CN109595041A - Become and recycles big Bypass Ratio Turbofan Engine - Google Patents
Become and recycles big Bypass Ratio Turbofan Engine Download PDFInfo
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- CN109595041A CN109595041A CN201710924605.3A CN201710924605A CN109595041A CN 109595041 A CN109595041 A CN 109595041A CN 201710924605 A CN201710924605 A CN 201710924605A CN 109595041 A CN109595041 A CN 109595041A
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- movable vane
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- bypass ratio
- vane section
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Turbines (AREA)
Abstract
The present invention provides a kind of changes to recycle big Bypass Ratio Turbofan Engine, including multiple turbine guide vanes, the turbine guide vane includes the blade-section of fixed structure, and multiple movable vane sections, the multiple movable vane section is connected by a hinge, and forms a hollow area with the blade-section of the fixed structure；By changing the movable vane section to rotating inside or outside the turbine guide vane, the throat opening area adjusted between two turbine guide vanes is realized.The present invention reduces turbine guide vane flow area under the conditions of high bypass ratio, changes booster stage guide vane established angle, can play booster stage anti-asthma effect；Deflation bring energy loss after booster stage is avoided, realizes whole envelope booster stage without deflation；Intension can provide bigger nargin by more air for the development of motor power.
Description
Technical field
The present invention relates to aero-engine field, in particular to a kind of change recycles big Bypass Ratio Turbofan Engine.
Background technique
Fig. 1 is the structural schematic diagram that twin shaft directly drives big Bypass Ratio Turbofan Engine in the prior art.As shown in Figure 1, general
Twin shaft directly drive big Bypass Ratio Turbofan Engine according to air-flow axial flow direction, will be successively by the wind to air-flow primary compression
Fan, the further booster stage of compression intension air-flow and high-pressure compressor, respectively drive high pressure at the combustion chamber heated to air-flow
The high-pressure turbine and low-pressure turbine of compressor and fan (including booster stage) allow the jet pipe of high-temperature high-pressure air flow high speed ejection.
In order to improve engine propulsive efficiency, more effective method is will to be divided into two-way by the air of engine, one
Compressor, combustion chamber, turbine and the jet pipe of main duct are flowed through in road, and another way flows through outer culvert fan and outer culvert jet pipe.Outer culvert
The ratio between air mass flow and intension air mass flow, we term it bypass ratios.
In entire operating envelope, aircraft changes the performance requirement of engine with working condition and changes.For example, on ground
When face takes off and climbs, aircraft is higher to the thrust requirements of engine.And in cruising condition, oil consumption rate of the aircraft to engine
It is more demanding.
Currently, the general variable cycle engine design method by becoming bypass ratio solves in order to solve above-mentioned this demand,
When i.e. ground takes off and climbs, engine is run under low bypass ratio state, is run under economical cruise Shi Gao bypass ratio state.
Variable cycle engine is followed by changing geometry, size or the position of some components of engine to change its heating power
The engine of ring.The variable cycle engine design method of traditional change bypass ratio is gone out when ground is taken off by improving combustion chamber
Mouth total temperature (current foreign countries have reached between 2000-2100K), and then increase core engine suction capactity, so that flowing through in engine
The air mass flow of culvert is more, realizes low bypass ratio state.But booster stage equilibrium running line decline at this time is larger, component efficiencies decline
More, and booster stage through-current capability is limited, high-pressure compressor import physics flow is practical to be increased insufficient, influences to become circulation
Efficiency.Chamber temperature is high simultaneously, by extreme influence engine thermal end pieces Cooling Design and service life.In economical cruise,
Core engine suction capactity is reduced, so that intension air mass flow is reduced, improves engine propulsive efficiency.But make booster stage total simultaneously
Rise with active line, influences booster stage surge margin, especially in engine coastdown, surge easily occurs for booster stage.Mesh
Before can only by booster stage export deflate solve, however this mode will sacrifice a part by booster stage compression sky
Gas brings energy loss.
Therefore, traditional change bypass ratio designs prevent total temperature is got higher before turbine and booster stage from matching each portion well
The aeroperformance of part reduces and becomes bypass ratio bring items advantage.
