CN102352789A - Low-entropy mixed-combustion turbine composite explosion-discharging engine - Google Patents
Low-entropy mixed-combustion turbine composite explosion-discharging engine Download PDFInfo
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- CN102352789A CN102352789A CN2011100473444A CN201110047344A CN102352789A CN 102352789 A CN102352789 A CN 102352789A CN 2011100473444 A CN2011100473444 A CN 2011100473444A CN 201110047344 A CN201110047344 A CN 201110047344A CN 102352789 A CN102352789 A CN 102352789A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
- F02B37/004—Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust drives arranged in series
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
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Abstract
The invention discloses a low-entropy mixed-combustion turbine composite explosion-discharging engine, which comprises a gas-inlet passage, a gas-discharging passage, an explosion-discharging engine, a turbine gas compressor and a power turbine, wherein a gas inlet of the turbine gas compressor is communicated with a low-pressure gas source, a compressed-gas outlet of the turbine gas compressor is communicated with the gas-inlet passage, the gas-inlet passage is communicated with a combustion chamber of the explosion-discharging engine through an inlet valve, the combustion chamber is communicated with the gas-discharging passage through an exhaust valve, the gas-discharging passage is communicated with a gas working-substance inlet of the power turbine, the gas pressure at the compressed-gas outlet of the turbine gas compressor is equal to or larger than the gas pressure in a cylinder when the compression stroke of a traditional internal-combustion engine is finished, power is not output to the turbine gas compressor by the explosion-discharging engine, and the power is output to the turbine gas compressor by the power turbine. Through the low-entropy mixed-combustion turbine composite explosion-discharging engine, the high efficiency and the low pollution of the engine are realized, and the environmental-protection property of the engine is greatly improved.
Description
Technical field
The present invention relates to heat energy and power field, the compound burst emission engine of especially a kind of low-entropy mixed-fuel turbine.
Background technique
The history of the existing last 100 years of turbocharging technology, turbine has the advantage that volume is little, in light weight, flow is big, yet cooperates the turbo charged level that also always stops between turbine up to now and the internal-combustion piston engine.Turbosupercharged engine is to utilize turbine that air is carried out supercharging; Air after the supercharging still need compress in cylinder; Though this mode has certain advantage than non pressurized; But because internal-combustion piston engine still needs compression stroke, so no matter be that volume, power per liter or efficient are all restricted.Therefore, need a kind of turbine and piston motor of advantage separately of giving full play to of invention.
Summary of the invention
In order to address the above problem, the technological scheme that the present invention proposes is following:
The compound burst emission engine of a kind of low-entropy mixed-fuel turbine; Comprise intake duct, air outlet flue, burst emission engine, turbocompressor and power turbine; The gas access of said turbocompressor is communicated with low-pressure gas source; The pressurized gas outlet of said turbocompressor is communicated with said intake duct, and said intake duct is communicated with the firing chamber of said burst emission engine through intake valve, and said firing chamber is communicated with said air outlet flue through exhaust valve; Said air outlet flue is communicated with the gas working medium inlet of said power turbine; Gas pressure in the cylinder when gas pressure in the pressurized gas outlet port of said turbocompressor is equal to or greater than the traditional combustion engine compression stroke and is over, said burst emission engine is not to said turbocompressor outputting power, and said power turbine is to said turbocompressor outputting power.
The compound burst emission engine of a kind of low-entropy mixed-fuel turbine; Comprise intake duct, air outlet flue, short journey inflating engine, turbocompressor and the power turbine of pressing; The gas access of said turbocompressor is communicated with low-pressure gas source; The pressurized gas outlet of said turbocompressor is communicated with said intake duct, and said intake duct is communicated with the said short firing chamber of journey inflating engine of pressing through intake valve, and said firing chamber is communicated with said air outlet flue through exhaust valve; Said air outlet flue is communicated with the gas working medium inlet of said power turbine; The gas pressure in the pressurized gas outlet port of said turbocompressor is greater than the pressure in the compressor turbine outlet port of traditional boosting internal combustion engine, and the said short journey inflating engine of pressing is not to said turbocompressor outputting power, and said power turbine is to said turbocompressor outputting power.
