CN107524522A - Receive expansion formula fanjet flow splitter - Google Patents
Receive expansion formula fanjet flow splitter Download PDFInfo
- Publication number
- CN107524522A CN107524522A CN201610444478.2A CN201610444478A CN107524522A CN 107524522 A CN107524522 A CN 107524522A CN 201610444478 A CN201610444478 A CN 201610444478A CN 107524522 A CN107524522 A CN 107524522A
- Authority
- CN
- China
- Prior art keywords
- flow splitter
- flow
- fanjet
- leading portion
- back segment
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides one kind to receive expansion formula fanjet flow splitter, it includes flow splitter leading portion and flow splitter back segment, the flow splitter leading portion is connected with the flow splitter back segment by connection member, and the flow splitter leading portion is rotated by the connection member relative to the flow splitter back segment, the flow splitter leading portion is made of marmem.Present invention receipts expansion formula fanjet flow splitter need not increase other flow-guiding structures beyond flow splitter, and the receipts of flow splitter expand the uniformity for adjusting and not influenceing air current flow.When receiving expansion regulation, the deterioration of aeroperformance will not be brought.Simultaneously, it can also meet that flow splitter leading portion accordingly floats according to the change of engine behavior, it is adapted so as to realize that the receipts of flow splitter front end expand angle with airflow direction, improve the flow regime for entering inside and outside culvert air-flow, and then realize that provided with internal duct and external duct preferably matches work, lifts the performance level of engine.
Description
Technical field
It is more particularly to a kind of to receive expansion formula fanjet point the present invention relates to fanjet turbomachine field
Flow ring.
Background technology
In fanjet turbine field, double duct fanjets are a kind of important shapes of aero-engine
Formula, developed by turbojet engine.However, compared with turbojet engine, it is mainly characterized by chopped-off head pressure
The area of contracting machine is much larger, is simultaneously used as air propeller (fan).What its core air passed through
Part turns into main duct, and the core engine Outboard Sections that only fan air passes through turn into by-pass air duct.
Flow splitter is to realize that air respectively enters the distribution structure of main duct and by-pass air duct, while is also to influence hair
Motivation is under different working condition, into the important component of inside and outside culvert air mass flow distribution.In the whole of flow splitter
In body structure, flowing angle and direction when the structure type of particularly its front end affects distribution of air flow.
Therefore, understood based on above description, flow splitter is to influence the bypass ratio of double duct fanjets and interior
The outer important component for containing assignment of traffic, its structure type directly affects the work of double duct fanjets
Make situation and performance level.
Fig. 1 is the attachment structure schematic diagram of conventional shunt ring.As shown in Figure 1 to Figure 3, flow splitter 10 includes
Flow splitter leading portion 11 and flow splitter back segment 12, pass through one between flow splitter leading portion 11 and flow splitter back segment 12
To bindiny mechanism 13,14.
In the prior art, when double duct fanjets are operated in different working conditions, import is passed through
Fan, which enters its main duct and the flow of by-pass air duct, can also convert.This change directly affects air-flow
Flowing angle and direction, the final working condition and performance level for influenceing engine.
The content of the invention
The technical problem to be solved in the present invention be in order to overcome in the prior art double duct fanjets working
Shi Liuliang is converted, easily the defects of the working condition and performance level of influence engine, there is provided Yi Zhongshou
Expansion formula fanjet flow splitter.
The present invention is that solve above-mentioned technical problem by following technical proposals：One kind is received expansion formula turbofan and started
Machine flow splitter, its feature are that the receipts expansion formula fanjet flow splitter includes flow splitter leading portion and shunting
Ring back segment, the flow splitter leading portion are connected with the flow splitter back segment by connection member, and cause described point
Stream ring leading portion is rotated by the connection member relative to the flow splitter back segment, and the flow splitter leading portion uses shape
Shape memory alloys are made.
It is preferred that when flow splitter leading portion keep level mutual with the flow splitter back segment, the connection
The vertical line of part forms one first angle with the vertical line midpoint and the flow splitter leading edge point line.