Summary of the invention
The technical problem to be solved by the present invention is in order to overcome, take off and climb shape on fanjet ground in the prior art
Under state, combustor exit temperature is high, the development of thrust nargin is limited and engine life is limited, also brings increasing with time-varying bypass ratio
The defects of work of arbitrarily downgrading mismatches provides a kind of change circulation big Bypass Ratio Turbofan Engine, in conjunction with variable turbine guide vane and increases
It arbitrarily downgrades adjustable vane coordination operation, changes aircraft engine duct ratio in real time.
The present invention is to solve above-mentioned technical problem by following technical proposals:
A kind of big Bypass Ratio Turbofan Engine of change circulation, including multiple turbine guide vanes, it is characterized in that, the turbine guide vane
Blade-section and multiple movable vane sections including fixed structure, the multiple movable vane section are connected by a hinge, and with
The blade-section of the fixed structure forms a hollow area；By changing the movable vane section to inside the turbine guide vane
Or external rotation, realize the throat opening area adjusted between two turbine guide vanes.
According to one embodiment of present invention, the movable vane section includes that first segment movable vane section and second segment are movable
One end of blade sections, the first segment movable vane section is connected by one end of first axle and the blade-section of the fixed structure
It connects, one end of the second segment movable vane section is connected by the other end of second hinge and the blade-section of the fixed structure
It connects；
The other end of the first segment movable vane section and the other end of the second segment movable vane section are bonded to each other.
According to one embodiment of present invention, the turbine guide vane further includes adjusting shaft, adjusting shaft armshaft, the first biography
One end of swing arm and the second transmission arm, first transmission arm passes through the first connecting shaft and the first segment movable vane Duan Lian
It connects, one end of second transmission arm is connect by the second connecting shaft with the second segment movable vane section；
The other end of the other end of first transmission arm and second transmission arm passes through third connecting shaft and the tune
The connection of shaft armshaft is saved, the adjusting shaft armshaft is connect with the adjusting shaft.
According to one embodiment of present invention, there is high pressure cold inside the turbine guide vane.
According to one embodiment of present invention, the blade-section of the fixed structure and the first segment movable vane section and
There is slot between the second segment movable vane section, the first segment movable vane section and the second segment movable vane section it
Between have slot.
According to one embodiment of present invention, the movable vane section includes that first segment movable vane section, second segment are movable
Blade sections and third section movable vane section；
One end that one end of the first segment movable vane section passes through first axle and the blade-section of the fixed structure
The other end of connection, the first segment movable vane section is connected by one end of second hinge and the second segment movable vane section
It connects, the other end of the second segment movable vane section is connect by third hinge with one end of the third section movable vane section；
The blade-section that the other end of the third section movable vane section is connected to the fixed structure by adjusting shaft
The other end.
According to one embodiment of present invention, there is high pressure cold inside the turbine guide vane.
According to one embodiment of present invention, the blade-section of the fixed structure and the first segment movable vane section and
There is slot between the third section movable vane section, the first segment movable vane section and the second segment movable vane section it
Between have slot, between the second segment movable vane section and the third section movable vane section have slot.
According to one embodiment of present invention, the booster stage guide vane established angle of the turbine guide vane is string and axial folder
Angle, the range of the angle are 0 ° -90 °.
The positive effect of the present invention is that:
The present invention becomes the big Bypass Ratio Turbofan Engine of circulation and passes through change turbine guide vane flow area, adjustable in conjunction with booster stage
The change of guide vane established angle, with following many advantages:
One, under the conditions of high bypass ratio, reduce turbine guide vane flow area, change booster stage guide vane established angle, can play
Booster stage anti-asthma effect；
Two, deflation bring energy loss after booster stage is avoided, realizes whole envelope booster stage without deflation；
Three, booster stage air bleed valve and corresponding regulating mechanism be can remove in structure；
Four, intension can provide bigger nargin by more air for the development of motor power；
Five, compared with existing traditional technology, under the conditions of identical thrust, total temperature before turbine can be reduced, engine is improved
Service life.
Detailed description of the invention
The above and other feature of the present invention, property and advantage will pass through description with reference to the accompanying drawings and examples
And become apparent, identical appended drawing reference always shows identical feature in the accompanying drawings, in which:
Fig. 1 is the structural schematic diagram that twin shaft directly drives big Bypass Ratio Turbofan Engine in the prior art.