On said intake duct, establish the air inlet cooler, and/or on said air outlet flue, establish the exhaust cooling device.
Said air inlet cooler is made as hybrid air inlet cooler, and/or said exhaust cooling device is made as hybrid exhaust cooling device.
Said turbocompressor is made as the multistage turbine gas compressor, and/or said power turbine is made as multistage power turbine.
Said turbocompressor is made as the multistage turbocompressor of being made up of a plurality of single stage turbine gas compressors, and said power turbine is made as the multistage power turbine of being made up of a plurality of single-stage power turbines.
The coaxial setting of first single-stage power turbine in first single stage turbine gas compressor in the said multistage turbocompressor and the said multistage power turbine; The coaxial setting of second said power turbine of single-stage in second single stage turbine gas compressor in the said multistage turbocompressor and the said multistage power turbine, the rest may be inferred.
A coaxial setting of single-stage power turbine beyond first single-stage power turbine in first single stage turbine gas compressor in the said multistage turbocompressor and the said multistage power turbine.
On said turbocompressor, establish turbine heat extraction device.
The compound burst emission engine of said low-entropy mixed-fuel turbine also comprises expander and deep cooling carbon dioxide storage tank; The gas outlet of said power turbine is communicated with the gas access of said expander; The liquid outlet of said expander is communicated with said deep cooling carbon dioxide storage tank; On said expander, establish the non-condensible gas outlet, on said intake duct, establish the air inlet cooler, said air inlet cooler is made as cooling heat exchanger; Said non-condensible gas outlet is communicated with the cold fluid inlet of said cooling heat exchanger, and said low-pressure gas source is made as atmosphere.
The compound burst emission engine of said low-entropy mixed-fuel turbine also comprises deep cooling carbon dioxide storage tank, exhaust deep freezer and liquid oxygen storage tank; The gas outlet of said power turbine is communicated with said exhaust deep freezer; The liquid outlet of said exhaust deep freezer is communicated with said deep cooling carbon dioxide storage tank; Said liquid oxygen storage tank is communicated with said exhaust deep freezer, on said exhaust deep freezer, establishes the oxygen-containing gas outlet, and said low-pressure gas source is made as said oxygen-containing gas outlet.
In said low-pressure gas source, said turbocompressor, said intake duct, said firing chamber, said air outlet flue, said power turbine and the formed fluid circulation space of said exhaust deep freezer, charge into helium, helium goes round and begins again as fixed gas and participates in circulation.
The gas pressure in the pressurized gas outlet port of said turbocompressor is greater than 2MPa, 2.5MPa, 3MPa, 3.5MPa, 4MPa, 45MPa, 5MPa, 55MPa, 6MPa, 6.5MPa, 7MPa, 75MPa, 8MPa, 8.5MPa, 9MPa, 9.5MPa, 10MPa, 10.5MPa, 11MPa, 11.5MPa, 12MPa, 12.5MPa, 13MPa, 13.5MPa, 14MPa, 14.5MPa or 15MPa.
The gas pressure in the pressurized gas outlet port of said turbocompressor is greater than 1MPa, 1.5MPa, 2MPa, 2.5MPa, 3MPa, 3.5MPa, 4MPa, 4.5MPa, 5MPa, 5.5MPa, 6MPa, 6.5MPa, 7MPa, 7.5MPa, 8MPa, 8.5MPa, 9MPa, 9.5MPa, 10MPa, 10.5MPa, 11MPa, 11.5MPa, 12MPa, 12.5MPa, 13MPa, 13.5MPa, 14MPa, 14.5MPa or 15MPa.
The said short journey inflating engine of pressing is made as adiabatic engine.
The said short journey inflating engine absolute magnitude that volume reduces in compression stroke of pressing increases 1/2nd of absolute magnitude less than volume in the expansion working stroke.
