CN104675556A - Large-bypass-ratio turbofan engine of vane tip jet driven fan - Google Patents
Large-bypass-ratio turbofan engine of vane tip jet driven fan Download PDFInfo
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Abstract
The invention provides a large-bypass-ratio turbofan engine of a vane tip jet driven fan and a designing method. A large-bypass-ratio fan rotor driven by vane tip jet is arranged on an external duct portion and comprises an additional ducted fan rotor, a vane tip driving portion and a rotary additional duct rotor hub; an additional duct stator is arranged on a downstream portion of the additional ducted fan rotor and a downstream portion of a vane tip driving portion; and air is led to vane tips of the additional ducted fan rotor from an external duct of the original double-rotor turbofan engine by an air leading channel. The large-bypass-ratio turbofan engine of the vane tip jet driven fan has the advantages that the bypass ratio is increased, torque transmission is implemented by an aerodynamic force, and the problem that the rotation speed of the fan is not matched with that of the driving component; the peripheral speed is greatly improved, and the improvement potential of the bypass ratio is high; compared with the prior art, the large-bypass-ratio turbofan engine is simple in structure; and the large-bypass-ratio turbofan engine is improved on the basis of the existing double-rotor turbofan engine, development risk and the development cost of the large-bypass-ratio turbofan engine of the vane tip jet driven fan are reduced, and the development cycle is shortened.
Description
Technical field
What the present invention relates to is a kind of large Bypass Ratio Turbofan Engine of blade tip reaction driving fan, belongs to new ideas turbofan engine technical field.
Background technique
Higher thrust weight ratio and more low-fuel-comsuption rate are the target of aeroengine unremitting pursue all the time, and turbofan engine is with the feature of its high thrust weight ratio and low-fuel-comsuption rate, and becoming the main flow of Aeroengine Design gradually, is aeroengine field, various countries core technology.Bypass ratio is one of core parameter of turbofan engine design, and less Bypass Ratio Turbofan Engine has high maneuverability, is usually applied in military domain; The oil consumption rate of large Bypass Ratio Turbofan Engine is low, is usually applied in civil area.The civilian type of Ge great aeroengine company is all to improve constantly the bypass ratio of turbofan engine for one of technical development route.Traditional large Bypass Ratio Turbofan Engine mostly is dual-rotor structure, with low-pressure turbine drive fan and low pressure compressor.Usual turbofan engine design is carried out based on core engine (turbojet engine), and when bypass ratio increases, the flow of core engine is constant, and just the flow of fan increases.Larger flow means that fan external diameter becomes large, now must reduce the rotating speed of fan, to avoid the too high decrease in efficiency problem brought of fan blade tip relative Mach number and the blade tip excessive blade strength problem brought of rim speed, particularly when blade tip relative Mach number is more than 1, fan noise also can be made sharply to increase, and this is very disadvantageous to civil aircraft.On the other hand, the fan of large Bypass Ratio Turbofan Engine is driven by low-pressure turbine, and in order to more extract combustion gas energy, the rim speed of turbine needs to improve.Increase rim speed and have two kinds of modes, one is promote radius, and two is promote rotating speed.And low-pressure turbine is positioned at main duct, by structure and size restrictions, radius is difficult to further lifting, and best mode promotes rotating speed exactly.In order to more excellent pneumatic design, low-pressure turbine and fan two kinds of speed demand conflicting, this contradiction is called (fan and low-pressure turbine) rotating speed mismatch problem is one of key problem of turbofan engine design.
At present, the technical way solving fan and this contradiction of low-pressure turbine has following three kinds:
1. Geared Turbofan Engine (GTF);
Low-pressure turbine, through gear reducer deceleration rear driving fan, can realize that low-pressure turbine rotating speed is high and rotation speed of the fan is low, makes both rotating speeds couplings.But program gear reducer transmitting torque is large, cause the design difficulty of the program very large, have the problem in reliability and life-span concurrently, when especially bypass ratio increases further, rotating ratio also becomes large, and the problems referred to above are more outstanding, becomes the bottleneck that bypass ratio increases further.
2. triple-spool turbofan engine;
Triple-spool motor more reasonably can arrange fan, low pressure compressor, power division between high-pressure compressor and turbine at different levels and rotating speed coupling, and the low-pressure turbine of drive fan can select lower rotating speed.But fan tip radlus contradiction that is large and low-pressure turbine radius little (by structure and size restrictions) does not solve, and just have certain alleviation, when bypass ratio increases further, rotating speed mismatch problem still exists.In addition, the shafting structure that triple-spool is concentric and rotor dynamics problems very complicated, strongly limit the utilization of the program in large Bypass Ratio Turbofan Engine.
3. aft-fan turbofan engine;
The fan of aft-fan turbofan engine is placed in motor rear portion, adopts independently low-pressure turbine to drive, the same with such scheme, alleviate rotating speed matching problem to a certain extent, and turbine and fan is without rotating shaft transmitting torque, avoid the design of concentric shafts system.But its shortcoming is also very remarkable: greatly, integrated manufacturing is difficult to realize for fan and turbine temperature, needs complicated seal structure avoid combustion gas to leak; Secondly, conventional front fan scheme, a part of gas is used by intension, can promote core engine pressure ratio, improve core engine Economy, but for aft-fan scheme, its pressurization gas is directly discharged, and cannot be that core engine is used.These shortcomings make the program in the near future just be substituted by other schemes gradually in appearance.
Summary of the invention
What the present invention proposed is a kind of large Bypass Ratio Turbofan Engine and design method of blade tip reaction driving fan, its objective is and increases turbofan engine bypass ratio further, and the object increase thrust to reach, reducing oil consumption rate, significantly improves motor Economy.The present invention proposes a kind of on general traditional double rotor turbofan engine (see figure 1) basis, increase blade tip reaction driving fan propeller and additional duct large Bypass Ratio Turbofan Engine design concept (as Fig. 2, Fig. 3) and Pneumatic design method (as Fig. 4).
Technical solution of the present invention: the large Bypass Ratio Turbofan Engine of blade tip reaction driving fan, to is characterized in that with double rotor turbofan engine, for prototype, adding an additional duct, introduces blade tip reaction driving fan propeller; This rotor comprises additional ducted fan rotor, blade tip driver part and rotates additional duct rotor hub; In addition, additional duct intake is also had in additional duct, additional shrouded nozzle and additional duct stator; Tap air channel is drawn near pressurization gas to blade tip from containing fan outlet cross section former turbofan engine, and gas is entered the tip segment of additional duct stator, transferred to axis in 5 cross sections by stator after being extracted energy by blade tip driver part by 4 cross sections; Blade tip driver part extracts energy, form driving moment Direct driver and add ducted fan rotor rotary work, the incoming flow being delivered to 1 cross section by additional duct intake is carried out supercharging, this part air-flow is delivered to 2 cross sections through additional ducted fan stator equally, and mix with 5 cross section air, flow into additional shrouded nozzle and spray backward; By said apparatus, blade tip drive fan spinner significantly can be greater than general turbofan engine by-pass air duct flow; According to engine quality additional principle, this new turbofan engine can obtain larger thrust and lower oil consumption rate; Meanwhile, the driver part of additional ducted fan rotor is in large radius, makes it still can keep higher bead wires speed when rotating speed is lower, ensures its acting ability.
Advantage of the present invention: the pressurization gas utilizing original double rotor turbofan engine by-pass air duct, by blade tip reaction driving fan, extracts energy and distributes in more air-flows of additional duct.According to quality additional principle, the amplitude that the reduction Amplitude Ratio quality of exhaust velocity increases is little, and the total momentum of engine exhaust strengthens, and bypass ratio increases, and realizes the pushing consumption reduction of motor.This blade tip reaction driving fan propeller is while significantly increasing bypass ratio, on the one hand by the ingenious transmission achieving power of pneumatic mode, on the other hand driver part is placed in blade tip, avoid the rotating speed contradiction of fan and low-pressure turbine dexterously, the fan comparatively slow-speed of revolution can be kept, blade tip relative Mach number is reduced, reduce fan noise, and the potentiality that bypass ratio is promoted increases greatly.Compared with 3 kinds of schemes of above-mentioned solution large Bypass Ratio Turbofan Engine rotating speed mismatch problem, this programme has more advantage: compared to first kind GTF turbofan engine scheme, program structure is more simple, compact, and reliability is high, life-span is long, and design difficulty is low; Compared to Equations of The Second Kind triple-spool turbofan engine scheme, This solution avoids complicated triple-spool concentric design, the potential that bypass ratio promotes is also larger; Compared to the 3rd class aft-fan turbofan engine scheme, This solution avoids a difficult problem for different materials fan and turbine integration manufacturing, also there is not the complicated densification device of hot and cold air.And the program can be improved on existing double rotor turbofan engine basis, its inner core scheming is pneumatic does not need too much change with structural design, can greatly reduce technical risk and development cost, shortens the lead time.
Comprehensive above advantage, the large Bypass Ratio Turbofan Engine of the blade tip reaction driving fan that the present invention proposes, there is the features such as structure is simple, cost is low, technical difficulty is little, turbofan engine bypass ratio can be significantly improved, increase thrust, reduce oil consumption rate, and then promote with the Economy of its flight instruments being power.Keep the relatively conspicuous number of fan blade tip horse to maintain reduced levels simultaneously, reduce fan noise.
Accompanying drawing explanation
Accompanying drawing 1 is traditional turbofan engine structural representation.
Accompanying drawing 2 (a) is blade tip reaction driving turbofan engine structural representation (air turbine).
Accompanying drawing 2 (b) is blade tip reaction driving turbofan engine structural representation (blade tip jet nozzle).
Accompanying drawing 3 is additional ducted fan rotor figure of band blade tip air turbine.
Accompanying drawing 4 is velocity triangle schematic diagram.
In figure, 1 expression is additional ducted fan, 2 represent additional ducted fan stator, 3 represent tap air channel, 4 represent additional duct casing, 5 expressions rotate additional duct rotor hub, and 6 represent additional duct intake, the additional shrouded nozzle of 7 expression, 11 represent blade tip driver part, and wherein additional ducted fan 1, the additional duct rotor hub 5 of rotation, blade tip driver part 11 form blade tip reaction driving fan propeller.8 is prototype double rotor turbofan engine, mainly contain with lower component: 81 is intake duct, 82 is fan propeller, and 83 is fan stator, and 84 represent multistage pressure gas compressor, 85 is firing chamber, 86 is high-pressure turbine, and 87 is low-pressure turbine, and 88 is high pressure rotor rotating shaft, 89 is low pressure rotor rotating shaft, and 80 is jet pipe.
