CN204283661U - A kind of turbofan aeroengine center cone goes out the structure that stream increases thrust - Google Patents
A kind of turbofan aeroengine center cone goes out the structure that stream increases thrust Download PDFInfo
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- CN204283661U CN204283661U CN201420777062.9U CN201420777062U CN204283661U CN 204283661 U CN204283661 U CN 204283661U CN 201420777062 U CN201420777062 U CN 201420777062U CN 204283661 U CN204283661 U CN 204283661U
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Abstract
A kind of turbofan aeroengine center cone goes out the structure that stream increases thrust, comprise center cone, center cone periphery is followed successively by intension passage, outer culvert passage, it is characterized in that: center cone inside forms convergent narrow-gap channel, and turbine support plate is between outer culvert passage and narrow-gap channel; Narrow-gap channel circulation area reduces vertically gradually; Center cone wall is offered a series of non-rule arrangement flow-out hole, its aperture reduces vertically gradually, and hole array pitch and hole arrange distance according to flow parameter along journey preferred arrangement.The utility model structural feature is, in center cone internal condition air flow rate and pressure evolution with distance rule, builds convergent narrow-gap channel, and the inner flow velocity of narrow-gap channel is substantially constant; According to air-flow differential evolution with distance rule inside and outside center cone, center cone wall is divided into 4 sections along journey, according to each section of aerodynamic parameter feature, wall is arranged different flow-out holes.
Description
Technical field
The utility model belongs to motor power increase technology, is specifically related to one by aeroengine center cone, and make the outer air-flow of containing of part heat supercharging, accelerated expansion discharge, flow losses after reduction center cone tail, improve the system of motor power simultaneously.
Background technique
Along with the raising that aircraft agility requires, require constantly to promote to engine thrust-weight ratio.At present, along with the raising required air maneuver, agility, engine thrust-weight ratio requires also to improve rapidly, and the development of aircraft relies on realization and the improvement of new concept propulsion system to a great extent.60 ~ seventies of 20th century turbofan engine appearance, make the flying speed of fighter, voyage and mobility occur historic leap.In the past few decades, engine thrust-weight ratio brings up to 8 ~ 10 from 1 ~ 2, estimates that the thrust weight ratio of 21 century first 20 years fighter engines likely reaches 15 ~ 20, for the world the 5th generation operational aircraft in future provides indispensable, unprecedented very strong driving force.
Thrust weight ratio is an important indicator of measured engine performance, is also the composite target of the design of measured engine, material and processing technology level.Thrust weight ratio all has a direct impact the flight performance of aircraft and useful load etc., and vertical and short field aircraft especially needs the motor of high thrust weight ratio.
The thrust weight ratio of modern turbojet engine is between 3.5 ~ 4.5, and afterburning turbojet engine is about 5 ~ 7; Augmented turbofan engine can reach more than 8; Lift engine can reach more than 16, for the vertical take off and landing (VTOL) of aircraft.Further raising thrust weight ratio is an important trend of aeroengine development.In April, 2005, first the high thrust weight ratio turbofan engine that China develops voluntarily is lighted a fire successfully, for the advanced aero engine further developing out high thrust weight ratio has established technical foundation.
The representation of aeroengine thrust is:
F＝mU
x+(p
e-p
a)A
e
In formula, m is the actual mass flow U of jet pipe
x, p
e, A
erepresent the axial velocity of nozzle exit, static pressure and area respectively, p
afor environment static pressure.
Can find out, in engine export area A
eunder constant condition, improve motor power and mainly contain following several approach:
(1) air mass flow is increased
Motor power can use the product representation of air mass flow and specific thrust.If engine air capacity increases, and motor specific thrust is constant or decline by a small margin, and motor power can be made to increase, and this improves the comparatively direct and effective method of thrust.
Because engine intake air mass flow is mainly by the diameter of fan and the restriction of rotating speed, improve air mass flow mainly can pass through: one is expand fan diameter, fan inlet anchor ring is long-pending to be increased thereupon, can increase air mass flow when axial velocity is constant, two is redesign the larger Fan/Compressor Operated of flow.
