CN105156227A - Pre-cooling air-breathing type variable cycle engine - Google Patents
Pre-cooling air-breathing type variable cycle engine Download PDFInfo
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- CN105156227A CN105156227A CN201510634719.5A CN201510634719A CN105156227A CN 105156227 A CN105156227 A CN 105156227A CN 201510634719 A CN201510634719 A CN 201510634719A CN 105156227 A CN105156227 A CN 105156227A
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Abstract
The invention discloses a pre-cooling air-breathing type variable cycle engine and relates to the reusable pre-cooling air-breathing type variable cycle engine applied to aeronautics and astronautics devices. The engine mainly consists of a pre-cooler, a turbine engine, a super combustion chamber and a super combustion ramjet engine, wherein the pre-cooler and the super combustion chamber form a subsonic combustion ramjet engine; a turbine subsonic combustion ramjet engine is connected with the super combustion ramjet engine in parallel; working states of the turbine subsonic combustion ramjet engine and the super combustion ramjet engine are selected by adjusting a switching adjusting device, so that the working modal of the whole engine is controlled. The pre-cooler can reduce an inlet gas flow temperature of a super combustion chamber, can increase the efficiency of the super combustion chamber, can expand the working range of a subsonic combustion punching modal, and can make up insufficient thrust force when turbine subsonic combustion ramjet engine is transferred to the super consumption ramjet engine, so that the pre-cooling air-breathing type variable cycle engine has the advantage that the transfer class of a combined engine is stably transferred.
Description
Technical field
Patent of the present invention relates to a kind of novel compositions motor, particularly a kind of reusable precooling air-inlet type variable cycle engine being applied to endoatmosphere aircraft.
Background technique
The existing air-inlet type power system in endoatmosphere flight mainly comprises turbogenerator and pressed engine, the feature of aeroengine is than leaping high, but being difficult to the power system of height 20km or speed more than 3.0 Mach aircraft, is the bottleneck of various countries' assembly power research and development; Pressed engine is applicable to higher flight Mach number and has higher specific impulse, but flight maneuver is poor, and need solve initial velocity problem by booster rocket.Therefore adopt turboram assembled scheme can make up respective deficiency at present, worm-gear combination motor is applicable to the hypersonic aircraft of Mach number 5-8, is one of following up-and-coming hypersonic power concept.But in the process of research turboram assembly power, encounter that transonic segment thrust is not enough, under low mach intake duct can not effectively start, turn level and be short of power and the thermally equilibrated problem of cruise section.
Above problem basic is exactly do not have to work the turbogenerator of Mach 2 ship 4 at present in the world always, domestic and external existing aero-turbine only can in Mach 2 ship 2-3 stable operation, if and sub-combustion punching press is started working from Mach 2 ship 2 and cannot be played its advantage, wherein just there is one section of steady transition zone thus cause combined engine operational difficulties in this.
Summary of the invention
The object of the invention is for the lower bottleneck problem of transition temperature efficiency in current turboram combination, a kind of precooling air-inlet type variable cycle engine is provided, namely precooler is utilized to lower the temperature to incoming air, the efficiency of super firing chamber can be increased, expand the operating range of sub-combustion punching press mode, make up the combustion of turbine Asia not enough to the thrust during transition of ultra-combustion ramjet mode, thus realize the smooth transition of turbogenerator to pressed engine.
For achieving the above object, technological scheme of the present invention is as follows:
A kind of precooling air-inlet type variable cycle engine, this variable cycle engine comprises the sub-burning ramjet of turbine and scramjet engine, and the sub-burning ramjet of turbine contains turbogenerator intake duct, gas compressor, firing chamber, turbine, super firing chamber and turbogenerator jet pipe; Scramjet engine contains ramjet engine air inlet, pressed engine distance piece, scramjet combustor and pressed engine jet pipe; Described scramjet engine is arranged on the below of the sub-burning ramjet of turbine with parallel way; It is characterized in that: described precooling air-inlet type variable cycle engine is also containing precooler and switching controlling device; Precooler is arranged in the outer culvert passage in front, super firing chamber, this precooler comprises coolant inlet union, coolant outlet union and multiple tubule, multiple tubule is arranged in radial pattern centered by the sub-burning ramjet axis of turbine, precooler entirety structure ringwise; Valve and egress selection valve are selected in described switching controlling device comprises turbogenerator import fender plate, turbogenerator outlet fender plate, pressed engine is adjustable leading edge, pressed engine is adjustable trailing edge and import.