It is preferred that when the flow splitter leading portion and the flow splitter back segment are in contraction state, the connection
The vertical line of part forms one second angle with the vertical line midpoint and the flow splitter leading edge point line.
It is preferred that first angle is more than second angle, and second angle and the described first folder
Difference between angle is less than or equal to 10 °.
It is preferred that when the flow splitter leading portion and the flow splitter back segment are in expansion state, the connection
The vertical line of part forms one the 3rd angle with the vertical line midpoint and the flow splitter leading edge point line.
It is preferred that the 3rd angle is more than first angle, and the 3rd angle and the described first folder
Difference between angle is less than or equal to 10 °.
It is preferred that also connected between the flow splitter leading portion and the flow splitter back segment by a rotating mechanism,
By-pass air duct side and main duct side between the flow splitter leading portion and the flow splitter back segment are equipped with connection
Plane, for closing the space around the rotating mechanism.
It is preferred that nearly by-pass air duct side and nearly main duct side are equipped with conduit, the company on the flow splitter back segment
Connect and connecting rod is provided with plane, the end of the connecting rod is provided with connected ball, and the connection plane drives institute
State connecting rod and the connected ball is slidably installed in the conduit.
It is preferred that the form that is flexible coupling of oscillating bearing is used between the connecting rod and the connected ball.
The positive effect of the present invention is：
Present invention receipts expansion formula fanjet flow splitter need not increase other flow-guiding structures beyond flow splitter, and
The receipts of flow splitter, which expand regulation, does not influence the uniformity of air current flow.When receiving expansion regulation, pneumatic property will not be brought
The deterioration of energy.Meanwhile it can also meet that flow splitter leading portion is corresponding according to the change of engine behavior
Float, be adapted so as to realize that the receipts of flow splitter front end expand angle with airflow direction, improvement enters inside and outside culvert
The flow regime of air-flow, and then realize that provided with internal duct and external duct preferably matches work, lifts the performance level of engine.
Brief description of the drawings
The present invention the above and other feature, property and advantage will be by with reference to the accompanying drawings and examples
Description and become apparent, identical reference represents identical feature all the time in the accompanying drawings, wherein：
Fig. 1 is the attachment structure schematic diagram of conventional shunt ring.
Fig. 2 is the attachment structure schematic diagram one that the present invention receives expansion formula fanjet flow splitter.
Fig. 3 is the attachment structure schematic diagram two that the present invention receives expansion formula fanjet flow splitter.
Fig. 4 is the close-up schematic view for the attachment structure that the present invention receives expansion formula fanjet flow splitter.
Fig. 5 is that the present invention receives the schematic diagram that expansion formula fanjet flow splitter is in horizontality.
Fig. 6 is that the present invention receives the schematic diagram that expansion formula fanjet flow splitter is in contraction state.
Fig. 7 is that the present invention receives the schematic diagram that expansion formula fanjet flow splitter is in expansion state.
Fig. 8 is position view of the flow splitter in fanjet.
Fig. 9 is the schematic diagram of flow splitter and booster stage leaf position.
Embodiment
For the above objects, features and advantages of the present invention can be become apparent, below in conjunction with accompanying drawing to this hair
Bright embodiment elaborates.
Embodiments of the invention are described with detailed reference to accompanying drawing now.Now with detailed reference to the preferred of the present invention
Embodiment, its example are shown in the drawings.In the case of any possible, phase will be used in all of the figs
With mark represent same or analogous part.In addition, although the term used in the present invention is from public affairs
Know what is selected in public term, but some terms mentioned in description of the invention are probably applicant
Carry out selection by his or her judgement, its detailed meanings illustrates in the relevant portion of description herein.In addition,
It is required that not only by used actual terms, and the meaning for being also to be contained by each term is managed
The solution present invention.
Fig. 2 is the attachment structure schematic diagram one that the present invention receives expansion formula fanjet flow splitter.Fig. 3 is this hair
The bright attachment structure schematic diagram two for receiving expansion formula fanjet flow splitter.Fig. 4 receives expansion formula turbofan hair for the present invention
The close-up schematic view of the attachment structure of motivation flow splitter.Fig. 5 receives expansion formula fanjet point for the present invention
Stream ring is in the schematic diagram of horizontality.Fig. 6 receives expansion formula fanjet flow splitter and be in for the present invention to be shunk
The schematic diagram of state.Fig. 7 is that the present invention receives the schematic diagram that expansion formula fanjet flow splitter is in expansion state.