Fig. 2 is that the present invention becomes the structural schematic diagram for recycling the embodiment one of turbine guide vane in big Bypass Ratio Turbofan Engine.
Fig. 3 is that the present invention becomes the arrangement state signal for recycling the embodiment one of turbine guide vane in big Bypass Ratio Turbofan Engine
Figure one.
Fig. 4 is that the present invention becomes the arrangement state signal for recycling the embodiment one of turbine guide vane in big Bypass Ratio Turbofan Engine
Figure two.
Fig. 5 is that the present invention becomes the structural schematic diagram for recycling the embodiment two of turbine guide vane in big Bypass Ratio Turbofan Engine.
Fig. 6 is that the present invention becomes the arrangement state signal for recycling the embodiment two of turbine guide vane in big Bypass Ratio Turbofan Engine
Figure one.
Fig. 7 is that the present invention becomes the arrangement state signal for recycling the embodiment two of turbine guide vane in big Bypass Ratio Turbofan Engine
Figure two.
Fig. 8 is that the present invention becomes the schematic diagram for recycling the booster stage for having adjustable vane in big Bypass Ratio Turbofan Engine.
Fig. 9 is that the present invention becomes the booster stage established angle for recycling big Bypass Ratio Turbofan Engine and turbine guide vane throat opening area connection
The qualitative curve schematic diagram of tune.
Specific embodiment
For the above objects, features and advantages of the present invention can be clearer and more comprehensible, below in conjunction with attached drawing to tool of the invention
Body embodiment elaborates.
The embodiment of the present invention is described with detailed reference to attached drawing now.Now with detailed reference to preferred implementation of the invention
Example, its example is shown in the drawings.In the case of any possible, phase will be indicated using identical label in all the appended drawings
Same or similar part.
In addition, the present invention is said although term used in the present invention is selected from public term
Some terms mentioned in bright book may be that applicant is judged to carry out selection as his or her, and detailed meanings are retouched this paper's
Illustrate in the relevant portion stated.
Furthermore, it is desirable that not only by used actual terms, and be also to the meaning contained by each term
To understand the present invention.
Become bypass ratio design method bring defect based on tradition, the present invention is by changing turbine guide vane circulation area, knot
The coordination operation for closing booster stage adjustable vane realizes that a kind of novel change recycles big Bypass Ratio Turbofan Engine, avoids tradition
The defect for becoming bypass ratio design method, specifically includes fan, the booster stage of adjustable vane, high-pressure compressor, combustion chamber, Yi Zhongke
The turbine and jet pipe of variable geometry IGV.Become the big Bypass Ratio Turbofan Engine of circulation to the present invention with reference to the accompanying drawing to retouch
It states.
Embodiment one:
Fig. 1 is the structural schematic diagram that twin shaft directly drives big Bypass Ratio Turbofan Engine in the prior art.Fig. 2 is that present invention change follows
The structural schematic diagram of the embodiment one of turbine guide vane in the big Bypass Ratio Turbofan Engine of ring.Fig. 3 is that the present invention becomes the big duct of circulation
Than the arrangement status diagram one of the embodiment one of turbine guide vane in fanjet.Fig. 4 is that the present invention becomes the big bypass ratio of circulation
The arrangement status diagram two of the embodiment one of turbine guide vane in fanjet.
As shown in Figures 1 to 4, it includes multiple turbine guide vanes 10 that the present invention, which becomes the big Bypass Ratio Turbofan Engine of circulation, packet
The blade-section 11 and multiple movable vane sections, the multiple movable vane section for including fixed structure are connected by a hinge, and with
The blade-section 11 of fixed structure forms a hollow area, by the variation movable vane section to 10 inside of turbine guide vane or outside
Portion's rotation, realizes the throat opening area adjusted between two turbine guide vanes 10.
Preferably, movable vane section described in the present embodiment includes first segment movable vane section 12 and second segment movable vane
One end of section 13, first segment movable vane section 12 is connect by first axle 14 with one end of the blade-section 11 of fixed structure,
One end of second segment movable vane section 13 is connect by second hinge 15 with the other end of the blade-section 11 of fixed structure.First
The other end of section movable vane section 12 and the other end of second segment movable vane section 13 are bonded to each other.