In technique scheme, in described precooler, each tubule is all for the straight length that is arranged in parallel by many and bending section form, and in serpentine bend shape, its diameter is 1-2mm, and straight length and air flow are 30-60 degree angle; The freezing mixture that described precooler adopts is liquid carbon hydrogen fuel, liquid hydrogen or liquid helium; Along on air-flow direction, coolant inlet union is positioned at the downstream of coolant outlet union, and in precooler, the overall flow direction of freezing mixture is contrary with air-flow direction, forms countercurrent flow.
The present invention compared with prior art, have the following advantages and high-lighting effect: inlet air flow temperature can reduce by precooler, increase the efficiency of super firing chamber, make up the combustion of turbine Asia not enough to thrust during scramjet engine transition, the present invention is had advantage that combined engine turns grade smooth transition; In addition, the present invention, by precooler and sub-burning stamping combustion chamber integrated design, can make full use of the advantage of sub-burning ramjet, solves the original Asia combustion punching press difficult problem that thrust declines under High Mach number.
Accompanying drawing explanation
Fig. 1 is that precooling air-inlet type becomes circulation combined engine schematic diagram.
The axial schematic diagram of Fig. 2 precool heat exchanger device.
Freezing mixture and air flow schematic diagram in Fig. 3 precooler.
In figure: 1-aircraft precursor; 2-turbogenerator intake duct; 3-aircraft fuselage; 4-turbogenerator inlet cone; Valve is selected in 5-import; 6-intension passage; 7-precooler; 8-gas compressor; 9-contains passage outward; 10-firing chamber; 11-egress selection valve; The super firing chamber of 12-; Body after 13-aircraft; 14-turbogenerator outlet fender plate; 15-turbogenerator jet pipe; 16-pressed engine is adjustable trailing edge; 17-pressed engine jet pipe; 18-turbine; The sub-burning ramjet of 19-turbine; 20-scramjet engine; 21-scramjet combustor; 22-pressed engine distance piece; 23-ramjet engine air inlet; Leading edge that 24-pressed engine is adjustable; 25-turbogenerator import fender plate; 26-tubule; 27-coolant outlet union; 28-coolant inlet union
Embodiment
Below in conjunction with accompanying drawing, structure of the present invention, principle and working procedure are described in detail.
As shown in Figure 1, pre-cooling type air-inlet type variable cycle engine of the present invention is based on the motor basis integrated with aircraft, by integrated for sub-to precooler 7 and turbine burning ramjet 19, adopt precooler 7 to cool incoming air and push away hypodynamic problem to solve the sub-burning ramjet pattern of turbine to what face during scramjet engine patten transformation.This variable cycle engine forms primarily of precooler 7, the sub-burning ramjet 19 of turbine, super firing chamber 12, scramjet engine 20; The sub-burning ramjet 19 of turbine is arranged on the bottom of aircraft fuselage 3, and be made up of turbogenerator intake duct 2, intension passage 6, outer culvert passage 9 and turbogenerator jet pipe 15, gas compressor 8, firing chamber 10 and turbine 18 are arranged in intension passage 6; Precooler 7 is positioned at the front of super firing chamber 12, and precooler 7 and super firing chamber 12 are arranged in outer culvert passage 9, and high speed incoming air is lowered the temperature by precooler 7, air-flow is introduced super firing chamber 12.Scramjet engine 20 is arranged on below the sub-burning ramjet 19 of turbine with parallel way, is made up of ramjet engine air inlet 23, pressed engine distance piece 22, scramjet combustor 21 and pressed engine jet pipe 17.Aircraft body precursor 1 lower surface, turbogenerator intake duct 2, ramjet engine air inlet 23, turbogenerator import fender plate 25 and the adjustable leading edge 24 of pressed engine form the intake duct of combined engine; The jet pipe of body 13 lower surface after aircraft, turbogenerator jet pipe 15, pressed engine jet pipe 17, turbogenerator outlet fender plate 14, pressed engine is adjustable trailing edge 16 forms combined engine.By regulating import to select the position of valve 5 and egress selection valve 11 can regulate the working state of intension passage 6 and outer culvert passage 9, by the operation mode regulating turbogenerator import fender plate 25 and turbogenerator outlet fender plate 14 can regulate the sub-burning ramjet of turbine and scramjet engine.