As shown in Figures 2 to 7, the invention discloses one kind to receive expansion formula fanjet flow splitter 100, its
Including flow splitter leading portion 110 and flow splitter back segment 120, by flow splitter leading portion 110 and flow splitter back segment 120
Connected by connection member 150, and cause flow splitter leading portion 110 by connection member 150 with respect to flow splitter
Back segment 120 rotates.Especially, flow splitter leading portion 110 herein is made of marmem, so
It can realize that the receipts of flow splitter expand formula regulation, and with three kinds of horizontality, contraction state and expansion state works
Make form.
Herein, the marmem of use is one kind of intellectual material, utilizes the phase of the crystal structure of material
Co-conversion come make it have change in shape and memory function.When marmem experiences extraneous stress etc.
After condition change, stress-induced martensite (SIM) phase transformation occurs for crystal inside, and macro manifestations are alloy
Reversible elasticity deformation.Different stress conditions can cause alloy that different alterations of form occurs；And when stress disappears
After mistake, alloy returns to original-shape.
Preferably, a rotating mechanism 130 is also passed through between flow splitter leading portion 110 and flow splitter back segment 120
Connection, while by-pass air duct side between flow splitter leading portion 110 and flow splitter back segment 120 and main duct side are equal
Provided with connection plane 140, it is mainly used in closing the space around the rotating mechanism.Main duct side uses phase
Same structure design, realizes identical function.
It is further preferred that nearly by-pass air duct side and nearly main duct side are equipped with conduit on flow splitter back segment 120
121, connecting rod 141 is correspondingly provided with connection plane 140, the end of connecting rod 141 is provided with connection
Ball 142, so that connection plane 140 can drive connecting rod 141 and connected ball 142 to be slidably installed in conduit
In 121.Can be preferably by the form that is flexible coupling of oscillating bearing between connecting rod 141 and connected ball 142.
Main duct side uses identical structure design, realizes identical function.
As shown in figure 5, when flow splitter leading portion 110 and flow splitter 120 mutual keep level of back segment, connection
The vertical line of part 150 forms one first angle α with the vertical line midpoint and the leading edge point line of flow splitter 100.
As shown in fig. 6, when flow splitter leading portion 110 and flow splitter back segment 120 are in contraction state, connection
The vertical line of part 150 forms one second angle β with the vertical line midpoint and the leading edge point line of flow splitter 100.
Specifically, it is right when fan outlet air-flow is changed into the direction of arrow in Fig. 6 from the direction of arrow in Fig. 5
The gas flow that main duct should be entered is reduced, and flow splitter leading portion 110 experiences the change of incoming-flow pressure condition, should
Power strain induced martensite phase transformation brings it about reversible elasticity deformation, and rotating mechanism 130 turns around the axle perpendicular to section
The dynamic shrinkage variable cross-section regulation for realizing flow splitter leading portion 110 itself.So main duct and by-pass air duct inlet face
Long-pending ratio reduces, and now the first angle α is decreased to second angle β.First angle α is more than the second angle
β, and the difference between the second angle β and the first angle α is less than or equal to 10 °, i.e. alpha-beta≤10 °.
As shown in fig. 7, when flow splitter leading portion 110 and flow splitter back segment 120 are in expansion state, connection
The vertical line of part 150 forms one the 3rd angle theta with the vertical line midpoint and the leading edge point line of flow splitter 100.
Specifically, it is corresponding to enter when fan outlet air-flow is changed into Fig. 7 directions from the direction of arrow in Fig. 5
The gas flow increase of main duct, flow splitter leading portion 110 experiences the change of incoming-flow pressure condition, stress-induced
Martensitic traoformation brings it about the reversible elasticity deformation with opposite direction in Fig. 6, rotating mechanism 130 around perpendicular to
The axle of section rotates the dilatancy variable cross-section regulation for realizing flow splitter leading portion 110 itself, main duct and by-pass air duct
Inlet -duct area ratio increase.Now, the first angle α increases to the 3rd angle theta, and the after increase the 3rd
Difference between angle theta and the first angle α is less than or equal to 10 °, i.e. θ-α≤10 °.