(2) turbine inlet temperature (TIT) is improved
Turbine inlet temperature is the important parameter affecting engine performance level, and improving turbine inlet temperature is also one of major measure improving motor power, is the important symbol of aeronautical technology progress simultaneously.When overall pressure tatio is constant, turbine inlet temperature (TIT) improves, and adds ratio of specific heat and increases, and the specific thrust of motor improves.The raising of turbine inlet temperature (TIT) needs by realizing the optimal design of firing chamber, by the design of high temperature rise combustor, improves the outlet temperature of firing chamber.This all will have higher requirement to the heatproof level of the design of firing chamber and the material of turbine, and at present, domestic air mail Engine Industry is carrying out research in this respect.
(3) total pressure ratio is improved
Along with total pressure ratio increases, the available work of motor improves, and specific thrust increases, the corresponding high total pressure ratio of high thrust.Realize pressure ratio to increase, can by carrying out the optimization Transform Type design of press machine progression and size, it must relate to the redesign to gas compressor.In design process, while raising the efficiency, prevent asthma, optimize blade structure.
(4) bypass ratio is improved
Bypass ratio is the ratio of the air mass flow by outer culvert fan and intension core engine.Engine core machine changes in flow rate is little, and the air mass flow overwhelming majority of increase flows through from by-pass air duct, therefore, the bypass ratio of motor is increased.Under the condition that engine core machine flow is constant, increase bypass ratio, can only realize by increasing outer culvert channel size, this just relates to the structural adjustment of inlet casing.
Make a general survey of above measure, measure (one)-(four) are although can improve the thrust of aeroengine, but often kind of measure all needs to carry out improvement in various degree and even redesign to the core component in motor, there is larger difficulty, more be applicable to the development of motor of new generation, then inapplicable to the Curve guide impeller of available engine, in addition, this design improvement cycle is comparatively very long.In addition, be subject to the restriction such as material, processing technology, make the improvement of aeroengine thrust characteristic be subject to larger restriction.
Above pushing measure is carried out mainly for intension air-flow, and in turbofan engine, outer culvert air-flow is also the significant contribution person of thrust, compare intension gas flow, its quality is suitable, but gas flow temperature, pressure are less, make momentum less, this also illustrates that the momentum of outer culvert air-flow has larger room for promotion.If heated externally containing air-flow, make its acceleration of expanding, temperature, pressure raise, then it will increase greatly to the contribution of thrust.
Within the engine, the main loss of jet pipe refers to pitot loss, and it comprises local air flow loss and along journey frictional loss.After center cone tail, there is vortex after stronger tail, after inside and outside culvert air-flow is mixed, produce larger local air flow loss, have a strong impact on motor power feature, according to the study, under motor different operating state, the local air flow loss that after tail, vortex produces accounts for the 2-5% of jet pipe pitot loss.
Model utility content
The utility model basic thought is, the high temperature intension gas flow heating of center cone flows outside is utilized to flow into the outer culvert air-flow of center cone, corresponding outer culvert flow expansion is accelerated, momentum increases, then flowed out by the flow-out hole on center cone wall, mix with intension air-flow and flow out jet pipe, improve motor power; Simultaneously by the flow-out hole that the cone of the heart within the engine tail end layout optimization arranges, go out stream after utilizing center cone tail and weaken vortex after tail, reduce jet pipe pitot loss, improve motor power.
Method is that its circulation area reduces vertically gradually at center cone internal placement convergent narrow-gap channel, makes airspeed substantially constant; Offer a series of flow-out hole at center cone wall, discharge from flow-out hole after the outer culvert air-flow entering center cone is heated.
Concrete technological scheme is as follows: at center cone internal build narrow-gap channel, arrange a series of flow-out hole at wall.By turbine support plate, outer culvert gas lower to temperature, pressure is introduced narrow-gap channel, high temperature intension gas flow heat exchange outer with center cone, increasing temperature and pressure, accelerated expansion, in flow process vertically, flow out center cone by flow-out hole, corresponding air-flow momentum is improved; Meanwhile, optimize the layout of terebrantia flow-out hole, go out stream by terebrantia air-flow, weaken cone tail rear portion vortex, reduce engine jet pipe local pitot loss.Above-mentioned two aspects comprehensively use, and can significantly improve the thrust of motor.This pushing form structure is simple, easily realizes, does not need to change engine core parts.