1 cross section represents additional ducted fan rotor inlet, 12 cross sections and 4 cross sections form additional ducted fan rotor and stator interface jointly, 2 cross sections and 5 cross sections are additional ducted fan stator outlet jointly, 3 cross sections (Fig. 2 (a)) are the import of blade tip air turbine guider, and 34 cross sections (Fig. 2 (a)) is blade tip air turbine guider and rotor interface.In velocity triangle, C represents the absolute velocity (opposite engine) of air-flow, the velocity of moving space that U representative produces due to rotor turns, W represents the relative velocity (relative rotor blade) of air-flow, numeric suffix represents its cross section, place, and subscript m represents axial velocity, and subscript u represents circumferential speed component.
Embodiment
Contrast Fig. 2, the large Bypass Ratio Turbofan Engine of blade tip reaction driving fan, its structure is with double rotor turbofan engine 8(Fig. 1) and for prototype, add an additional duct, introduce blade tip reaction driving fan propeller; This rotor comprises additional ducted fan rotor 1, blade tip driver part 11 and rotates additional duct rotor hub 5(three-dimensional structure sees Fig. 3).In addition, additional duct intake 6 is also had in additional duct, additional shrouded nozzle 7 and additional duct stator 2; Tap air channel 3 is drawn near pressurization gas to blade tip from containing fan outlet cross section 82 former turbofan engine, after gas is extracted energy by blade tip driver part 11, is entered the tip segment of additional duct stator, transferred to axis in cross section 5 by stator by cross section 4.Blade tip driver part extracts energy, form driving moment Direct driver and add ducted fan rotor rotary work, the incoming flow being delivered to cross section 1 by additional duct intake 6 is carried out supercharging, this part air-flow is delivered to cross section 2 through additional ducted fan stator 2 equally, and mix with cross section 5 air, flow into additional shrouded nozzle 7 and spray backward.By said apparatus, blade tip drive fan spinner significantly can be greater than general turbofan engine by-pass air duct flow.According to engine quality additional principle, this new turbofan engine can obtain larger thrust and lower oil consumption rate.Meanwhile, the driver part of additional ducted fan rotor is in relatively large radius place, makes it still can keep higher bead wires speed when rotating speed is lower, ensures its acting ability.Namely additional ducted fan can select lower rotating speed, and the potentiality that motor bypass ratio increases are larger.
Above-mentioned prototype double rotor turbofan engine 8, its structure comprises intake duct 81, fan propeller 82, fan stator 83, multistage pressure compressor stage 84, firing chamber 85, high-pressure turbine level 86, low-pressure turbine stage 87, high-pressure spool 88, low-pressure spool 89, jet pipe 80.
During work, enter the air-flow of prototype turbofan engine intake duct 81, after fan propeller 82 supercharging, a part enters tap air channel 3, and another part enters motor intension.Enter the airflow passes fan stator 83 of intension, multistage pressure gas compressor 84, further adherence pressure, firing chamber 85 of then entering, the high-temperature fuel gas of generation successively enters high-pressure turbine 86, low-pressure turbine 87 expansion work.The power that turbine extracts passes to high-pressure compressor and fan propeller respectively by high-pressure spool 88, low-pressure spool 89, normally works to maintain these parts.This part air-flow last, by jet pipe 80 ejection at a high speed, produces thrust, and the ratio accounting for motor suction total discharge due to interior air flux is very little, therefore this part thrust only accounts for the very fraction of motor gross thrust.The air-flow that another part enters tap air channel is additional ducted fan rotator tip part along with gas circuit causes, and extracts energy by blade tip driver part 11, then after being turned to by additional duct stator tip segment, finally reaches cross section 5.Blade tip driver part extracts flowed energy and obtains driving moment, is directly passed to additional ducted fan rotor, thus the incoming flow of additional duct intake 6 is carried out supercharging.After this part air-flow that additional duct intake 6 is come in is pressurized, transfers axis to by additional duct stator, and be delivered to 2 cross sections, mix with the air-flow in 5 cross sections, and enter additional shrouded nozzle 7 together, sprayed backward by additional duct, produce thrust.The air flow rate at additional shrouded nozzle 7 place contains the outer culvert air mass flow of prototype turbofan engine and the flow of additional duct, and its total discharge is far longer than the part entering intension, is the main source that whole motor power produces.The nominal bypass ratio of this motor is the air mass flow that mixes of cross section 7 and the ratio of air mass flow entering intension.
The present invention is on traditional double rotor turbofan engine basis, its by-pass air duct part introduces the blade tip reaction driving fan propeller that has larger bypass ratio, and this rotor comprises additional ducted fan rotor 1, blade tip driver part 11 and rotates additional duct rotor hub 5.Utilize tap air channel, traditional double rotor turbofan engine by-pass air duct air-flow is caused additional ducted fan blade tip, and blade tip driver part extracts this flowed energy and Direct driver adds ducted fan rotor.Additional ducted fan rotor contains fan outward compared to prototype turbofan engine, can compress, therefore can increase bypass ratio on former turbofan engine basis, make motor significantly promote thrust to more gas, reduces oil consumption rate.Traditional mechanical torsion pass mode conversion is pneumatic torsion pass by one side, solves fan and low pressure rotating speed turbine contradiction, the problems such as the development avoiding complex mechanical structure to bring, reliability, life-span and weight; On the other hand, driver part is positioned at fan leaf nose part, can make fan under comparatively slow-speed of revolution condition, self still keeps stronger acting ability, is conducive to reducing fan blade tip relative Mach number, reduces fan noise.
