and the second turbine.
18. The turbofan engine of claim 14 wherein the second recuperator is two symmetrical pieces symmetrically disposed on either side of a rigid shaft between the second compressor and the second turbine.
19. The turbofan engine of claim 14 wherein the first heater is symmetrically two-piece, symmetrically disposed on either side of a rigid shaft between the second compressor and the second turbine.
20. The turbofan engine of claim 14 wherein the second heater is annular or symmetrical two pieces, the second heater being disposed between the first turbine and the second turbine.
21. The turbofan engine of any one of claims 14-20 wherein the cooler is a printed circuit board air cooler.
22. The turbofan engine of any one of claims 14-20 wherein the fan comprises: duct fan and Flade fan, the Flade fan is connected on the duct fan.
23. An aircraft, characterized in that it comprises a turbofan engine according to any one of claims 1-22.
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| CN201910961284.3A CN110685817A (en) | 2019-10-11 | 2019-10-11 | Turbofan engine and aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2794479C1 (en) * | 2022-08-30 | 2023-04-19 | Евгений Вадимович Задорожный | Double-circuit gas turbine fan motor |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| RU2794479C1 (en) * | 2022-08-30 | 2023-04-19 | Евгений Вадимович Задорожный | Double-circuit gas turbine fan motor |
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