Turbine guide vane 10 further includes adjusting shaft 16, adjusting shaft armshaft 17, the first transmission arm 18 and the second transmission arm 19,
One end of first transmission arm 18 is connect by the first connecting shaft 181 with first segment movable vane section 12, and the one of the second transmission arm 19
End is connect by the second connecting shaft 191 with second segment movable vane section 13.The other end and the second transmission arm of first transmission arm 18
19 other end is connect by third connecting shaft 182 with shaft armshaft 17 is adjusted, and adjusts shaft armshaft 17 and adjusting shaft 16 connects
It connects.
Further, there is high pressure cold inside turbine guide vane 10.The blade-section 11 and first segment of fixed structure can
There is slot, first segment movable vane section 12 and second segment movable vane between movable vane segment 12 and second segment movable vane section 13
There is slot between section 13.
It is described according to above structure, the present embodiment becomes the working principle for recycling big Bypass Ratio Turbofan Engine: the present embodiment
The blade-section 11 of middle fixed structure, first segment movable vane section 12 and the composition band of second segment movable vane section 13 are certain hollow
Turbine guide vane 10 has high pressure cold inside turbine guide vane 10, for cooling down movable member turbine guide vane 10 inside, connecting
The connects hinge of axis and each section blade makes it guarantee reliably working.The blade-section 11 and first segment of fixed structure are movable
Between blade sections 12 and second segment movable vane section 13, between first segment movable vane section 12 and second segment movable vane section 13,
There is small slot.Due to the pressure difference of internal high pressure cold air and outer combustion gas, cold air can be outside guide vane by the slot
Cooling air film is formed on wall surface.
It under different working condition, is rotated by actuating system and adjusts shaft 16, driven and adjust shaft armshaft 17 and first
Transmission arm 18, the movement of the second transmission arm 19, and the first transmission arm 18 and the second transmission arm 19 drive first segment movable vane respectively
Section 12, second segment movable vane section 13 is around connects hinge guide interlobar part or external rotation, thus change throat opening area between guide vane,
It realizes the through-current capability for adjusting stage of turbine, and then improves engine intension runner through-current capability.
In the present embodiment aviation engine operation take off, climb mode when, pass through expand turbine guide vane throat opening area, adjust
Whole booster stage guide vane established angle improves the air-flow matching of engine components, and then increases intension runner through-current capability, realizes duct
Than becoming smaller, circulation that thrust becomes larger.
Embodiment two:
Fig. 5 is that the present invention becomes the structural schematic diagram for recycling the embodiment two of turbine guide vane in big Bypass Ratio Turbofan Engine.
Fig. 6 is that the present invention becomes the arrangement status diagram one for recycling the embodiment two of turbine guide vane in big Bypass Ratio Turbofan Engine.Fig. 7
Become the arrangement status diagram two for recycling the embodiment two of turbine guide vane in big Bypass Ratio Turbofan Engine for the present invention.
As shown in Figures 5 to 7, it includes multiple turbine guide vanes 20 that the present invention, which becomes the big Bypass Ratio Turbofan Engine of circulation, packet
The blade-section 21 and multiple movable vane sections, the multiple movable vane section for including fixed structure are connected by a hinge, and with
The blade-section 21 of fixed structure forms a hollow area, by the variation movable vane section to 20 inside of turbine guide vane or outside
Portion's rotation, realizes the throat opening area adjusted between two turbine guide vanes 20.
Preferably, movable vane section described in the present embodiment includes first segment movable vane section 22, second segment movable vane
Section 23 and third section movable vane section 24.Wherein, one end of first segment movable vane section 22 passes through first axle 221 and fixed knot
One end of the blade-section 21 of structure connects, and the other end of first segment movable vane section 22 can by second hinge 222 and second segment
One end of movable vane segment 23 connects, and the other end of second segment movable vane section 23 can movable vane by third hinge 231 and third section
One end of segment 24 connects.The blade that the other end of third section movable vane section 24 is connected to fixed structure by adjusting shaft 25
The other end of part 21.By above structure, by the blade-section 21 of fixed structure, first segment movable vane section 22, second segment
Movable vane section 23 and third section movable vane section 24, by the first axle 221, the second hinge 222 that connect each section blade
And third hinge 231 is formed as an integrated structure.