Described blade tip reaction driving fan propeller, its feature by adding ducted fan rotor 1, be positioned at the rotation at the blade tip driver part 11 of its blade tip and rotor blade root place and add duct rotor hub 5 and form.Flow into the air-flow of the large Bypass Ratio Turbofan Engine core 81 of blade tip reaction driving fan, after fan propeller 82 supercharging, be delivered near additional ducted fan rotator tip by tap air channel 3, and flow into blade tip driver part 11, flow into additional duct stator 2 through flow section 4 after being absorbed most of flowed energy by this blade tip driver part.The driving force that blade tip driver part 11 obtains directly passes to additional ducted fan rotor 1 by blade, makes it the additional duct air-flow supercharging larger to flow.Rotate additional duct rotor hub 5 for isolating the air-flow of additional duct and former double rotor turbofan engine by-pass air duct different pressures.Because blade tip driver part 11 is positioned at the larger additional ducted fan rotator tip of radius, therefore under same rotor condition, (without the need to speed changer) solves fan wheel rim rotational velocity and the inharmonic problem of driver part rotational velocity.
Described additional duct stator 2, its effect transfers the tangential-velocity component of additional ducted fan rotor 1 and blade tip driver part 11 exit flow to axis, and keep the stream pressure that fan propeller exports and blade tip driver part exports to keep balancing, with Appropriate application energy of trying one's best.Because this stator operating temperature is not high, hollow blade and lightweight material can be selected as required, to reduce engine weight.
Described tap air channel 3, its effect is that the pressurized air stream of former double rotor turbofan engine by-pass air duct is caused additional ducted fan rotator tip region, drives additional ducted fan rotor.The design form of tap air channel, two kinds are had: 1. blade tip driver part 11 adopts blade tip air driven turbine form according to driving the mode of additional ducted fan rotor different, then this tap air channel is made up of the gas circuit of adding in duct stator 2 and additional duct casing 4, and places the guider 10 of blade tip air turbine at tap air channel outlet 34 place.2. blade tip driver part 11 adopts the form of blade tip jet nozzle, then this tap air channel is made up of the gas circuit of adding in ducted fan rotor, and at blade tip, air-flow is introduced jet nozzle.
Described additional duct intake 6, its major function be ensure as far as possible to enter additional duct airflow smooth Uniform Flow and deceleration diffusion is carried out to air-flow, be beneficial to flying speed higher time the fan added in duct efficiently work.Additional duct intake can use for reference the intake duct technology of conventional large Bypass Ratio Turbofan Engine.After the large Bypass Ratio Turbofan Engine of blade tip reaction driving fan of the present invention is equipped with additional duct intake, its flight Mach number scope adapted to is wider, can work under high-subsonic flight condition.
Described additional shrouded nozzle 7, its purpose of design coordinates with additional duct intake, additional duct is worked under lower axial flow velocity, after then the flow expansion of supercharging in additional duct being accelerated, accelerates ejection, make motor obtain the thrust increased from additional duct.This jet pipe does not mix with the exhaust of former double rotor turbofan engine jet pipe 80, therefore its length is shorter; And this road air-flow non high temperature, jet pipe can select lightweight material, further weight reduction.
Described additional ducted fan rotor 1, is characterized in that by its flow
m f (pressure ratio
π f , efficiency
η f ) the nominal bypass ratio determined
bcompare and contain partial discharge outward with former double rotor turbofan engine
m c (pressure ratio
π c , efficiency
η c ) bypass ratio determined
b 'larger, above-mentioned parameter has following relation:
.At selected additional ducted fan rotor hub
hratio and inflow Mach number
m in after, can with the tip radlus of flow formula determination fan propeller
r point .For fan, be first estimated to take selected loading coefficient
, then have:
, wherein
, once determine
u point then pressure ratio can be calculated
π f .In order to make air turbine and fan propeller mixing loss minimum, and meet energy balance condition
w t =
w f , have through deriving:
, wherein
, can solve
u point and rotating speed
n.Can see, rotating speed
nlower (
u point little) time, bypass ratio
blarger.The low one side of rotating speed can realize larger bypass ratio, extraction flow increase (flow being additional duct of increase) that the jet-driven large bypass ratio Duct-Burning Turbofan of band blade tip is total, and the available energy of motor is divided equally by larger flow.The amplitude increased due to the reduction Amplitude Ratio quality of exhaust velocity is little, therefore engine exhaust total momentum increases, and correspond to thrust increases, and oil consumption rate reduces.Fan propeller relative velocity is known on the other hand by velocity triangle (Fig. 4)
, rotating speed is then low
u 1little, rotor inlet relative velocity (relative Mach number) can be reduced, avoid fan blade tip to occur supersonic speed situation, reduce fan design difficulty, avoid the noise nuisance that blade tip brings because of supersonic speed simultaneously.