During above-mentioned Fig. 5 to the regulation described in Fig. 7, the connection plane 140 of flow splitter 100 has envelope
The effect of the surrounding space of rotating mechanism 130 is closed, so can effectively ensure the company on the surface of rotating mechanism 130
Continuous uninterrupted, avoiding air turbulence, mobile performance deterioration etc. influences.The main duct side of flow splitter 100
Connection and regulation process it is identical with the by-pass air duct side of flow splitter 100, and then realize flow splitter 100 from
Adapt to receive and expand regulation.After incoming-flow pressure condition is recovered to initial condition, reverse bullet occurs inside alloy material
Property deformation, flow splitter leading portion 110 can return to initial configuration formula as shown in Figure 5.
Fig. 8 is position view of the flow splitter in fanjet.Fig. 9 is flow splitter and supercharging grade blade
The schematic diagram of position.
As shown in Figure 8 and Figure 9, present invention receipts expansion formula fanjet flow splitter is mainly used in fanjet.
Fanjet includes fanjet fan 200, fan and contains casing 300, fan and booster stage wheel hub outside
400th, flow splitter 100, by-pass air duct guide vane 500 and main duct supercharging grade blade 600.Flow splitter 100
Installed in by-pass air duct guide vane 500 and main duct supercharging grade blade 600 between, and flow splitter 100 with it is interior
The leading edge of duct supercharging grade blade 600 forms intersection point 160.The horizontal length of flow splitter leading portion 110 is general not
More than 1/3rd of its leading edge point and the horizontal range of intersection point 160.
According to said structure, the present invention uses New Shape Memory Alloys, it is possible to achieve flow splitter front-end architecture
Receipts expand formula regulation.Its structure does not influence the uniformity of air current flow, will not be brought when receiving and expanding regulation pneumatic
The deterioration of performance.
In summary, the present invention receive that expansion formula fanjet flow splitter need not increase beyond flow splitter other lead
Flow structure, and the receipts of flow splitter expand the uniformity for adjusting and not influenceing air current flow., will not when receiving expansion regulation
Bring the deterioration of aeroperformance.Meanwhile it can also meet flow splitter leading portion according to engine behavior
Change and accordingly float, so as to realize the receipts of flow splitter front end expand angle be adapted with airflow direction, improve into
Enter the flow regime to inside and outside culvert air-flow, and then realize that provided with internal duct and external duct preferably matches work, lifting engine
Performance level.
Although the foregoing describing the embodiment of the present invention, it will be appreciated by those of skill in the art that
These are merely illustrative of, and protection scope of the present invention is defined by the appended claims.This area
Technical staff can make more on the premise of without departing substantially from the principle and essence of the present invention to these embodiments
Kind change or modification, but these changes and modification each fall within protection scope of the present invention.
Claims (9)
1. one kind receives expansion formula fanjet flow splitter, it is characterised in that the receipts expansion formula fanjet point
Stream ring includes flow splitter leading portion and flow splitter back segment, and the flow splitter leading portion and the flow splitter back segment pass through company
Relay part is connected, and the flow splitter leading portion is turned by the relatively described flow splitter back segment of the connection member
Dynamic, the flow splitter leading portion is made of marmem.
2. expansion formula fanjet flow splitter is received as claimed in claim 1, it is characterised in that when described point
When flowing the mutual keep level of ring leading portion and the flow splitter back segment, the vertical line of the connection member and the vertical line
Midpoint and the flow splitter leading edge point line form one first angle.
3. expansion formula fanjet flow splitter is received as claimed in claim 2, it is characterised in that when described point
When stream ring leading portion is in contraction state with the flow splitter back segment, the vertical line of the connection member and the vertical line
Midpoint and the flow splitter leading edge point line form one second angle.