Principle of the present invention is to utilize said turbocompressor (so-called low-pressure gas source is meant atmosphere or low pressure oxygen-containing gas or the non-oxygen-containing gas of low pressure with said low-pressure gas source; Be made as in the structure of the non-oxygen-containing gas of low pressure in said low pressure gas body source; Need on certain position that is exported to said firing chamber of said turbocompressor, establish the oxygenant introducing port) in gas compression pressure in the cylinder when being equal to or higher than the traditional combustion engine compression stroke and being over; These pressurized gas are imported in the said firing chamber; In said firing chamber, no longer compressing just burns promotes the external work done of piston; The gas that work done is in the rear cylinder is discharged from cylinder action in said power turbine, makes said power turbine to said gas compressor work done; Perhaps utilize said turbocompressor that the pressure greater than the compressor turbine outlet port of traditional boosting internal combustion engine is arrived in the gas compression in the said low-pressure gas source; In said short exhaust stroke before pressing the journey inflating engine to be in exhaust stroke to be over, these pressurized gas are imported in the firing chamber of said short pressure journey inflating engine; In said firing chamber, only carrying out the part compression stroke just burns and promotes the external work done of piston; The gas that work done is in the rear cylinder is discharged from cylinder action in said power turbine, makes said power turbine to said gas compressor work done.
Among the present invention; Because said compressor turbine is higher to the compression dynamics of gas; So need said power turbine to have higher power output capacity; For this requirement, can adopt the mode of high pressure gas, so-called high pressure gas is meant that when cylinder pressure is higher relatively (pressure in the cylinder when being higher than the conventional engines exhaust stroke and beginning) open exhaust valve and carry out exhaust; Also can utilize piston stroking upward in the exhaust stroke to the pressure of exhaust work done, improve the ability of said power turbine outputting power with the working medium inlet that promotes power turbine.
Among the present invention, the so-called short journey inflating engine of pressing is meant not independently suction stroke, and the shared stroke of exhaust process, breathing process and compression process carries out the motor of combustion explosion stroke after exhaust, air inlet, compression process are over; The gas pressure in said turbocompressor outlet port is high more, and compression process accounts for the share of the length of a stroke can be more little, and this also means the advantage of calming the anger of having utilized turbocompressor more fully.
Among the present invention; In order to improve the efficient of motor as much as possible; Said turbocompressor is compressed gas under constant temperature or approximately constant temperature condition; Compressed gas carries out adiabatic compression said short the pressure in the journey inflating engine after importing said short pressure journey inflating engine, after adiabatic compression, utilizes fuel to carry out the internal combustion heating, carries out thermal insulation or approximate adiabatic expansion work done then; Figure 12 describes the schematic representation that pressure P and temperature T concern in this process; Among Figure 12; Line segment shown in the O-A (can be that straight line also can be a curve) is constant temperature or approximately constant temperature compression process in said turbocompressor; Curve shown in the A-B is in said short adiabatic or approximate adiabatic compression process of pressing in the journey inflating engine; Line segment shown in the B-C (can be that straight line also can be a curve) is constant volume or approximate constant volume internal combustion burning heating process in said short pressure journey inflating engine, and curve shown in the C-O is in said short adiabatic or approximate adiabatic expansion work done process of pressing in the journey inflating engine.In this figure; If curve shown in the C-O with carry out thermal insulation or the resulting O-H curve of approximate adiabatic compression coincides from starting point O (for example atmospheric conditions point); Then represent all to get back to initial state the whole or intimate merit that all is converted into of the heat energy that this explanation combustion process fuel is emitted through temperature, pressure after the circulation.Among the present invention; Can plan as a whole to adjust O-A process, A-B process and B-C process; Make state point after state point C carries out thermal insulation or approximate adiabatic expansion work done on curve shown in the O-H or in the left side of curve shown in the O-H; Even perhaps on O-H curve right side but curve shown in the as close as possible O-H, so just can improve the efficient of motor effectively.Among the present invention, as this section is said compression process is divided into two sections, first section is the constant temperature compression; Second section is adiabatic compression; Its objective is under the prerequisite that reduces compression work as far as possible, make working medium keep certain temperature rise again as much as possible, so just realized under the less prerequisite of compression process power consumption; Working medium has uniform temperature again before the burning, thereby reduces the irreversible loss in the internal combustion heating process.
Among the present invention, so-called " said short press the journey inflating engine absolute magnitude that volume reduces in compression stroke less than volume in the expansion working stroke increase absolute magnitude 1/2nd " be meant from compression stroke and begin to be over amount that gas volume reduces less than 1/2nd of gas volume increasing amount the whole expansion working stroke to compression stroke.
