CN104863751A - Circular jet-propelled double-rotor turbofan aero-engine - Google Patents
Circular jet-propelled double-rotor turbofan aero-engine Download PDFInfo
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Abstract
The invention discloses a circular jet-propelled double-rotor turbofan aero-engine, and belongs to the overall design of an aero-engine, and the technical field of turbofan aero-engines. According to the design, the circular jet-propelled double-rotor turbofan aero-engine is a super-speed aero-engine with a high thrust-weight ratio, and characterized in that a hollow turbofan aero-engine serves as a main body; large-diameter hollow low-pressure rotors and a controllable throat part are contained; a coolant from the air inlet of a center duct is pressurized at a tail air compressor, and then the pressurized coolant enters a turbine for cooling the turbine, so that the turbine can be effectively cooled and combined with a mature cooling system to form a double-cooling system; during a super-speed flight, a ramjet operates to solve the problems of insufficient high-speed flight power and the like; functions of removing foreign matters in an engine and inhibiting the centrifugal force of a large-diameter fan and the turbine are realized. The circular jet-propelled double-rotor turbofan aero-engine has the advantages that the engine power can be improved and sufficient pushing force is provided for an aircraft; damage caused by a bird strike is relived; the surface temperature of the turbine is lowered; the infrared radiation in the tail direction of an exhaust system is greatly reduced.
Description
Technical field
The present invention relates to a kind of turbine aircraft engines, and relate more specifically to a kind of system architecture of annular turbofan aeroengine.
Background technique
The development of aeroengine and development are one and relate to the comprehensive systems engineerings such as aerodynamics, material, gongwu, machinery, electronics, sealing, Automated condtrol.The structure of aeroengine causes it to have the features such as high temperature, high pressure, high rotating speed, high load.Current advanced Gas Turbine inlet gas temperature has exceeded 1700 DEG C, and the temperature of 2100 DEG C even higher of marching toward further.Gas compressor increases overall pressure tatio and reaches 40+'s.The linear velocity of turbine blade blade tip reach 2000 kilometers/time and how long its blade has 3 meters.Under high-temperature high-load like this, improving overall engine structure is an important developing direction.
State-of-the-art turbogenerator in the world, as meet with bird hit, flying bird is inhaled into turbofan, make motor flabellum be out of shape or block, cause motor shut down so that on fire, very easily cause aircraft stall to crash.Aircraft take off and descent in the most easily occur bird hit.Annual all can have bird accident of hitting to occur, and has the direct economic loss of more than more than ten hundred million dollars.
For the turbine blade of aviation gas turbine owing to operating in high-temperature gas.Outer surface is exposed in high-temperature gas, so in order to prevent turbine blade overheated, within it or internal circulation freezing mixture, cools from inner side or inside turbine blade.To coolant feed to turbine rotor blade or wheel blade be a major issue in combustion gas turbine design, and therefore proposed the many different system and method realizing coolant feed.For example U.S. Patent No. 5,226,785 discuss and use fluid director and impeller to carry out conveying blade cool stream, and U.S. Patent No. 5,317,877 discuss and make extracting air through heat exchange, and deliver air on rotor through annulus, wherein use impeller by air pumping until turbine blade entrance.In any situation, in current turbine blade cooling system, the cooling air volume needed for cooling turbine bucket is about 30% to 40% of the total additional air flow for given machine.Therefore, any raising of turbine blade cooling agent delivery method all can produce larger improvement to the performance of machine.
Casing must have enough intensity, and the blade containing any one fracture when high rotating speed or come off, larger breaking and gross distortion does not occur casing.By foreign object strike damage (FOD), high cycle fatigue (HCF) and low cycle fatigue (LCF) impact, inevitably there is leaf destruction.Therefore reliability design must be carried out to casing, with the secondary injury after avoiding motor impaired.