As shown in Figures 2 and 3, precooler 7 entirety adopts annular design, and size and turbogenerator by-pass air duct 9 match.Precooler 7 main structure is made up of coolant outlet union 27 and coolant inlet union 28 and multiple smooth tubule 26, and arrange in radial pattern, wherein capillary diameter is about 1 ~ 2mm.In precooler 7, each tubule 26 is all for being made up of multiple straight length of being arranged in parallel and bending section, and in serpentine bend shape, straight length and air flow are 30-60 degree angle.Freezing mixture flows to each tubule 26 uniformly by import union 28, finally respectively go out tubule 26 outlet be pooled to coolant outlet union 27.Coolant inlet union 28 is positioned at the downstream of coolant outlet union 27, and freezing mixture is contrary with air-flow direction on the whole, forms countercurrent flow.The freezing mixture that precooler 7 adopts is liquid carbon hydrogen fuel, liquid hydrogen or liquid helium.
The working procedure of precooling air-inlet type variable cycle engine of the present invention is: when aircraft takes off from ground, turbogenerator import fender plate 25 is in straight position, leading edge 24 that pressed engine is adjustable and the adjustable trailing edge 16 of pressed engine are inclined upwardly, export fender plate 14 with turbogenerator import fender plate 25 and turbogenerator respectively to overlap, turbogenerator import selects valve 5 and egress selection valve 11 to open, outer culvert passage 9 is blocked, air-flow enters intension passage 6 from turbogenerator intake duct 2 and to slow down supercharging, the intension turbine startup work of the sub-burning ramjet 19 of turbine, air is after gas compressor 8 supercharging, burn in firing chamber 10 blending with fuel, combustion gas sprays through turbogenerator jet pipe 15 and produces thrust after turbine 18 expands, when after engine operation to Mach number 2, turbogenerator import selects valve 5 and egress selection valve 11 to close gradually, intension passage 6 is blocked gradually, the air-flow entering outer culvert passage 9 from turbogenerator intake duct 2 increases gradually, through precooler 7 lower the temperature laggard enter super firing chamber 12.When Mach number reaches 3, intension passage 6 is closed, and outer culvert passage 9 opens work completely, and motor is in sub-combustion press work pattern.After Mach number reaches 5, by regulating turbogenerator import fender plate 25, close turbogenerator intake duct 2 gradually, ramjet engine air inlet 23 is opened completely, fuel laterally sprays into from wall, and scramjet engine 20 starts, and motor enters ultra-combustion ramjet operation mode.
Claims (4)
1. a precooling air-inlet type variable cycle engine, this variable cycle engine comprises the sub-burning ramjet (19) of turbine and scramjet engine (20); The sub-burning ramjet (19) of turbine is containing turbogenerator intake duct (2), gas compressor (8), firing chamber (10), turbine (18), super firing chamber (12) and turbogenerator jet pipe (15); Scramjet engine (20) is containing ramjet engine air inlet (23), pressed engine distance piece (22), scramjet combustor (21) and pressed engine jet pipe (17); Described scramjet engine (20) is arranged on the below of the sub-burning ramjet (19) of turbine with parallel way; It is characterized in that: described precooling air-inlet type variable cycle engine is also containing precooler (7) and switching controlling device; Described precooler (7) is arranged in the outer culvert passage (9) in super firing chamber (12) front, this precooler comprises coolant inlet union (28), coolant outlet union (27) and multiple tubule (26), multiple tubule is arranged in radial pattern centered by sub-burning ramjet (7) axis of turbine, precooler (7) structure ringwise on the whole; Valve (5) and egress selection valve (11) are selected in described switching controlling device comprises turbogenerator import fender plate (25), turbogenerator outlet fender plate (14), pressed engine is adjustable leading edge (24), pressed engine is adjustable trailing edge (16) and import.