In order further to raise the efficiency, in the present invention, on intake duct, be provided with the air inlet cooler.
Among the present invention, help exhaust liquefaction, on air outlet flue, be provided with the exhaust cooling device in order to reduce through the delivery temperature behind the said power turbine; Reduce significantly if desired through the delivery temperature behind the turbine; Can adopt the mode of high pressure gas; So-called high pressure gas is meant that when cylinder pressure is higher relatively (pressure in the cylinder when being higher than the conventional engines exhaust stroke and beginning) open exhaust valve and carry out exhaust; Also can utilize the pressure that piston stroking upward enters the mouth with the working medium that promotes power turbine to the exhaust work done in the exhaust stroke, thereby realize that bigger expansion ratio reduces delivery temperature.
So-called burst emission engine is meant the motor that has only blast power stroke and exhaust stroke among the present invention; The gas that this motor will compress good low-pressure gas source in advance charges into the firing chamber; In the firing chamber, no longer compress and just carry out combustion explosion; This motor is only explode the piston type thermal power system and the rotator type thermal power system of power stroke and exhaust stroke; For make this motor proper functioning in air inlet, add fuel or in the firing chamber burner oil, based on fuel is different, can adopt the form (compression ignite that is equivalent to conventional engines) of lighting or spraying the back spontaneous combustion; So-called exhaust deep freezer is meant the device that can make the cooling of the exhaust degree of depth reach liquefaction or partial liquefaction; So-called expander is the device with the exhaust expansion cooling, can be throttling expansion device, can be the expansion power unit also, and exhaust throttle expands and lowers the temperature in throttling expansion device, exhaust expansion work done cooling in the expansion power unit; So-called exhaust cooling device is meant the device that exhaust is lowered the temperature; It can be radiator; Also can be to be the heat exchanger of purpose with the exhaust cooling, can also be the hybrid exhaust cooling device that the fluid that temperature is lower mixes with exhaust, and so-called hybrid exhaust cooling device is meant exhaust and cryogen are directly mixed the cooler that conducts heat; Its essence is a container; Exhaust and cryogen are mixed in this container, in order to increase the uniformity of mixing, in this container, can establish flow guide structure, stirring mechanism or fluidic architecture; So-called air inlet cooler is meant the device that air inlet is lowered the temperature, with the exhaust cooling device; So-called turbocompressor is meant the mechanism that utilizes rotation blade or rotating channel that gas is compressed, and it can be single-stage, multistage, also can be a plurality of single-stages or a plurality of multistage combining; So-called power turbine is meant and utilizes exhaust promotion blade or passage to rotate the mechanism of external work done; So-called multistage is meant a plurality of turbocompressor series connection or the series connection of a plurality of power turbine; So-called first single-stage and second single-stage to put in order to leave the firing chamber distance be foundation, apart from the firing chamber near be the first order, taking second place is the second level, the rest may be inferred; So-called deep cooling carbon dioxide is meant the degree that carbon dioxide is cooled to liquefaction and/or solidifies; So-called low-pressure gas source is meant the system that air, low oxygen or low pressure oxygen-containing gas or the non-oxygen-containing gas of low pressure can be provided, for example gas handling system of motor etc.
Be meant can be with the heat exchanger that the heat in the gas sheds that is compressed in the said turbocompressor for so-called turbine heat extraction device among the present invention.Among the present invention, in the structure that is provided with said deep cooling carbon dioxide storage tank, exist in vent systems on the position of condensed water the condensed water export mouth can be set.Among the present invention so-called be communicated be meant direct connection, through the indirect communication of several processes (comprise with other material mixing etc.) or through controlled connections such as pump, control valves.Among the present invention,, parts, unit or systems such as pump, control valve, correct time control valve, oil sprayer or spark plug can be set in position according to the known technology in heat energy and power field; Said turbocompressor can be communicated with the firing chamber of two or more work done mechanism, and the firing chamber of said work done mechanism is meant the firing chamber and the said short firing chamber of pressing the journey inflating engine of said burst emission engine.Beneficial effect of the present invention is following:
1, the present invention has realized efficient, the low pollution of motor, has improved the feature of environmental protection of motor greatly.