Further, there is high pressure cold inside turbine guide vane 20.The blade-section 21 and first segment of fixed structure can
There is slot, first segment movable vane section 22 and second segment movable vane between movable vane segment 22 and third section movable vane section 24
There is slot between section 23, there is slot between second segment movable vane section 23 and third section movable vane section 24.
It is described according to above structure, the present embodiment becomes the working principle for recycling big Bypass Ratio Turbofan Engine: the present embodiment
The blade-section 21 of middle fixed structure, first segment movable vane section 22, second segment movable vane section 23, third section movable vane section
The 24 certain hollow turbine guide vanes 20 of composition band.There is high pressure cold, for cooling down inside turbine guide vane inside turbine guide vane 20
Movable member, connecting shaft and each section blade connects hinge, so that it is guaranteed reliably working.The blade-section of fixed structure
Between 21 and first segment movable vane section 22 and third section movable vane section 24, first segment movable vane section 22 is movable with second segment
Between blade sections 23, between second segment movable vane section 22 and third section movable vane section 24, there is small slot.Due to interior
The pressure difference of portion's high pressure cold and outer combustion gas, cold air can form cooling air film by slot in guide vane outside wall surface.
It under different working condition, is rotated by actuating system and adjusts shaft 25, drive designs the third being integrated with it
Section movable vane section 24 rotates, and drives connects hinge movement by third section movable vane section 24, being further transferred to second segment can
Movable vane segment 23 and first segment movable vane section 22, make its position change, to change throat opening area between guide vane.It realizes and adjusts
The through-current capability of stage of turbine is saved, turbine difference operating condition lower component Performance Match is improved, engine stabilization is improved and reduction is started
Machine fuel consumption.
Fig. 8 is that the present invention becomes the schematic diagram for recycling the booster stage for having adjustable vane in big Bypass Ratio Turbofan Engine.Fig. 9
Become for the present invention and recycles the booster stage established angle of big Bypass Ratio Turbofan Engine and the qualitative song of turbine guide vane throat opening area joint debugging
Line schematic diagram.
As shown in Figure 8 and Figure 9, the big Bypass Ratio Turbofan Engine of present invention change circulation has the booster stage A of adjustable vane such as
Shown in Fig. 8, established angle can arbitrarily change in a certain range.Preferably, the booster stage guide vane established angle of the turbine guide vane
For string and axial angle, the range of the angle is 0 ° -90 °.
Aviation engine operation reduces turbine guide vane throat opening area in economic circulation state in the present embodiment, and adjustment increases
Guide vane established angle of arbitrarily downgrading improves the air-flow matching of engine components, and then reduces intension runner through-current capability, realizes that bypass ratio becomes
Greatly, the circulation that propulsive efficiency improves.
In conclusion the present invention, which becomes the big Bypass Ratio Turbofan Engine of circulation, passes through change turbine guide vane flow area, in conjunction with
The change of booster stage adjustable vane established angle, with following many advantages:
One, under the conditions of high bypass ratio, reduce turbine guide vane flow area, change booster stage guide vane established angle, can play
Booster stage anti-asthma effect；
Two, deflation bring energy loss after booster stage is avoided, realizes whole envelope booster stage without deflation；
Three, booster stage air bleed valve and corresponding regulating mechanism be can remove in structure；
Four, intension can provide bigger nargin by more air for the development of motor power；
Five, compared with existing traditional technology, under the conditions of identical thrust, total temperature before turbine can be reduced, engine is improved
Service life.
Although specific embodiments of the present invention have been described above, it will be appreciated by those of skill in the art that these
It is merely illustrative of, protection scope of the present invention is defined by the appended claims.Those skilled in the art is not carrying on the back
Under the premise of from the principle and substance of the present invention, various changes or modifications can be made to these embodiments, but these are changed
Protection scope of the present invention is each fallen with modification.
Claims (9)
1. a kind of change recycles big Bypass Ratio Turbofan Engine, including multiple turbine guide vanes, which is characterized in that the turbine guide vane packet
The blade-section and multiple movable vane sections, the multiple movable vane section for including fixed structure are connected by a hinge, and with institute
The blade-section for stating fixed structure forms a hollow area；By change the movable vane section to inside the turbine guide vane or
Outside rotation, realizes the throat opening area adjusted between two turbine guide vanes.