2. according to a kind of precooling air-inlet type variable cycle engine according to claim 1, it is characterized in that: each tubule (26) is all for the straight length that is arranged in parallel by many and bending section form, in serpentine bend shape, its diameter is 1-2mm, and straight length and air flow are 30-60 degree angle.
3. according to a kind of precooling air-inlet type variable cycle engine described in claim 1 or 2, it is characterized in that: the freezing mixture that described precooler (7) adopts is liquid carbon hydrogen fuel, liquid hydrogen or liquid helium.
4. according to a kind of precooling air-inlet type variable cycle engine according to claim 3, it is characterized in that: along on air-flow direction, coolant inlet union (28) is positioned at the downstream of coolant outlet union (27), the overall flow direction of precooler (7) interior freezing mixture is contrary with air-flow direction, forms countercurrent flow.
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| CN201510634719.5A CN105156227B (en) | 2015-09-29 | 2015-09-29 | Pre-cooling air-breathing type variable cycle engine |
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Cited By (16)
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| CN107630767A (en) * | 2017-08-07 | 2018-01-26 | 南京航空航天大学 | Based on pre- cold mould assembly power hypersonic aircraft aerodynamic arrangement and method of work |
| CN107701312A (en) * | 2017-11-10 | 2018-02-16 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of hypersonic jets |
| CN107989699A (en) * | 2017-11-27 | 2018-05-04 | 北京航空航天大学 | Punching press based on double fuel Compound cooling-strong precooling combination aircraft propulsion |
| CN106968835B (en) * | 2017-04-14 | 2018-07-06 | 西北工业大学 | Full runner is combined in a kind of rocket punching press of wide scope work |
| CN108317019A (en) * | 2018-05-04 | 2018-07-24 | 西北工业大学 | A kind of precooling turbine ultra-combustion ramjet combined engine |
| CN108910059A (en) * | 2018-07-18 | 2018-11-30 | 中国人民解放军国防科技大学 | Precooling type air inlet and hypersonic aircraft |
| CN109026444A (en) * | 2017-06-09 | 2018-12-18 | 范学军 | Composite engine |
| CN109098859A (en) * | 2018-08-13 | 2018-12-28 | 厦门大学 | A kind of hypersonic interior Parallet three-way valve road intake valve deposit mechanism design method |
| CN109236496A (en) * | 2018-11-15 | 2019-01-18 | 厦门大学 | The three power combination engine design methods that Asia combustion can be switched with super burn channel |
| CN110647052A (en) * | 2019-08-16 | 2020-01-03 | 南京航空航天大学 | Variable cycle engine mode switching self-adaptive identity card model construction method |
| CN110985210A (en) * | 2019-11-07 | 2020-04-10 | 北京动力机械研究所 | Micro-fine tube bundle type precooler membrane |
| CN112392628A (en) * | 2019-08-15 | 2021-02-23 | 中国航发商用航空发动机有限责任公司 | Aeroengine core machine, control method and aeroengine |
| CN112963861A (en) * | 2021-03-11 | 2021-06-15 | 哈尔滨工业大学 | Dual-fuel precooler with distributable heat exchange area |
| CN114856855A (en) * | 2022-05-06 | 2022-08-05 | 中国科学院工程热物理研究所 | Wide-speed-range variable-cycle engine based on inter-stage combustion chamber driving low-pressure turbine rotor |
| CN114922740A (en) * | 2022-05-31 | 2022-08-19 | 中国科学院力学研究所 | Wide-range air suction combined type aerospace engine and working method and application thereof |
| CN116291868A (en) * | 2023-03-17 | 2023-06-23 | 南京航空航天大学 | Stamping combined cooling and power device based on reverse brayton variable cycle |
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| CN106968835B (en) * | 2017-04-14 | 2018-07-06 | 西北工业大学 | Full runner is combined in a kind of rocket punching press of wide scope work |
| CN109026444B (en) * | 2017-06-09 | 2021-04-20 | 中国科学院力学研究所 | Combined engine |
| CN109026444A (en) * | 2017-06-09 | 2018-12-18 | 范学军 | Composite engine |
| CN107630767A (en) * | 2017-08-07 | 2018-01-26 | 南京航空航天大学 | Based on pre- cold mould assembly power hypersonic aircraft aerodynamic arrangement and method of work |
| CN107630767B (en) * | 2017-08-07 | 2019-07-09 | 南京航空航天大学 | Based on pre- cold mould assembly power hypersonic aircraft aerodynamic arrangement and working method |
| CN107701312A (en) * | 2017-11-10 | 2018-02-16 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of hypersonic jets |
| CN107989699A (en) * | 2017-11-27 | 2018-05-04 | 北京航空航天大学 | Punching press based on double fuel Compound cooling-strong precooling combination aircraft propulsion |
| CN107989699B (en) * | 2017-11-27 | 2019-09-27 | 北京航空航天大学 | Aircraft propulsion is combined in pre-cooling by force for punching press-based on double fuel Compound cooling |
| CN108317019A (en) * | 2018-05-04 | 2018-07-24 | 西北工业大学 | A kind of precooling turbine ultra-combustion ramjet combined engine |
| CN108910059B (en) * | 2018-07-18 | 2020-07-31 | 中国人民解放军国防科技大学 | Precooling type air inlet and hypersonic aircraft |
| CN108910059A (en) * | 2018-07-18 | 2018-11-30 | 中国人民解放军国防科技大学 | Precooling type air inlet and hypersonic aircraft |
| CN109098859A (en) * | 2018-08-13 | 2018-12-28 | 厦门大学 | A kind of hypersonic interior Parallet three-way valve road intake valve deposit mechanism design method |
| CN109098859B (en) * | 2018-08-13 | 2019-10-18 | 厦门大学 | A kind of hypersonic interior Parallet three-way valve road intake valve deposit mechanism design method |
| CN109236496A (en) * | 2018-11-15 | 2019-01-18 | 厦门大学 | The three power combination engine design methods that Asia combustion can be switched with super burn channel |
| CN109236496B (en) * | 2018-11-15 | 2020-03-27 | 厦门大学 | Design method of three-power combined engine with switchable sub-combustion and super-combustion channels |
| CN112392628A (en) * | 2019-08-15 | 2021-02-23 | 中国航发商用航空发动机有限责任公司 | Aeroengine core machine, control method and aeroengine |
| CN110647052B (en) * | 2019-08-16 | 2021-06-22 | 南京航空航天大学 | Variable cycle engine mode switching self-adaptive identity card model construction method |
| CN110647052A (en) * | 2019-08-16 | 2020-01-03 | 南京航空航天大学 | Variable cycle engine mode switching self-adaptive identity card model construction method |
| CN110985210B (en) * | 2019-11-07 | 2020-11-20 | 北京动力机械研究所 | Micro-fine tube bundle type precooler membrane |
| CN110985210A (en) * | 2019-11-07 | 2020-04-10 | 北京动力机械研究所 | Micro-fine tube bundle type precooler membrane |
| CN112963861A (en) * | 2021-03-11 | 2021-06-15 | 哈尔滨工业大学 | Dual-fuel precooler with distributable heat exchange area |
| CN112963861B (en) * | 2021-03-11 | 2022-08-30 | 哈尔滨工业大学 | Dual-fuel precooler with distributable heat exchange area |
| CN114856855A (en) * | 2022-05-06 | 2022-08-05 | 中国科学院工程热物理研究所 | Wide-speed-range variable-cycle engine based on inter-stage combustion chamber driving low-pressure turbine rotor |
| CN114856855B (en) * | 2022-05-06 | 2023-08-08 | 中国科学院工程热物理研究所 | Wide-speed-range variable cycle engine for driving low-pressure turbine rotor based on interstage combustion chamber |
| CN114922740B (en) * | 2022-05-31 | 2024-05-24 | 中国科学院力学研究所 | Wide-area air suction combined type aerospace engine as well as working method and application thereof |
| CN114922740A (en) * | 2022-05-31 | 2022-08-19 | 中国科学院力学研究所 | Wide-range air suction combined type aerospace engine and working method and application thereof |
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