Description of drawings
Fig. 1 is the structural representation of the embodiment of the invention 1;
Fig. 2 is the structural representation of the embodiment of the invention 2;
Fig. 3 is the structural representation of the embodiment of the invention 3;
Fig. 4 is the structural representation of the embodiment of the invention 4;
Fig. 5 is the structural representation of the embodiment of the invention 5;
Fig. 6 is the structural representation of the embodiment of the invention 6;
Fig. 7 is the embodiment of the invention 7 and embodiment's 12 a structural representation;
Fig. 8 is the structural representation of the embodiment of the invention 8;
Fig. 9 is the structural representation of the embodiment of the invention 9;
Figure 10 is the structural representation of the embodiment of the invention 10;
Figure 11 is the structural representation of the embodiment of the invention 11;
Figure 12 is the schematic representation of the present invention program's pressure P and temperature T relation.
Embodiment
The compound burst emission engine of low-entropy mixed-fuel turbine as shown in Figure 1; Comprise intake duct 1, air outlet flue 2, burst emission engine 3, turbocompressor 4 and power turbine 5; The gas access of turbocompressor 4 is communicated with low-pressure gas source 6; The pressurized gas outlet of turbocompressor 4 is communicated with intake duct 1, and intake duct 1 is communicated with the firing chamber 301 of burst emission engine 3 through intake valve 7, and firing chamber 301 is communicated with air outlet flue 2 through exhaust valve 8; Air outlet flue 2 is communicated with the gas working medium inlet of power turbine 5; Gas pressure in the cylinder when gas pressure in the pressurized gas outlet port of turbocompressor 4 is equal to or greater than the traditional combustion engine compression stroke and is over, said burst emission engine 3 be to said turbocompressor 4 outputting powers, 5 pairs of turbocompressor 4 outputting powers of power turbine.
The compound burst emission engine of low-entropy mixed-fuel turbine as shown in Figure 2, itself and embodiment's 1 difference is: on intake duct 1, establish air inlet cooler 100.The purpose that is provided with like this is the efficient that improves said turbocompressor for further, and then improves the efficient of the compound burst emission engine of said low-entropy mixed-fuel turbine.
The compound burst emission engine of low-entropy mixed-fuel turbine as shown in Figure 3, itself and embodiment's 1 difference is: on air outlet flue 2, establish exhaust cooling device 200.The purpose that is provided with like this is to help exhaust liquefaction in order to reduce through the delivery temperature behind the said power turbine, realizes the closure of system.
The compound burst emission engine of low-entropy mixed-fuel turbine as shown in Figure 4, itself and embodiment's 1 difference is: turbocompressor 4 is made as multistage turbine gas compressor 400, and power turbine 5 is made as multistage power turbine 500.
The compound burst emission engine of low-entropy mixed-fuel turbine as shown in Figure 5; Itself and embodiment's 1 difference is: turbocompressor 4 is made as the multistage turbocompressor of being made up of a plurality of single stage turbine gas compressors 401, and power turbine 5 is made as the multistage power turbine of being made up of a plurality of single-stage power turbines 501; The coaxial setting of first single-stage power turbine in first single stage turbine gas compressor in the multistage turbocompressor 401 and the multistage power turbine 501; Second coaxial setting of single-stage power turbine in second single stage turbine gas compressor in the multistage turbocompressor 401 and the multistage power turbine 501, the rest may be inferred.
The compound burst emission engine of low-entropy mixed-fuel turbine as shown in Figure 6, itself and embodiment's 5 difference is: a coaxial setting of single-stage power turbine beyond first single-stage power turbine in first single stage turbine gas compressor in the multistage turbocompressor 401 and the multistage power turbine 501.
The compound burst emission engine of low-entropy mixed-fuel turbine as shown in Figure 7, itself and embodiment's 1 difference is: on turbocompressor 4, establish turbine heat extraction device 402.