2. as described in claim 1 become recycles big Bypass Ratio Turbofan Engine, which is characterized in that the movable vane section includes
One end of first segment movable vane section and second segment movable vane section, the first segment movable vane section passes through first axle and institute
State one end connection of the blade-section of fixed structure, one end of the second segment movable vane section by second hinge with it is described solid
Determine the other end connection of the blade-section of structure；
The other end of the first segment movable vane section and the other end of the second segment movable vane section are bonded to each other.
3. as claimed in claim 2 become recycles big Bypass Ratio Turbofan Engine, which is characterized in that the turbine guide vane further includes
It adjusts shaft, adjust shaft armshaft, the first transmission arm and the second transmission arm, one end of first transmission arm passes through the first connection
Axis is connect with the first segment movable vane section, and one end of second transmission arm can by the second connecting shaft and the second segment
The connection of movable vane segment；
The other end of the other end of first transmission arm and second transmission arm is turned by third connecting shaft and described adjust
The connection of axis armshaft, the adjusting shaft armshaft are connect with the adjusting shaft.
4. as claimed in claim 3 become recycles big Bypass Ratio Turbofan Engine, which is characterized in that tool inside the turbine guide vane
There is high pressure cold.
5. as claimed in claim 3 become recycles big Bypass Ratio Turbofan Engine, which is characterized in that the blade of the fixed structure
There is slot, the first segment can movable vane between part and the first segment movable vane section and the second segment movable vane section
There is slot between segment and the second segment movable vane section.
6. as described in claim 1 become recycles big Bypass Ratio Turbofan Engine, which is characterized in that the movable vane section includes
First segment movable vane section, second segment movable vane section and third section movable vane section；
One end of the first segment movable vane section is connect by first axle with one end of the blade-section of the fixed structure,
The other end of the first segment movable vane section is connect by second hinge with one end of the second segment movable vane section, described
The other end of second segment movable vane section is connect by third hinge with one end of the third section movable vane section；
The other end of the third section movable vane section by adjust shaft be connected to the fixed structure blade-section it is another
One end.
7. as claimed in claim 6 become recycles big Bypass Ratio Turbofan Engine, which is characterized in that tool inside the turbine guide vane
There is high pressure cold.
8. as claimed in claim 6 become recycles big Bypass Ratio Turbofan Engine, which is characterized in that the blade of the fixed structure
There is slot, the first segment can movable vane between part and the first segment movable vane section and the third section movable vane section
There is slot, the second segment movable vane section and the third section can movable vanes between segment and the second segment movable vane section
There is slot between segment.
9. the change as described in claim 1-8 any one recycles big Bypass Ratio Turbofan Engine, which is characterized in that the turbine
The booster stage guide vane established angle of guide vane is string and axial angle, and the range of the angle is 0 ° -90 °.
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| CN201710924605.3A CN109595041B (en) | 2017-09-30 | 2017-09-30 | Variable-circulation large-bypass-ratio turbofan engine |
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| CN201710924605.3A CN109595041B (en) | 2017-09-30 | 2017-09-30 | Variable-circulation large-bypass-ratio turbofan engine |
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| CN109595041B CN109595041B (en) | 2021-10-19 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112664274A (en) * | 2019-10-15 | 2021-04-16 | 通用电气公司 | Forward ratio for a single unducted rotor engine |
| CN113062777A (en) * | 2021-06-03 | 2021-07-02 | 中国航发上海商用航空发动机制造有限责任公司 | Performance debugging method of booster stage and turbofan engine |
| CN113217226A (en) * | 2021-06-02 | 2021-08-06 | 中国航发湖南动力机械研究所 | Paddle-fan-turbine integrated engine |
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| CN113217226B (en) * | 2021-06-02 | 2022-08-02 | 中国航发湖南动力机械研究所 | Paddle-fan-turbine integrated engine |
| CN113062777A (en) * | 2021-06-03 | 2021-07-02 | 中国航发上海商用航空发动机制造有限责任公司 | Performance debugging method of booster stage and turbofan engine |
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| CN109595041B (en) | 2021-10-19 |
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