The utility model structural feature is, in center cone internal condition air flow rate and pressure evolution with distance rule, builds convergent narrow-gap channel, and the inner flow velocity of narrow-gap channel is substantially constant; According to air-flow differential evolution with distance rule inside and outside center cone, center cone wall is divided into 4 sections along journey, according to each section of aerodynamic parameter feature, wall is arranged different flow-out holes.
Implementation procedure is as follows: a kind of turbofan aeroengine center cone goes out the structure that stream increases thrust, comprise center cone, center cone periphery is followed successively by intension passage, outer culvert passage, it is characterized in that: center cone inside forms convergent narrow-gap channel, and turbine support plate is between outer culvert passage and narrow-gap channel; Narrow-gap channel circulation area reduces vertically gradually; Center cone wall is offered a series of non-rule arrangement flow-out hole, its aperture reduces vertically gradually, and hole array pitch and hole arrange distance according to flow parameter along journey preferred arrangement.
As improvement: center cone is divided into 4 parts vertically, each section of wall lays out discharge orifice, first paragraph flow-out hole, second segment flow-out hole, the 3rd section of flow-out hole, the 4th section of flow-out hole is followed successively by cone tail from the import of turbine support plate, hole pitch, the hole array pitch of flow-out hole reduce gradually, narrow-gap channel height is followed successively by h1, h2, h3, h4, length is followed successively by L1, L2, L3, L4, wherein, h1<h2<h3<h4, L1>L2>L3>L4.
Further optimization: flow-out hole parameter is defined as follows: aperture is D, aperture and wall angle are α, same row is adjacent, and two flow-out hole spacing are P, the adjacent two flow-out hole array pitch of same row are S, obtaining first paragraph flow-out hole parameter is thus D1, α 1, P1, S1, and second segment flow-out hole parameter is D2, α 2, P2, S2, and the 3rd section of flow-out hole parameter is D3, α 3, P3, S3,4th section of flow-out hole parameter is D4, α 4, P4, S4, and flow-out hole is uniform section hole; Wall axial overall length center cone laying out discharge orifice is L, and for first paragraph L1, D1=3.0mm, α 1=15 ° ~ 25 °, P1 is not more than 10 times of flow-out hole footpath D1, and S1 is not more than 15 times of flow-out hole footpath D1; For second segment L2, D2=2.0mm, α 2=20 °-30 °, P2 is not more than 8 times of flow-out hole footpath D2, and S2 is not more than 12 times of flow-out hole footpath D1; For the 3rd section L3, D3=1.2mm, α 3=25 °-35 °, P3 is not more than 6 times of flow-out hole footpath D3, and S3 is not more than 10 times of flow-out hole footpath D3; For the 4th section L4, D4=0.4-0.6mm, α 4=60 °-90 °, P4 is not more than 4 times of flow-out hole footpath D4, and S4 is not more than 6 times of flow-out hole footpath D4.
Part outer culvert air-flow, by turbine support plate, is introduced center cone, is flowed, be subject to the heating of high temperature intension gas flow, accelerated expansion in the narrow-gap channel of center cone inside by the utility model; Along in journey flow process, segment fluid flow is flowed out by flow-out hole, and in narrow-gap channel, total discharge reduces, designed by appropriate flow cross-section areas, regulate fluid-flow rate, keep heat transfer effect substantially constant, overcome the shortcoming that in traditional uniform section passage, heat exchange weakens gradually.Outer culvert air-flow is after journey increasing temperature and pressure, and the flow-out hole arranged from center cone wall flows out, and temperature and pressure all enlarge markedly, and flow out jet pipe after mixing with intension air-flow, and thrust is increased.
In aeroengine, near the axial position corresponding with center cone, intension stream pressure reduces gradually along journey.And the center cone internal gas flow pressure range of decrease is less than intension air-flow, center cone inside and outside differential pressure is increased.Adopt less flow-out hole aperture at center cone back segment wall, reduce and stream flow, weaken its disturbance to intension air-flow, reduce aerodynamic loss, improve motor power.Consider the complexity of structure, the utility model is according to the aerodynamic parameter feature of advanced motor, according to its air-flow differential evolution with distance rule, center cone wall is divided into vertically 4 regions, the flow-out hole in each region carries out difference preferred arrangement, improve the temperature rise level stream entirety, thrust coefficient is improved 0.3%-0.7%.