The compound burst emission engine of low-entropy mixed-fuel turbine as shown in Figure 8; Itself and embodiment's 1 difference is: the compound burst emission engine of low-entropy mixed-fuel turbine also comprises expander 50 and deep cooling carbon dioxide storage tank 10; The gas outlet of power turbine 5 is communicated with the gas access of expander 50, and the liquid outlet of expander 50 is communicated with deep cooling carbon dioxide storage tank 10, on expander 50, establishes non-condensible gas outlet 501; On intake duct 1, establish air inlet cooler 100; Air inlet cooler 100 is made as cooling heat exchanger 1001, and non-condensible gas outlet 501 is communicated with the cold fluid inlet of cooling heat exchanger 1001, and low-pressure gas source 6 is made as atmosphere.
Embodiment 9
The compound burst emission engine of low-entropy mixed-fuel turbine as shown in Figure 9; Itself and embodiment's 1 difference is: the compound burst emission engine of low-entropy mixed-fuel turbine also comprises deep cooling carbon dioxide storage tank 10, exhaust deep freezer 11 and liquid oxygen storage tank 61; The gas outlet of power turbine 5 is communicated with exhaust deep freezer 11; The liquid outlet of exhaust deep freezer 11 is communicated with deep cooling carbon dioxide storage tank 10; Liquid oxygen storage tank 61 is communicated with exhaust deep freezer 11, on exhaust deep freezer 11, establishes oxygen-containing gas outlet 1101, and low-pressure gas source 6 is made as oxygen-containing gas outlet 1101;
In low-pressure gas source 6, turbocompressor 4, intake duct 1, firing chamber 301, air outlet flue 2, power turbine 5 and exhaust deep freezer 11 formed fluid circulation spaces, charge into helium, helium goes round and begins again as fixed gas and participates in circulation.
The compound burst emission engine of low-entropy mixed-fuel turbine shown in figure 10; Comprise intake duct 1, air outlet flue 2, short journey inflating engine 333, turbocompressor 4 and the power turbine 5 of pressing; The gas access of said turbocompressor 4 is communicated with low-pressure gas source 6; The pressurized gas outlet of said turbocompressor 4 is communicated with said intake duct 1; Said intake duct 1 is communicated with the said short firing chamber 301 of journey inflating engine 333 of pressing through intake valve 7; Said firing chamber 301 is communicated with said air outlet flue 2 through exhaust valve 8, and said air outlet flue 2 is communicated with the gas working medium inlet of said power turbine 5, and the gas pressure in the pressurized gas outlet port of said turbocompressor 4 is greater than the pressure in the compressor turbine outlet port of traditional boosting internal combustion engine; Said weak point presses journey inflating engine 333 not to said turbocompressor 4 outputting powers, 5 pairs of said turbocompressor 4 outputting powers of said power turbine.
Embodiment 11
The compound burst emission engine of low-entropy mixed-fuel turbine shown in figure 11; Itself and embodiment's 1 difference is: on said intake duct 1, establish air inlet cooler 100; Said air inlet cooler 100 is made as hybrid air inlet cooler 101; On said air outlet flue 2, establish exhaust cooling device 200, said exhaust cooling device 200 is made as hybrid exhaust cooling device 201.
Embodiment 12
The compound burst emission engine of low-entropy mixed-fuel turbine as shown in Figure 7; Itself and embodiment's 1 difference is: on said turbocompressor 4, establish turbine heat extraction device 402; The said short journey inflating engine 333 of pressing is made as adiabatic engine, and said short journey inflating engine 333 absolute magnitude that volume reduces in compression stroke of pressing increases 1/2nd of absolute magnitude less than volume in the expansion working stroke.
Obviously, the invention is not restricted to above embodiment, many distortion can also be arranged.Those of ordinary skill in the art, all distortion that can directly derive or associate from content disclosed by the invention all should be thought protection scope of the present invention.