Described blade tip driver part 11, its structure is positioned at additional ducted fan rotator tip, and its rotating speed is all mutually with fan propeller rotating speed
n, flow
m t with double rotor turbofan engine by-pass air duct flow
m c equal.Because it is positioned at fan blade tip, therefore turbine circumference speed
, according to energy balance condition, have
, wherein
(Fig. 4) be turbine loading coefficient.Can find out, when
blarger (
nless), then turbine loading coefficient is larger; In order to avoid turbine occurs across sound and even Supersonic phenomenon,
h t unsuitable excessive, corresponding rotating speed
nshould not be too little; Therefore rotating speed
nalso be the key parameter of air turbine designs, choosing
nin time, needs to consider fan and turbine, makes both design difficulty suitable; When
h t time large, again choose rotating speed
n, calculate
h f , then calculate
h t , iterate; The blow down ratio of air turbine
π t obtained by following formula:
.By parameters such as blow down ratio, flow and efficiency, air driven turbine rotor pneumatic modelling can be obtained by existing aero-turbine design method design, or existing designs of nozzles method design obtains blade tip jet nozzle.Compared with the low-pressure turbine of the large Bypass Ratio Turbofan Engine of tradition, this air turbine can still keep higher peripheral velocity compared with under the slow-speed of revolution
u t , the acting ability drive fan rotor making turbine still keep stronger under not high loading coefficient, solves rotating speed mismatch problem.By matched design, fan and air turbine can be made all to obtain preferably performance, realize the design of large Bypass Ratio Turbofan Engine simultaneously.
Described blade tip air turbine, is arranged in additional ducted fan rotator tip, the center of gravity of blade amass folded direction and bending direction should with the trend correlation of fan blade, the blade root place of this blade tip air turbine with crossette, for being connected with fan blade (Fig. 3).Blade tip air turbine plays extraction air energy, the effect of drive fan rotor turns.Crossette not only plays connection function, also plays the effect of the gas of different pressures near isolation fan and turbine blade.Air turbine guider supporting is with it arranged in the outer casing of additional duct, plays and is accelerated and the effect of leading by the air of tap air channel, makes air spray to air turbine rotor at a high speed.The air turbine guider in this blade tip air turbine and front thereof, all can adopt low denseness turbine vane type designing technique to obtain its primitive blade profile, and amasss superimposition bending mode by aforementioned center of gravity and generate three-dimensional modeling.Because the operating temperature of air turbine is not high, its rotor can adopt hollow blade and lightweight material, to reduce leaf weight.
Described blade tip jet nozzle, the blade tip being arranged in fan blade is inner, nozzle interior passage trend is consistent with the mean camber line of fan blade tip, and near jet expansion direction and fan blade trailing edge the angle in mean camber line direction within the specific limits, to reduce mixing loss.The effect of nozzle is that the pressurized gas of intension being drawn accelerate ejection, and produce reaction force drive fan rotor and rotate, the passage of bleed is positioned at fan rotor blade inside, and fan rotor blade must adopt hollow blade.The effect of this jet nozzle is consistent with blade tip air turbine in fact, can think that jet nozzle has the aerodynamic parameter of equivalence with it.By the Aerodynamic Characteristic Calculation Methods same with blade tip air turbine, the parameters such as nozzle flow, jet velocity, jet direction can be obtained, according to existing designs of nozzles technology, the pneumatic modelling of nozzle can be obtained afterwards.
The design method of the large Bypass Ratio Turbofan Engine of blade tip reaction driving fan, comprises the steps:
1) selected prototype double rotor turbofan engine.After prototype is selected, the main duct overall pressure tatio of motor and turbine inlet temperature are determined all, and these two parameters have reached the limit of present material and manufacturing process all usually.This patent only need carry out following improvement to fan by-pass air duct part;
2) bypass ratio be improved after this motor increases additional duct is first tentatively determined
b, and then calculate annex ducted fan flow
m f , and design fan hub ratio and obtain tip radlus
r point; Select the loading coefficient of fan
h f after, utilize former double rotor turbofan engine to contain air energy and the minimum condition of mixing loss outward according to maximum, have
, wherein
, obtain fan propeller tip speed
u pointand rotating speed
.Again by
, obtain additional ducted fan pressure ratio
π f .
3) design of blade tip driver part, for air turbine.Its flow is that former double rotor fan contains flow outward
m t =
m c , its loading coefficient is determined by following formula
.In fact, when fan pressure ratio is
π f time, rotating speed
nwith loading coefficient
h f relevant, choose
nlow, then
h f height, corresponding loading coefficient turbine
h t also high;
h t one of judge criterion of turbine design difficulty, particularly
h t after exceeding certain value, turbine needs to adopt Supersonic or across sound design, be even difficult to design.The blow down ratio of blade tip driver part is obtained by following formula
.After obtaining the parameter such as flow, blow down ratio, draw additional duct and turn stator import and export velocity triangle and air turbine velocity triangle (see figure 4).One dimension estimation aspect is taken turns iteration optimization by and determined each cross section parameter, especially preferably suitable rotating speed
n, make turbine and fan all can obtain good aeroperformance; When driver part selects jet nozzle, its function under rotating coordinate system is consistent with air turbine, can have " velocity triangle " of equivalence with it, but its outlet relative velocity
w 4 should with the relative velocity of fan outlet
w 12 direction is consistent;
4) according to the velocity triangle of gained, the additional duct of design turns stator, the meridional channel of blade tip driver part (and stator) and pneumatic external form.Carry out three-dimensional optimized design by computational fluid mechanics technology, make additional duct turn stator, blade tip driver part best performance;
5) according to the pressure of the additional ducted fan of the large Bypass Ratio Turbofan Engine of blade tip reaction driving after optimization
π f ratio, flow
m f , efficiency
η f parameter, can obtain additional ducted fan rotor and stator pneumatic modelling thereof according to current existing aerial engine fan design method design;
6) according to the blow down ratio of the blade tip driver part after optimization
π t , flow
m t , efficiency
η t (be equivalent parameters for jet nozzle), according to blade tip air turbine, then can obtain air driven turbine rotor and stator pneumatic modelling thereof according to current existing aero-turbine design method design; According to blade tip jet nozzle, then existing designs of nozzles method is utilized to carry out the pneumatic design of nozzle.
7) if select blade tip air turbine to drive, then after the pneumatic modelling obtaining additional ducted fan rotor and blade tip air turbine rotor, crossette design is between the two carried out, crossette thickness should not be too thin, to ensure join strength, also should not be too thick, to ensure the aeroperformance of parts; In addition, crossette should have certain aerodynamic configuration (as similar fin class), to reduce the impact of crossette on air-flow itself.
8) tap air channel is in fact pipe circulation road, according to the parameter such as flow, pressure, temperature of bleed air-flow, adopts the design method of two-dimentional pipe stream, select lower gas flow rate, runner in each parts of fairing, to reduce the aerodynamic loss of stream, completes tap air channel design.Corresponding parts are made hollow simultaneously.
9) specific design of additional duct intake and jet pipe can adopt the relevant design technology of current existing large Bypass Ratio Turbofan Engine to complete respectively.
10) after the parts pneumatic design of all increases or change and General structure scheme have designed, by existing Aeroengine Design technology, detailed structural design has been carried out to these parts, checked intensity and rotor dynamics.So far the large Bypass Ratio Turbofan Engine design of the blade tip reaction driving fan improved on double rotor turbofan engine basis is completed.
Embodiment
For a double rotor turbofan engine, its total discharge is 95.3kg/s, intension overall pressure tatio 23, outer culvert overall pressure tatio 1.7, bypass ratio 5.3, maximum thrust 2546.6dN, corresponding oil consumption rate 1.05kg/(dN*h).After the mode proposed by the present invention carries out Transform Type design, outer culvert overall pressure tatio 1.09, bypass ratio 28.1, pass through ship performance calculation, maximum thrust can arrive 4817.3dN, corresponding oil consumption rate 0.47kg/ (dN*h), and thrust ratio prototype turbofan engine improves 89.1%, oil consumption rate reduces by 55.2%, and performance is greatly improved.Meanwhile, fan blade tip relative Mach number is only about 0.8, is very beneficial for the noise weakening fan.
Claims (9)
1. the large Bypass Ratio Turbofan Engine of blade tip reaction driving fan, to is characterized in that with double rotor turbofan engine, for prototype, adding an additional duct, introduces blade tip reaction driving fan propeller; This rotor comprises additional ducted fan rotor, blade tip driver part and rotates additional duct rotor hub; In addition, additional duct intake is also had in additional duct, additional shrouded nozzle and additional duct stator; Tap air channel is drawn near pressurization gas to blade tip from containing fan outlet cross section former turbofan engine, and gas is entered the tip segment of additional duct stator, transferred to axis in 5 cross sections by stator after being extracted energy by blade tip driver part by 4 cross sections; Blade tip driver part extracts energy, form driving moment Direct driver and add ducted fan rotor rotary work, the incoming flow being delivered to 1 cross section by additional duct intake is carried out supercharging, this part air-flow is delivered to 2 cross sections through additional ducted fan stator equally, and mix with 5 cross section air, flow into additional shrouded nozzle and spray backward; By said apparatus, blade tip drive fan spinner significantly can be greater than general turbofan engine by-pass air duct flow; According to engine quality additional principle, this new turbofan engine can obtain larger thrust and lower oil consumption rate; Meanwhile, the driver part of additional ducted fan rotor is in large radius, makes it still can keep higher bead wires speed when rotating speed is lower, ensures its acting ability.
2. the large Bypass Ratio Turbofan Engine of blade tip reaction driving fan as claimed in claim 1, is characterized in that described blade tip reaction driving fan propeller comprises additional ducted fan rotor, is positioned at the rotation at the blade tip driver part of its blade tip and rotor blade root place and adds duct rotor hub; Flow into the air-flow of blade tip reaction driving fan large Bypass Ratio Turbofan Engine core intake duct, after fan propeller supercharging, be delivered near additional ducted fan rotator tip by tap air channel, and flow into blade tip driver part, flow into additional duct stator through 4 cross sections of flowing after being absorbed most of flowed energy by this blade tip driver part; The driving force that blade tip driver part obtains directly passes to additional ducted fan rotor by blade, makes it the additional duct air-flow supercharging larger to flow; Rotate additional duct rotor hub then for isolating the air-flow of additional duct and former double rotor turbofan engine by-pass air duct different pressures; Because blade tip driver part is positioned at the additional ducted fan rotator tip of large radius, therefore under same rotor condition, solve fan wheel rim rotational velocity and the inharmonic problem of driver part rotational velocity without the need to speed changer.
3. the large Bypass Ratio Turbofan Engine of blade tip reaction driving fan as claimed in claim 1, it is characterized in that described additional duct stator, after being arranged in additional ducted fan rotor, stator tip segment is turned round to different with the mean camber line direction of other parts, turns round to also different; Its effect transfers the tangential-velocity component of additional ducted fan rotor and blade tip driver part exit flow to axis, and keep the stream pressure that fan propeller exports and blade tip driver part exports to keep balancing, with Appropriate application energy of trying one's best; Because this stator operating temperature is not high, hollow blade and lightweight material can be selected as required, to reduce engine weight.
4. the large Bypass Ratio Turbofan Engine of blade tip reaction driving fan as claimed in claim 1, it is characterized in that the design form of described tap air channel, two kinds are had: 1. blade tip driver part adopts blade tip air driven turbine form according to driving the mode of additional ducted fan rotor different, then this tap air channel is made up of the gas circuit of adding in duct stator and additional duct casing, and exports at tap air channel the guider that 34 sections place blade tip air turbine; 2. blade tip driver part adopts the form of blade tip jet nozzle, then this tap air channel is made up of the gas circuit of adding in ducted fan rotor, and at blade tip, air-flow is introduced jet nozzle.
5. the large Bypass Ratio Turbofan Engine of blade tip reaction driving fan as claimed in claim 1, is characterized in that described additional ducted fan rotor, by its flow
m f (pressure ratio
π f , efficiency
η f ) the nominal bypass ratio determined
bcompare and contain partial discharge outward with former double rotor turbofan engine
m c (pressure ratio
π c , efficiency
η c ) bypass ratio determined
b 'larger, above-mentioned parameter has following relation:
; At selected additional ducted fan rotor hub
hratio and inflow Mach number
m in after, can with the tip radlus of flow formula determination fan propeller
r point ; For fan, be first estimated to take selected loading coefficient
, then have:
, wherein
, once determine
u point then pressure ratio can be calculated
π f ; In order to make air turbine and fan propeller mixing loss minimum, and meet energy balance condition
w t =
w f , have through deriving:
, wherein
, can solve
u point and rotating speed
n; Can see, rotating speed
nlower (
u point little) time, bypass ratio
blarger; The low one side of rotating speed can realize larger bypass ratio, the extraction flow increase that the jet-driven large bypass ratio Duct-Burning Turbofan of band blade tip is total, the flow being additional duct of increase, and the available energy of motor is divided equally by larger flow; The amplitude increased due to the reduction Amplitude Ratio quality of exhaust velocity is little, therefore engine exhaust total momentum increases, and correspond to thrust increases, and oil consumption rate reduces; Fan propeller relative velocity is known on the other hand by velocity triangle
, rotating speed is then low
u 1little, rotor inlet relative velocity can be reduced, relative Mach number, avoid fan blade tip to occur supersonic speed situation, reduce fan design difficulty, avoid the noise nuisance that blade tip brings because of supersonic speed simultaneously.
6. the large Bypass Ratio Turbofan Engine of blade tip reaction driving fan as claimed in claim 1, it is characterized in that described blade tip driver part, its structure is arranged in additional ducted fan rotator tip, and its rotating speed is all mutually with fan propeller rotating speed
n, flow
m t with double rotor turbofan engine by-pass air duct flow
m c equal; Because it is positioned at fan blade tip, therefore turbine circumference speed
, according to energy balance condition, have
, wherein
for turbine loading coefficient; Can find out, when
bit is larger,
nless, then turbine loading coefficient is larger; In order to avoid turbine occurs across sound and even Supersonic phenomenon,
h t unsuitable excessive, corresponding rotating speed
nshould not be too little; Therefore rotating speed
nalso be the key parameter of air turbine designs, choosing
nin time, needs to consider fan and turbine, makes both design difficulty suitable; When
h t time large, again choose rotating speed
n, calculate
h f , then calculate
h t , iterate; The blow down ratio of air turbine
π t obtained by following formula:
; By parameters such as blow down ratio, flow and efficiency, air driven turbine rotor pneumatic modelling can be obtained by existing aero-turbine design method design, or existing designs of nozzles method design obtains blade tip jet nozzle; Compared with the low-pressure turbine of the large Bypass Ratio Turbofan Engine of tradition, this air turbine can still keep higher peripheral velocity compared with under the slow-speed of revolution
u t , the acting ability drive fan rotor making turbine still keep stronger under not high loading coefficient, solves rotating speed mismatch problem; By matched design, fan and air turbine can be made all to obtain preferably performance, realize the design of large Bypass Ratio Turbofan Engine simultaneously.
7. the large Bypass Ratio Turbofan Engine of blade tip reaction driving fan as claimed in claim 4, it is characterized in that described blade tip air turbine, be arranged in additional ducted fan rotator tip, the center of gravity of blade amass folded direction and bending direction should with the trend correlation of fan blade, the blade root place of this blade tip air turbine with crossette, for being connected with fan blade; Blade tip air turbine plays extraction air energy, the effect of drive fan rotor turns; Crossette not only plays connection function, also plays the effect of the gas of different pressures near isolation fan and turbine blade; Air turbine guider supporting is with it arranged in the outer casing of additional duct, plays and is accelerated and the effect of leading by the air of tap air channel, makes air spray to air turbine rotor at a high speed; The air turbine guider in this blade tip air turbine and front thereof, all can adopt low denseness turbine vane type designing technique to obtain its primitive blade profile, and amasss superimposition bending mode by aforementioned center of gravity and generate three-dimensional modeling; Because the operating temperature of air turbine is not high, its rotor can adopt hollow blade and lightweight material, to reduce leaf weight.
8. the large Bypass Ratio Turbofan Engine of blade tip reaction driving fan according to claim 4, it is characterized in that described blade tip jet nozzle, the blade tip being arranged in fan blade is inner, nozzle interior passage trend is consistent with the mean camber line of fan blade tip, and the angle of jet expansion direction and fan blade trailing edge mean camber line tangent line within the specific limits, to reduce mixing loss; The effect of nozzle is that the pressurized gas of intension being drawn accelerate ejection, and produce reaction force drive fan rotor and rotate, the passage of bleed is positioned at fan rotor blade inside, and fan rotor blade must adopt hollow blade; The effect of this jet nozzle is consistent with blade tip air turbine in fact, can think that jet nozzle has the aerodynamic parameter of equivalence with it; By the Aerodynamic Characteristic Calculation Methods same with blade tip air turbine, the parameters such as nozzle flow, jet velocity, jet direction can be obtained, according to existing designs of nozzles technology, the pneumatic modelling of nozzle can be obtained afterwards.
9. the design method of the large Bypass Ratio Turbofan Engine of blade tip reaction driving fan, is characterized in that comprising following design procedure:
1) selected prototype double rotor turbofan engine; After prototype is selected, the main duct overall pressure tatio of motor and turbine inlet temperature are determined all, and these two parameters have reached the limit of present material and manufacturing process all usually; This patent only need carry out following improvement to fan by-pass air duct part;
2) bypass ratio be improved after this motor increases additional duct is first tentatively determined
b, and then calculate annex ducted fan flow
m f , and design fan hub ratio and obtain tip radlus
r point; Select the loading coefficient of fan
h f after, utilize former double rotor turbofan engine to contain air energy and the minimum condition of mixing loss outward according to maximum, have
, wherein
, obtain fan propeller tip speed
u pointand rotating speed
; Again by
, obtain additional ducted fan pressure ratio
π f ;
3) design of blade tip driver part, for air turbine; Its flow is that former double rotor fan contains flow outward
m t =
m c , its loading coefficient is determined by following formula
; In fact, when fan pressure ratio is
π f time, rotating speed
nwith loading coefficient
h f relevant, choose
nlow, then
h f height, corresponding loading coefficient turbine
h t also high;
h t one of judge criterion of turbine design difficulty, particularly
h t after exceeding certain value, turbine needs to adopt Supersonic or across sound design, be even difficult to design; The blow down ratio of blade tip driver part is obtained by following formula
; After obtaining flow, blow down ratio parameter, draw additional duct and turn stator import and export velocity triangle and air turbine velocity triangle; One dimension estimation aspect is taken turns iteration optimization by and determined each cross section parameter, especially preferably suitable rotating speed
n, make turbine and fan all can obtain good aeroperformance; When driver part selects jet nozzle, its function under rotating coordinate system is consistent with air turbine, can have " velocity triangle " of equivalence with it, but its outlet relative velocity
w 4 should with the relative velocity of fan outlet
w 12 direction is consistent;
4) according to the velocity triangle of gained, the additional duct of design turns the meridional channel of stator, blade tip driver part and stator and pneumatic external form; Carry out three-dimensional optimized design by computational fluid mechanics technology, make additional duct turn stator, blade tip driver part best performance;
5) according to the pressure of the additional ducted fan of the large Bypass Ratio Turbofan Engine of blade tip reaction driving after optimization
π f ratio, flow
m f , efficiency
η f parameter, can obtain additional ducted fan rotor and stator pneumatic modelling thereof according to current existing aerial engine fan design method design;
6) according to the blow down ratio of the blade tip driver part after optimization
π t , flow
m t , efficiency
η t , be equivalent parameters for jet nozzle, according to blade tip air turbine, then can obtain air driven turbine rotor and stator pneumatic modelling thereof according to current existing aero-turbine design method design; According to blade tip jet nozzle, then existing designs of nozzles method is utilized to carry out the pneumatic design of nozzle;
7) if select blade tip air turbine to drive, then after the pneumatic modelling obtaining additional ducted fan rotor and blade tip air turbine rotor, crossette design is between the two carried out, crossette thickness is unsuitable thin, to ensure join strength, also unsuitable thick, to ensure the aeroperformance of parts; In addition, crossette should have aerodynamic configuration, as similar fin class, to reduce the impact of crossette on air-flow itself;
8) tap air channel is in fact pipe circulation road, according to flow, pressure, the temperature parameter of bleed air-flow, adopts the design method of two-dimentional pipe stream, select lower gas flow rate, runner in each parts of fairing, to reduce the aerodynamic loss of stream, completes tap air channel design; Corresponding parts are made hollow simultaneously;
9) specific design of additional duct intake and jet pipe can adopt the relevant design technology of current existing large Bypass Ratio Turbofan Engine to complete respectively;
10) after the parts pneumatic design of all increases or change and General structure scheme have designed, by existing Aeroengine Design technology, detailed structural design has been carried out to these parts, checked intensity and rotor dynamics; So far the large Bypass Ratio Turbofan Engine design of the blade tip reaction driving fan improved on double rotor turbofan engine basis is completed.
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| CN108374732A (en) * | 2018-04-04 | 2018-08-07 | 朱志胤 | A kind of geostationary punching press aerospace engine and its application method and purposes |
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| CN110162863B (en) * | 2019-05-15 | 2021-07-13 | 北京玮航科技有限公司 | Thermal coupling design method of electric ducted fan |
| CN110222467B (en) * | 2019-06-20 | 2021-05-04 | 北京理工大学 | Analysis method for swing high-speed jet characteristic of underwater engine spray pipe |
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