Summary of the invention
The present invention is not enough in order to overcome above-mentioned prior art, provide a kind of big thrust loading, superfast aeroengine, little in order to solve thrust weight ratio, turbogenerator cannot carry out hypervelocity flight (when flight Mach number is greater than 4 (M > 4), compressor pressure air-flow is disadvantageous on the contrary), suction bird and foreign matter enter the impact on motor, the problems such as turbine cooling and casing intensity.The present invention, for realizing above-mentioned target, adopts following technological scheme:
The invention provides a kind of core engine of turbofan aeroengine, its engine body is hollow turbofan aeroengine.Structure as shown in drawings.Be followed successively by from front to back: air inlet protection, inlet guide vane, fan, low pressure compressor, high-pressure compressor, firing chamber, high-pressure turbine, low-pressure turbine and be applicable to turbine blade cooling system of the present invention.Note: turbofan engine structure division be not described.The through whole turbogenerator of center duct, electric fan extends to center.Its effect prevents the formation of the bowshock dynamic aerodynamic parameter of Hair Fixer that liquidates from damaging.Duct rear portion, center has controlled throat and is used for controlling the flow by center duct air-flow.The short flabellum of larynx formula of throat front end is used for control centre's duct flow rotation and filtering the freezing mixture entering center duct inlet.Center duct inlet is freezing mixture suction port, and it is between short flabellum.The freezing mixture that suction port enters is through turbine shaft supercharging again, and pumping, to turbine, cools turbine.Distance piece rear end is combustor section (center duct discharge portion), is lobe shape jet pipe.Containing fuel nozzle in jet pipe, the necessary parts needed for the pressed engine such as igniter and flame holder.
Fan outer rim and runner band are equipped with rolling bearing or magnetic bearing and calutron.Fan, turbine can use band crown gear dish, and wheel disc external diameter uses rolling bearing or magnetic bearing to support, and centrifugal force is carried out to the rigid requirements suppressing effectively to improve material.But corresponding reliability and the accuracy increasing bearing.The pulling force of rotor to blade is made to become pressure to rolling bearing or magnetic bearing.Improve fan design aerodynamic parameter.Reduce centrifugal force to the rigid requirements of tenon tongue-and-groove, also improve at generation FOD, HCF, LCF the destruction of casing containment.
Center duct entrance (i.e. pressed engine suction port place) has electric fan to extend to center, and the short flabellum of larynx formula is tail end closing in shape blade.Note: if sense of rotation is clockwise, the short flabellum of larynx formula is manufacture counterclockwise.Electric fan extends its effect to center be the formation preventing bowshock, and the short flabellum of tail end larynx formula increases coolant inlet pressure.Stickiness due to actual airflow can cause entering gas rotating, can form air film, with isolated Aerodynamic Heating at center duct table wall.
Controlled throat controls the parts of throat's open part air-flow by size.Controlled throat is divided into diffuser and distance piece, and its effect is that diffuser carries out diffusion to center duct, and the isolation of distance piece when starting pressed engine, does not use during pressed engine and cool turbine engine exhaust.
The short fan blade structure of larynx formula becomes the cleaning device in order to clean extracting air.Its effect is the foreign matter to entering, and cleaning device will filter it.Utilize centrifugal force that the thing such as water, ice is peeled off suction port by short flabellum, as entered cooling system, regional temperature is too low, and differences in expansion easily causes irreversible damage to turbine.
Afterbody gas compressor has air intake valve and controls entered air filtering, and relief opening also exists valve controls air mass flow.Its effect, when adopting pressed engine work, when turbogenerator does not work, reduces air loss.
Low pressure rotor axle afterbody has calm the anger flabellum and air chamber and tail cone and forms afterbody air compressor structure.Its effect carries out supercharging to the air entered, and air chamber can deposit a small amount of high-pressure air, maintains pressure steady, for turbine cooling provides freezing mixture.
Turbine coolant discharging system, has air chamber, turbine disk tilted air holes, valve.Its effect is that the gas of discharging after turbine cooling has Free up Memory.Cooling-air can be introduced in a large number to cool turbine.After cooling, gas is discharged to by-pass air duct or tail cone exhaust, can be incorporated in the middle of air-conditioning system when pressure reaches certain value.And during pressed engine work, valve is closed, reduce diffusion loss.
Front end fan outer rim and runner band are equipped with magnetic bearing or rolling bearing and casing Upper shaft sleeve and form and match, and axle sleeve is furnished with circuit, produce high-frequency voltage.Its effect is used to Detection & Controling engine speed.As reasonable in design, can be used for generating electricity.