Claims (16)
1. compound burst emission engine of low-entropy mixed-fuel turbine; Comprise intake duct (1), air outlet flue (2), burst emission engine (3), turbocompressor (4) and power turbine (5); It is characterized in that: the gas access of said turbocompressor (4) is communicated with low-pressure gas source (6); The pressurized gas outlet of said turbocompressor (4) is communicated with said intake duct (1); Said intake duct (1) is communicated with the firing chamber (301) of said burst emission engine (3) through intake valve (7); Said firing chamber (301) is communicated with said air outlet flue (2) through exhaust valve (8), and the gas working medium inlet of said air outlet flue (2) and said power turbine (5) is communicated with, the interior gas pressure of cylinder when the gas pressure in the pressurized gas outlet port of said turbocompressor (4) is equal to or greater than the traditional combustion engine compression stroke and is over; Said burst emission engine (3) is not to said turbocompressor (4) outputting power, and said power turbine (5) is to said turbocompressor (4) outputting power.
2. compound burst emission engine of low-entropy mixed-fuel turbine; Comprise intake duct (1), air outlet flue (2), short journey inflating engine (333), turbocompressor (4) and the power turbine (5) of pressing; It is characterized in that: the gas access of said turbocompressor (4) is communicated with low-pressure gas source (6); The pressurized gas outlet of said turbocompressor (4) is communicated with said intake duct (1); Said intake duct (1) is communicated with the said short firing chamber (301) of journey inflating engine (333) of pressing through intake valve (7); Said firing chamber (301) is communicated with said air outlet flue (2) through exhaust valve (8), and said air outlet flue (2) is communicated with the gas working medium inlet of said power turbine (5), and the gas pressure in the pressurized gas outlet port of said turbocompressor (4) is greater than the pressure in the compressor turbine outlet port of traditional boosting internal combustion engine; The said short journey inflating engine (333) of pressing is not to said turbocompressor (4) outputting power, and said power turbine (5) is to said turbocompressor (4) outputting power.
3. the compound burst emission engine of low-entropy mixed-fuel turbine according to claim 1 or claim 2 is characterized in that: on said intake duct (1), establish air inlet cooler (100), and/or on said air outlet flue (2), establish exhaust cooling device (200).
4. like the compound burst emission engine of the said low-entropy mixed-fuel turbine of claim 3, it is characterized in that: said air inlet cooler (100) is made as hybrid air inlet cooler (101), and/or said exhaust cooling device (200) is made as hybrid exhaust cooling device (201).
5. the compound burst emission engine of low-entropy mixed-fuel turbine according to claim 1 or claim 2, it is characterized in that: said turbocompressor (4) is made as multistage turbine gas compressor (400), and/or said power turbine (5) is made as multistage power turbine (500).
6. the compound burst emission engine of low-entropy mixed-fuel turbine according to claim 1 or claim 2; It is characterized in that: said turbocompressor (4) is made as the multistage turbocompressor of being made up of a plurality of single stage turbine gas compressors (401), and said power turbine (5) is made as the multistage power turbine of being made up of a plurality of single-stage power turbines (501).
7. like the compound burst emission engine of the said low-entropy mixed-fuel turbine of claim 6; It is characterized in that: the coaxial setting of first single-stage power turbine in first single stage turbine gas compressor in the said multistage turbocompressor (401) and the said multistage power turbine (501); The coaxial setting of second said power turbine of single-stage in second single stage turbine gas compressor in the said multistage turbocompressor (401) and the said multistage power turbine (501), the rest may be inferred.
8. like the compound burst emission engine of the said low-entropy mixed-fuel turbine of claim 6, it is characterized in that: a coaxial setting of single-stage power turbine beyond first single-stage power turbine in first single stage turbine gas compressor in the said multistage turbocompressor (401) and the said multistage power turbine (501).
9. the compound burst emission engine of low-entropy mixed-fuel turbine according to claim 1 or claim 2 is characterized in that: on said turbocompressor (4), establish turbine heat extraction device (402).
10. the compound burst emission engine of low-entropy mixed-fuel turbine according to claim 1 or claim 2; It is characterized in that: the compound burst emission engine of said low-entropy mixed-fuel turbine also comprises expander (50) and deep cooling carbon dioxide storage tank (10); The gas outlet of said power turbine (5) is communicated with the gas access of said expander (50); The liquid outlet of said expander (50) is communicated with said deep cooling carbon dioxide storage tank (10); On said expander (50), establish non-condensible gas outlet (501), on said intake duct (1), establish air inlet cooler (100), said air inlet cooler (100) is made as cooling heat exchanger (1001); Said non-condensible gas outlet (501) is communicated with the cold fluid inlet of said cooling heat exchanger (1001), and said low-pressure gas source (6) is made as atmosphere.