4. expansion formula fanjet flow splitter is received as claimed in claim 3, it is characterised in that described first
Angle is more than second angle, and the difference between second angle and first angle is less than or equal to
10°。
5. expansion formula fanjet flow splitter is received as claimed in claim 2, it is characterised in that when the shunting
When ring leading portion and the flow splitter back segment be in expansion state, the vertical line of the connection member and the vertical line midpoint and
The flow splitter leading edge point line forms one the 3rd angle.
6. expansion formula fanjet flow splitter is received as claimed in claim 5, it is characterised in that described the
Three angles are more than first angle, and the difference between the 3rd angle and first angle is less than etc.
In 10 °.
7. expansion formula fanjet flow splitter is received as claimed in claim 1, it is characterised in that described point
Flow and also connected between ring leading portion and the flow splitter back segment by a rotating mechanism, in the flow splitter leading portion and
By-pass air duct side and main duct side between the flow splitter back segment are equipped with connection plane, for closing described turn
Space around motivation structure.
8. expansion formula fanjet flow splitter is received as claimed in claim 7, it is characterised in that described point
Nearly by-pass air duct side and nearly main duct side are equipped with conduit on stream ring back segment, and connection is provided with the connection plane
Bar, the end of the connecting rod are provided with connected ball, and the connection plane drives the connecting rod and the connection
Ball is slidably installed in the conduit.
9. expansion formula fanjet flow splitter is received as claimed in claim 8, it is characterised in that the company
The form that is flexible coupling of oscillating bearing is used between extension bar and the connected ball.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610444478.2A CN107524522B (en) | 2016-06-20 | 2016-06-20 | Collecting and expanding type turbofan engine flow distribution ring |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610444478.2A CN107524522B (en) | 2016-06-20 | 2016-06-20 | Collecting and expanding type turbofan engine flow distribution ring |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107524522A true CN107524522A (en) | 2017-12-29 |
| CN107524522B CN107524522B (en) | 2021-06-11 |
Family
ID=60733896
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610444478.2A Active CN107524522B (en) | 2016-06-20 | 2016-06-20 | Collecting and expanding type turbofan engine flow distribution ring |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107524522B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112343718A (en) * | 2019-08-08 | 2021-02-09 | 通用电气公司 | Shape memory alloy reinforced sleeve |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6260567B1 (en) * | 1997-07-22 | 2001-07-17 | The Boeing Company | Mission adaptive inlet |
| US20080236133A1 (en) * | 2007-03-30 | 2008-10-02 | Snecma | Turbomachine front portion comprising a deflector system for deflecting foreign bodies, such as hailstones |
| CN104295405A (en) * | 2014-08-15 | 2015-01-21 | 中国航空工业集团公司沈阳发动机设计研究所 | Method of lowering gas flow resistance to outer duct of aviation turbofan engine with small bypass ratio |
| CN205277599U (en) * | 2016-01-13 | 2016-06-01 | 中国航空动力机械研究所 | Flow splitter and aeroengine |
-
2016
- 2016-06-20 CN CN201610444478.2A patent/CN107524522B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6260567B1 (en) * | 1997-07-22 | 2001-07-17 | The Boeing Company | Mission adaptive inlet |
| US20080236133A1 (en) * | 2007-03-30 | 2008-10-02 | Snecma | Turbomachine front portion comprising a deflector system for deflecting foreign bodies, such as hailstones |
| CN104295405A (en) * | 2014-08-15 | 2015-01-21 | 中国航空工业集团公司沈阳发动机设计研究所 | Method of lowering gas flow resistance to outer duct of aviation turbofan engine with small bypass ratio |
| CN205277599U (en) * | 2016-01-13 | 2016-06-01 | 中国航空动力机械研究所 | Flow splitter and aeroengine |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112343718A (en) * | 2019-08-08 | 2021-02-09 | 通用电气公司 | Shape memory alloy reinforced sleeve |
| US11591932B2 (en) | 2019-08-08 | 2023-02-28 | General Electric Company | Shape memory alloy reinforced casing |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107524522B (en) | 2021-06-11 |
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