The short flabellum of throat's front end larynx formula, blade is netted knot, and blade height is less than 10% of center duct diameter, and increases highly to the back-end.Its effect is improvement center duct air-flow rotating speed, peels off foreign matter and discharges from closing in, keeps suction port to clean.
Accompanying drawing explanation
Fig. 1 is ring jet formula double rotor turbofan aeroengine overall structure schematic diagram of the present invention
Fig. 2 is this engine blower front view
Fig. 3 is this engine turbine and cooling import sectional drawing
Description of reference numerals
1 air inlet protection, 2 air inlet water conservancy diversion leaves, 3 fans, 4 by-pass air ducts; 5 center ducts, 6 low pressure compressors, 7 high-pressure compressors; 8 annular combustion chambers, 9 high-pressure turbines, 10 low-pressure turbines; the short flabellum of 11 larynx formula, 12 center duct inlets, 13 tail cones; 14 exhausts rectification (or tail pipe burner), 15 controlled throats, 16 magnetic bearings; 17 lobe shape jet pipes, 18 tilted air holes, 19 afterbody gas compressors.
Embodiment
Below in conjunction with accompanying drawing, working procedure of the present invention is described further:
The present invention adopts annular engine structure as shown in Figure 1.The basis of original turbofan aeroengine is removed fan rectifying cone, center is made into pressed engine pattern.Turbofan engine part will be omitted in follow-up explanation.Pressed engine cannot work be carried out without during relative movement, so existing pressed engine major part be hybrid engine as Qinling Mountains turbofan engine, its tail pipe burner part is exactly a kind of pressed engine.Current state-of-the-art turbogenerator operationally center of circle part (rotor shaft) does not do work, and all effective output is between rotor and casing, thus the present invention uses hollow rotor shafts allow do not do work part be utilized effectively.The hollow space of hollow rotor shafts is the intake duct that diameter is very large.The Design of Inlet parameter of pressed engine will be ensured during practical design: a small amount of fuel feeding of turbogenerator or not fuel feeding time, by pressed engine provide power must air mass flow nargin.Intake duct parameter is: total pressure recovery coefficient, external resistance coefficient, and exit flow field is even.
Air-flow can produce aerodynamical resistance and normal shock wave after running into fairing cone, compression front air.External compression inlet design point, is designed to slightly subcritical state, that is: pressure perturbation does not move forward at suction port a little.But the rocket motor degree of external compression inlet is maximum, and the inclination angle of casing outer wall is maximum, so resistance is larger; Because the degree of turning back of air-flow is comparatively large, so the pitot loss in pipeline is also larger.So by finding out that external compression inlet to design the intake duct becoming ultra high speed motor above.Center of the present invention duct is a kind of internal compressioninlet.Unify by front end fan, controlled throat and turbine cooling system and improve bowshock, reducing outside excess mass air overfall.Effectively can solve and be difficult to " starting " problem.More on the fighter of Mach 2 ship less than 2.5 of external compression inlet.
Pressed engine is the important system unit of the present invention.Working principle is: will reduce air inlet to turbogenerator when flight Mach number is greater than 3 (M > 3) air inlet protection, pressed engine starts to carry out work.In real engine runs, reach the minimum starting standard of pressed engine, pressed engine starts to carry out work immediately.Note: when flight Mach number is greater than 4 (M > 4), compressor pressure is unfavorable on the contrary.
Schematic diagram of the present invention only has one-level fan as shown in Figure 2, because pressed engine diffusion casing is low pressure rotor axle, so pressed engine casing rotates.Aircraft gas handling system when high-speed flight will face serious Aerodynamic Heating, and after flight Mach number is greater than the wall of 5 (M > 5) motor and air friction, temperature can reach 1000 DEG C.So cooling system is also one of emphasis of the present invention: remove fairing cone and design extension fan.Extend the air-flow of flabellum supply, the stickiness due to actual airflow can cause entering gas rotating, can form disturbance air film, with isolated Aerodynamic Heating at center duct table wall.And the short flabellum of larynx formula is for improving flow rotation design.The flabellum of the short flabellum of larynx formula is many mesh, except for improving flow rotation, also as filtering gas and improve the impact of shock wave on Diffuser.
The center duct inlet of center duct, for the gaseous film control of gas-turbine blade and end wall provides freezing mixture.Throat's short flabellum of front portion welding larynx formula gives the freezing mixture supercharging that will enter center duct inlet.The air that suction port enters, the afterbody gas compressor formed through calm the anger flabellum and the tail cone of low pressure rotor axle afterbody carries out supercharging, after air chamber diffusion, is cooled turbine by turbine cooling structure.Freezing mixture after supercharging is from the root of high-pressure turbine and low-pressure turbine to end diffluence.Center duct inlet not directly at rotor inner wall opening, but at the platform of the protruding about 1cm of axial wall, at Platform center opening.Guarantee bottom water, ice are discharged under platform.Suction port be tilt to strengthen air inlet.Sealing can adopt brush seal.Strict to seal request herein.Freezing mixture cools from turbine disk root to wheel rim (overall wheel disc) direction.
The heat-eliminating medium that duct place, center enters, the existing pictures such as gas flow is large, there is not gas flow deficiency when implementing gaseous film control, and air film is not enough.Concrete gaseous film control method can consult application publication number: the similar approach such as CN 101910564 A repeat no more herein, and the present invention mainly emphasizes overall structure.
Attention: the present invention only uses this kind of cooling means, traditional type of cooling also can use in the present invention, reduces cooling risk and improves cooling reliability.
During high-speed flight, the pressed engine distance piece of center duct is that the short flabellum tail end of larynx formula is to flame holder front end.Its length is by calculating:
θ in formula---distance piece import boundary layer momentum thickness
Ma
i---inflow Mach number
---outlet and import static pressure ratio
Re---based on the reynolds' number of import momentum thickness θ
Pressed engine throat is controlled: 1. time as common pressed engine, can change and adjust pressed engine margin of operation by flow area.2. as shock wave ignite pressed engine time, be used as cowling use to adjust shock wave.Distance piece is minimum dimension.Throat's controllable part is in low-pressure turbine rear end.At the making initial stage, fixed throat can be used, make outlet even flow field.Throat is separated with low pressure rotor, available brush seal.
Distance piece rear end be combustor section it be lobe shape jet pipe, containing fuel nozzle in jet pipe, the necessary parts needed for the pressed engine such as igniter and flame holder.It and turbine engine exhaust are same air chamber, and principle is consulted tail pipe burner and do not repeated.Under low-speed operations condition, do not use during pressed engine and be used for reducing tail cone delivery temperature and infrared suppressing by the air-flow of throat.
Fan section of the present invention is because fan center is without node, and when fan is enough large, the centrifugal force of fan can change the aerodynamic parameter of fan.So this fan can not be adopted when first making, only embody thought of the present invention and just can reach good result.Centrifugal force is the maximum difficult point of the present invention, and how controllable centrifugal the present invention also proposes a plan: fan is band hat flabellum, and bizet is the supporting point of its centrifugal force, and bizet is the installation position of magnetic bearing or rolling bearing.The present invention's the method suppresses centrifugal force.Change and become the pressure of fan to casing bearing from the pulling force of original rotor to fan, therefore very strict to bearing requirements.Rolling bearing must suppress flabellum centrifugal force with magnetic force as cannot be reached requirement.If magnetic force also cannot suppress, fan can be removed, only retain and extend flabellum.As adopted high-strength material, the undeformed outer load-carrying construction that can not adopt indication of the present invention of center duct.Note: runner band end also can use magnetic bearing to suppress centrifugal force.
It is duplicate protection that the present invention enters foreign matter: 1. air inlet protection.It is used for improving the shock wave inhaled and to improve airplane engine when bird and other foreign matter enter damage to motor, aircraft at normal flight and produce when taking off landing.In addition turbogenerator air inlet is controlled.2. inlet guide vane is also one heavily to protect, and enters into airplane engine suction port if any foreign matter, the duct flowing of air inlet protection Shi Qixiang center, and discharges from throat.If foreign matter quality is excessive, air inlet protection is severed and cannot enter center duct, the foreign matter after now consuming kinetic energy cannot be entered gas compressor by import water conservancy diversion leaf resistance shelves, plays the effect of protection core engine.
The present invention is different from existing turbofan engine structure in sum, have the following advantages and high-lighting effect: (1) improves the thermal efficiency of aeroengine, the most important to be turbofan engine provided by the present invention be a kind of can carry out superelevation sonic flight aeroengine (2) center duct and casing have dual-cooled system, all can provide cooling.Former intrinsic and full-fledged cooling system and the cooling system pointed by the present invention can and deposit.Leaf temperature can be reduced to scope of design by two cover systems rapidly.(3) inlet guide vane has dual functions, is air inlet and protection respectively.Reduce the air inlet to turbogenerator when high-speed flight, when generation bird hits or other object enters motor, inlet guide vane can, as one barrier, make foreign matter discharge, to core engine with margin of safety from center duct throat.(4) thermal boundary to empty resistance and high-speed flight of fundamentally disappearance hair loss motivation fairing cone.
The invention describes a case study on implementation of above-mentioned ring jet formula double rotor turbofan aeroengine, should it is easily understood that the present invention be not limited to embodiment disclosed in these.Conversely, can revise the present invention with combine do not describe before this many modification, change, replacement or equivalent arrangements, but it is suitable with the spirit and scope of the present invention.In addition, but should be understood that, the invention is not restricted to turbofan aeroengine details and the air-flow method of operation of foregoing description, but the content containing claims to limit, and amplify thus and the equivalence principle of being out of shape and structure.
Claims (9)
1. a ring jet formula double rotor turbofan aeroengine, is characterized in that: agent structure is hollow turbofan aeroengine; The through whole motor of center duct (5) and ingress has electric fan to extend to center; Duct rear portion, center has controlled throat (15); Throat's short flabellum of front end larynx formula (11); There is between flabellum center duct inlet (12); Duct inlet rear portion, center has afterbody gas compressor (19); High and low pressure turbine dish has tilted air holes (18); Center duct discharge portion is lobe shape jet pipe (17), it is connected with low pressure rotor by brush seal, containing fuel nozzle in jet pipe, necessary parts needed for the pressed engine such as igniter and flame holder, front end fan outer rim and runner band are equipped with magnetic bearing (16) and calutron.
2. motor according to claim 1, it is characterized in that duct (5) ingress, described center has fan (3) flabellum to extend to center, the short flabellum of larynx formula is tail end closing in shape blade, if sense of rotation is clockwise, the short flabellum of larynx formula (11) is manufacture counterclockwise.
3. motor according to claim 1, is characterized in that described controlled throat (15) separates diffuser and distance piece.
4. motor according to claim 1, is characterized in that the short flabellum of larynx formula (11) becomes the cleaning device in order to clean extracting air at front-end structure.
5. motor according to claim 1, it is characterized in that afterbody gas compressor have air intake valve to enter air filtering and control, and also there is valve in relief opening, controls air mass flow.
6. motor according to claim 1, is characterized in that described low pressure rotor axle afterbody has calm the anger flabellum and air cavity and tail cone and forms afterbody air compressor structure.
7. motor according to claim 1, is characterized in that described turbine coolant discharging system, has air cavity, turbine disk tilted air holes, valve.
8. motor according to claim 1, it is characterized in that described front end fan outer rim and runner band are equipped with magnetic bearing (16) or rolling bearing and casing Upper shaft sleeve paired, axle sleeve is furnished with circuit, produces high-frequency voltage.
9. motor according to claim 2, it is characterized in that described throat front end larynx formula short flabellum (11) blade is reticular structure, blade height is less than 10% of center duct (5) diameter, and increases highly to the back-end.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510136365.1A CN104863751B (en) | 2015-03-27 | 2015-03-27 | Ring jet formula birotor turbofan aero-engine |
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| CN201510136365.1A CN104863751B (en) | 2015-03-27 | 2015-03-27 | Ring jet formula birotor turbofan aero-engine |
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| CN104863751A true CN104863751A (en) | 2015-08-26 |
| CN104863751B CN104863751B (en) | 2017-12-26 |
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| CN201510136365.1A Expired - Fee Related CN104863751B (en) | 2015-03-27 | 2015-03-27 | Ring jet formula birotor turbofan aero-engine |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105512408A (en) * | 2015-12-14 | 2016-04-20 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Trisection grooving prefabrication method for disc, blade and shaft integrated turbine rotor with ultrahigh rotation speed |
| CN107559103A (en) * | 2017-09-14 | 2018-01-09 | 王闯业 | A kind of birotor punching engine |
| CN108049985A (en) * | 2018-01-29 | 2018-05-18 | 余四艳 | Rotary ejection type variable cycle aero-jet engine |
| CN108310926A (en) * | 2018-04-25 | 2018-07-24 | 大连恒通和科技有限公司 | Combustion tail gas processing and heat reclaim unit |
| CN108412615A (en) * | 2018-04-25 | 2018-08-17 | 大连恒通和科技有限公司 | Vortex-spraying type power generation combustor |
| CN108489083A (en) * | 2018-04-25 | 2018-09-04 | 大连恒通和科技有限公司 | Complete hot swirl penetrates formula water heater |
| CN108518673A (en) * | 2018-04-25 | 2018-09-11 | 大连恒通和科技有限公司 | Vortex-spraying type combustor |
| CN110793399A (en) * | 2019-11-08 | 2020-02-14 | 江苏兆胜空调有限公司 | Infrared suppression device |
| CN112160835A (en) * | 2019-11-03 | 2021-01-01 | 谭健 | Combustion chamber of turbofan aircraft engine |
| CN113446128A (en) * | 2021-08-09 | 2021-09-28 | 无锡友鹏航空装备科技有限公司 | Self-cleaning engine |
| CN114483366A (en) * | 2022-02-24 | 2022-05-13 | 中国商用飞机有限责任公司 | Tail jet pipe assembly and jet system |
| CN115143489A (en) * | 2022-06-15 | 2022-10-04 | 南京航空航天大学 | Combustion chamber suitable for full-ring large-scale cyclone air intake |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105512408A (en) * | 2015-12-14 | 2016-04-20 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Trisection grooving prefabrication method for disc, blade and shaft integrated turbine rotor with ultrahigh rotation speed |
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| CN108412615A (en) * | 2018-04-25 | 2018-08-17 | 大连恒通和科技有限公司 | Vortex-spraying type power generation combustor |
| CN108489083A (en) * | 2018-04-25 | 2018-09-04 | 大连恒通和科技有限公司 | Complete hot swirl penetrates formula water heater |
| CN108518673A (en) * | 2018-04-25 | 2018-09-11 | 大连恒通和科技有限公司 | Vortex-spraying type combustor |
| CN108518673B (en) * | 2018-04-25 | 2024-04-16 | 大连恒通和科技有限公司 | Vortex spraying type burner |
| CN108310926B (en) * | 2018-04-25 | 2024-01-19 | 大连恒通和科技有限公司 | Combustion tail gas treatment and heat recovery device |
| CN108489083B (en) * | 2018-04-25 | 2023-10-13 | 李宏生 | Total heat jet type water heater |
| CN112160835A (en) * | 2019-11-03 | 2021-01-01 | 谭健 | Combustion chamber of turbofan aircraft engine |
| CN110793399A (en) * | 2019-11-08 | 2020-02-14 | 江苏兆胜空调有限公司 | Infrared suppression device |
| CN113446128B (en) * | 2021-08-09 | 2022-06-14 | 无锡友鹏航空装备科技有限公司 | Self-cleaning engine |
| CN113446128A (en) * | 2021-08-09 | 2021-09-28 | 无锡友鹏航空装备科技有限公司 | Self-cleaning engine |
| CN114483366A (en) * | 2022-02-24 | 2022-05-13 | 中国商用飞机有限责任公司 | Tail jet pipe assembly and jet system |
| CN115143489A (en) * | 2022-06-15 | 2022-10-04 | 南京航空航天大学 | Combustion chamber suitable for full-ring large-scale cyclone air intake |
| CN115143489B (en) * | 2022-06-15 | 2023-08-11 | 南京航空航天大学 | Combustion chamber suitable for full-ring large-scale rotational flow air intake |
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