11. the compound burst emission engine of low-entropy mixed-fuel turbine according to claim 1 or claim 2; It is characterized in that: the compound burst emission engine of said low-entropy mixed-fuel turbine also comprises deep cooling carbon dioxide storage tank (10), exhaust deep freezer (11) and liquid oxygen storage tank (61); The gas outlet of said power turbine (5) is communicated with said exhaust deep freezer (11); The liquid outlet of said exhaust deep freezer (11) is communicated with said deep cooling carbon dioxide storage tank (10); Said liquid oxygen storage tank (61) is communicated with said exhaust deep freezer (11), on said exhaust deep freezer (11), establishes oxygen-containing gas outlet (1101), and said low-pressure gas source (6) is made as said oxygen-containing gas outlet (1101).
12. like the compound burst emission engine of the said low-entropy mixed-fuel turbine of claim 11; It is characterized in that: in said low-pressure gas source (6), said turbocompressor (4), said intake duct (1), said firing chamber (301), said air outlet flue (2), said power turbine (5) and the formed fluid circulation space of said exhaust deep freezer (11), charge into helium, helium goes round and begins again as fixed gas and participates in circulation.
13. the compound burst emission engine of low-entropy mixed-fuel turbine according to claim 1, it is characterized in that: the gas pressure in the pressurized gas outlet port of said turbocompressor (4) is greater than 2MPa, 2.5MPa, 3MPa, 3.5MPa, 4MPa, 4.5MPa, 5MPa, 5.5MPa, 6MPa, 6.5MPa, 7MPa, 7.5MPa, 8MPa, 8.5MPa, 9MPa, 9.5MPa, 10MPa, 10.5MPa, 11MPa, 11.5MPa, 12MPa, 12.5MPa, 13MPa, 13.5MPa, 14MPa, 14.5MPa or 15MPa.
14. like the compound burst emission engine of the said low-entropy mixed-fuel turbine of claim 2, it is characterized in that: the gas pressure in the pressurized gas outlet port of said turbocompressor (4) is greater than 1MPa, 1.5MPa, 2MPa, 2.5MPa, 3MPa, 3.5MPa, 4MPa, 4.5MPa, 5MPa, 5.5MPa, 6MPa, 6.5MPa, 7MPa, 7.5MPa, 8MPa, 8.5MPa, 9MPa, 9.5MPa, 10MPa, 10.5MPa, 11MPa, 11.5MPa, 12MPa, 12.5MPa, 13MPa, 13.5MPa, 14MPa, 14.5MPa or 15MPa.
15. like the compound burst emission engine of the said low-entropy mixed-fuel turbine of claim 2, it is characterized in that: the said short journey inflating engine (333) of pressing is made as adiabatic engine.
16. like the compound burst emission engine of the said low-entropy mixed-fuel turbine of claim 2, it is characterized in that: said short journey inflating engine (333) absolute magnitude that volume reduces in compression stroke of pressing increases 1/2nd of absolute magnitude less than volume in the expansion working stroke.
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| CN2011100473444A CN102352789A (en) | 2010-10-18 | 2011-02-28 | Low-entropy mixed-combustion turbine composite explosion-discharging engine |
| CN2011103128639A CN102364071B (en) | 2010-10-18 | 2011-10-15 | Turbine cylinder low-entropy engine |
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| CN201010509904 | 2010-10-18 | ||
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| CN201110037932 | 2011-02-15 | ||
| CN2011100473444A CN102352789A (en) | 2010-10-18 | 2011-02-28 | Low-entropy mixed-combustion turbine composite explosion-discharging engine |
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| CN2011103128639A Active CN102364071B (en) | 2010-10-18 | 2011-10-15 | Turbine cylinder low-entropy engine |
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Also Published As
| Publication number | Publication date |
|---|---|
| CN102364071B (en) | 2013-09-11 |
| CN102364071A (en) | 2012-02-29 |
| WO2012051784A1 (en) | 2012-04-26 |
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