Consider that the pressure difference of air-flow inside and outside center cone becomes large gradually, and air-flow arranges the impact that slit pressure of sening as an envoy to weakens from flow-out hole along journey, in order to keep air-flow differential inside and outside center cone, narrow-gap channel adopts astringent runner, under subsonics flox condition, passage stream pressure is increased to some extent, be beneficial to back segment go out stream discharge from flow-out hole.Concrete sectional area design consideration actual airflow pressure is determined.
Accompanying drawing explanation
Fig. 1 is aeroengine jet pipe cavity schematic diagram;
Fig. 2 is that aeroengine center cone flow-out hole is along journey distribution map.
In figure, 1-contains passage outward, 2-intension passage, and 3, narrow-gap channel, 4-internal face, 5-turbine support plate, 6-center cone, 7-lobed mixer, 8-flame holder, 9-jet pipe back segment, 10-tail pipe burner cylindrical shell, 11-the 4th section of flow-out hole, 12-the 3rd section of flow-out hole, 13-second segment flow-out hole, 14-first paragraph flow-out hole, 15-outer wall.
Embodiment
Below in conjunction with accompanying drawing and embodiment, the utility model is described in more detail.
If Fig. 1 is aeroengine jet pipe cavity schematic diagram.Aeroengine jet pipe comprises intension passage 2, outer culvert passage 1, lobed mixer 7, flame holder 8, center cone 6, turbine support plate 5, jet pipe back segment 9.Intension passage 2 is contained inside passage 1 outside, and center cone 6 is in intension passage 2, and lobed mixer 7 is arranged on outer culvert passage 1, and flame holder 8 is arranged on lobed mixer 7 downstream, and jet pipe back segment 9 is arranged on tail pipe burner cylindrical shell 10 downstream.Center cone 6 has outer wall 15 and internal face 4, is narrow-gap channel 3 therebetween, and turbine support plate 5 is between outer culvert passage 1 and narrow-gap channel 3; The axial circulation area of narrow-gap channel 3 changes vertically; Outer wall 15 is offered a series of non-rule arrangement flow-out hole, its aperture and setting type according to flow parameter along journey preferred arrangement.The circulation area of narrow-gap channel 3 reduces from import gradually to cone tail vertically.
If Fig. 2 is that center cone flow-out hole is along journey distribution map.Outer culvert passage 1 installs 6 turbine support plates 5 in center cone 6 front end circumference, is connected with center cone 6; Center cone 6 internal placement narrow-gap channel 3, be divided into 4 sections vertically, be highly respectively h1, h2, h3, h4, wherein h1<h2<h3<h4, length is respectively L1, L2, L3, L4, wherein L1>L2>L3>L4.
First paragraph flow-out hole 14 hole array pitch is S1, and hole pitch is P1, and aperture is D1, and aperture and wall angle are α 1; Second segment flow-out hole 13 hole array pitch is S2, and hole pitch is P2, and aperture is D2, and aperture and wall angle are α 2; 3rd section of flow-out hole 12 hole array pitch is S3, and hole pitch is P3, and aperture is D3, and aperture and wall angle are α 3; 4th section of flow-out hole 11 hole array pitch is S4, and hole pitch is P4, and aperture is D4, and aperture and wall angle are α 4.
First paragraph flow-out hole parameter is D1, α 1, P1, S1, and second segment flow-out hole parameter is D2, α 2, P2, S2, and the 3rd section of flow-out hole parameter is D3, α 3, P3, S3, and the 4th section of flow-out hole parameter is D4, α 4, P4, S4, and flow-out hole is uniform section hole; Wall axial overall length center cone laying out discharge orifice is L, and for first paragraph, D1=3.0mm, α 1=15 °-25 °, P1 is not more than 10 times of flow-out hole footpath D1, and S1 is not more than 15 times of flow-out hole footpath D1; D2=2.0mm, α 2=20 °-30 °, P2 is not more than 8 times of flow-out hole footpath D2, and S2 is not more than 12 times of flow-out hole footpath D1; D3=1.2mm, α 3=25 °-35 °, P3 is not more than 6 times of flow-out hole footpath D3, and S3 is not more than 10 times of flow-out hole footpath D3; D4=0.4-0.6mm, α 4=60 °-90 °, P4 is not more than 4 times of flow-out hole footpath D4, and S4 is not more than 6 times of flow-out hole footpath D4.
Claims (3)
1. turbofan aeroengine center cone goes out the structure that stream increases thrust, and comprise center cone, center cone periphery is followed successively by intension passage, outer culvert passage, it is characterized in that: center cone inside forms narrow-gap channel, and narrow-gap channel circulation area reduces vertically gradually; Turbine support plate is between outer culvert passage and narrow-gap channel; Center cone wall is offered a series of non-rule arrangement flow-out hole, its aperture reduces vertically gradually, and hole array pitch and hole arrange distance according to flow parameter along journey preferred arrangement.
2. a kind of turbofan aeroengine center cone according to claim 1 goes out the structure that stream increases thrust, it is characterized in that: center cone is divided into 4 parts vertically, each section of wall lays out discharge orifice, first paragraph flow-out hole is followed successively by cone tail from the import of turbine support plate, second segment flow-out hole, 3rd section of flow-out hole, 4th section of flow-out hole, the hole pitch of flow-out hole, hole array pitch reduces gradually, narrow-gap channel height is followed successively by h1, h2, h3, h4, length is followed successively by L1, L2, L3, L4, wherein, h1<h2<h3<h4, L1>L2>L3>L4.
3. a kind of turbofan aeroengine center cone according to claim 1 goes out the structure that stream increases thrust, it is characterized in that: flow-out hole parameter is defined as follows: aperture is D, aperture and wall angle are α, same row is adjacent, and two flow-out hole spacing are P, the adjacent two flow-out hole array pitch of same row are S, obtaining first paragraph flow-out hole parameter is thus D1, α 1, P1, S1, second segment flow-out hole parameter is D2, α 2, P2, S2,3rd section of flow-out hole parameter is D3, α 3, P3, S3,4th section of flow-out hole parameter is D4, α 4, P4, S4, and flow-out hole is uniform section hole; Wall axial overall length center cone laying out discharge orifice is L, and for first paragraph, D1=3.0mm, α 1=15 °-25 °, P1 is not more than 10 times of flow-out hole footpath D1, and S1 is not more than 15 times of flow-out hole footpath D1; D2=2.0mm, α 2=20 °-30 °, P2 is not more than 8 times of flow-out hole footpath D2, and S2 is not more than 12 times of flow-out hole footpath D1; D3=1.2mm, α 3=25 °-35 °, P3 is not more than 6 times of flow-out hole footpath D3, and S3 is not more than 10 times of flow-out hole footpath D3; D4=0.4-0.6mm, α 4=60 °-90 °, P4 is not more than 4 times of flow-out hole footpath D4, and S4 is not more than 6 times of flow-out hole footpath D4.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420777062.9U CN204283661U (en) | 2014-12-10 | 2014-12-10 | A kind of turbofan aeroengine center cone goes out the structure that stream increases thrust |
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| CN201420777062.9U CN204283661U (en) | 2014-12-10 | 2014-12-10 | A kind of turbofan aeroengine center cone goes out the structure that stream increases thrust |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104454234A (en) * | 2014-12-10 | 2015-03-25 | 南京航空航天大学 | Structure for increasing thrust by outflow from turbofan central cone |
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- 2014-12-10 CN CN201420777062.9U patent/CN204283661U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104454234A (en) * | 2014-12-10 | 2015-03-25 | 南京航空航天大学 | Structure for increasing thrust by outflow from turbofan central cone |
| CN104454234B (en) * | 2014-12-10 | 2016-06-29 | 南京航空航天大学 | A kind of turbofan aero-engine center cone goes out stream increases the structure of thrust |
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| AV01 | Patent right actively abandoned |
Granted publication date: 20150422 Effective date of abandoning: 20160629 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |