CN206397816U - A kind of fan structure for aero-engine - Google Patents
A kind of fan structure for aero-engine Download PDFInfo
- Publication number
- CN206397816U CN206397816U CN201621344186.3U CN201621344186U CN206397816U CN 206397816 U CN206397816 U CN 206397816U CN 201621344186 U CN201621344186 U CN 201621344186U CN 206397816 U CN206397816 U CN 206397816U
- Authority
- CN
- China
- Prior art keywords
- fan
- blade profile
- guide vane
- blade
- degree
- 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.)
- Active
Links
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model provides a kind of fan structure for aero-engine, and the fan structure includes：Fan outer casing, wheel hub, fan and fan guide vane, the fan is located between the wheel hub and the outer casing of the fan, it is fixedly connected with the wheel hub, the fan guide vane is located at the upstream of the fan, outside the wheel hub and the fan between casing with the wheel hub fixed-link, the blade tip of the fan guide vane, which has, just prewhirls, and blade root has counter prewhirl.
Description
Technical field
The utility model is related to aero-engine field, more particularly to a kind of fan structure for aero-engine.
Background technology
Turbogenerator is that a kind of parts using rotation pass through the engine type that kinetic energy is drawn in its fluid certainly, is
One kind of internal combustion engine, has a wide range of applications in aviation field.
The effect of fan structure and the effect of compressor are similar in turbogenerator, after air stream passing through fan, are divided into two-way：
It is intension air-flow all the way, air continues on through compressor compression, and in combustion chamber and fuel oil mixed combustion, combustion gas is swollen through turbine and jet pipe
Swollen, combustion gas is discharged with fast state from nozzle, produces thrust, and it is through low-pressure compressor, high-pressure compressor, burning to flow through distance
Room, high-pressure turbine, low-pressure turbine, combustion gas are discharged from jet pipe.
Another road is that air is directly discharged into air or with intension combustion gas together in jet pipe through by-pass air duct after outer culvert air-flow, fan
Discharge.Turbofan is combined with the advantage of turbojet and turbo-propeller engine.Fanjet conversion is most of
Combustion gas energy driving fan and compressor moment of torsion, remaining is converted into thrust.The gross thrust of fanjet is core hair
The thrust sum that motivation and fan are produced.
It can be seen that the thrust that fan is produced for turbogenerator is most important.
In order that after circulation passing through fan structure of bringing about the desired sensation, resulting in higher speed.In the prior art, by designing fan
The outlet flow angle of the fan guide vane of structure carries out design of prewhirling to the blade of fan guide vane.It is so-called to prewhirl, refer to lead fan
Leaf carries out structure design so that the inlet air flow velocity attitude of compressor first order movable vane piece (being usually fan) is not parallel to hair
Motivation axial direction.
The blade shape construction of current fan guide vane is as shown in figure 1, the general metal angle transition from root to tip mean camber line
Rule is identical, i.e., meanline curvature direction is identical from root to point.
When blade root, blade tip all design just to prewhirl, blade root movable vane amount of work can be reduced.When blade root, blade tip are all to be anti-pre-
During rotation design, blade tip shock strength, increase noise can be increased.
Utility model content
The purpose of this utility model is a kind of fan guide vane structure different from prior art of offer, can reduce tip
While shock strength, the problem of compressor inlet root reaction degree is too small is solved.
According to above-mentioned purpose, the utility model provides a kind of fan structure for aero-engine, the fan structure
Including：Fan outer casing, wheel hub, fan and fan guide vane, the fan are located between the wheel hub and the outer casing of the fan,
It is fixedly connected with the wheel hub, the fan guide vane is located at the upstream of the fan, the casing outside the wheel hub and the fan
Between with the wheel hub fixed-link, the blade tip of the fan guide vane, which has, just prewhirls, and blade root has counter prewhirl.
In one embodiment, the blade profile in the leaf of the fan guide vane is without prewhirling.
In one embodiment, blade profile of the fan guide vane on symmetrical two sections in its leaf middle section is identical
Blade profile line position there is the metal angle of negative each other.
In one embodiment, blade profile of the fan guide vane on symmetrical two sections in its leaf middle section has mutual
The mutual and equal bent angle of established angle for negative.
In one embodiment, the metal angle at the trailing edge of the blade profile of 90% leaf eminence of the fan guide vane is -15~-25
Metal angle at degree, the trailing edge of the blade profile of its 10% leaf eminence is 15~25 degree.
In one embodiment, the metal angle at 50% blade profile line of the blade profile of 90% leaf eminence of the fan guide vane is -5
Metal angle at~-15 degree, 50% blade profile line of the blade profile of its 10% leaf eminence is 5~15 degree.
In one embodiment, the established angle of the blade profile of 90% leaf eminence of the fan guide vane is 5~25 degree, its 10% leaf
The established angle of the blade profile of eminence is -5~-25 degree.
In one embodiment, the established angle of the blade profile of 70% leaf eminence of the fan guide vane is 0.5~15 degree, and it 30%
The established angle of the blade profile of leaf eminence is -0.5~-15 degree.
In one embodiment, the bent angle of the blade profile of 90% leaf eminence of the fan guide vane and 10% leaf eminence is 8~30
Degree.
In one embodiment, the bent angle of the blade profile of 70% leaf eminence of the fan guide vane and 30% leaf eminence be 0.5~
20 degree.
The utility model is swashed by just prewhirl design and the negative design of prewhirling of blade root of fan guide vane blade tip in reduction blade tip
Blade root movable vane amount of work is improved while intensity of wave, reduction noise.
Brief description of the drawings
Fig. 1 shows the blade shape construction schematic diagram of conventional fan stator；
Fig. 2 shows the schematic diagram of the fan layout structure of traditional aero-engine；
Fig. 3 shows the structural representation of the utility model fan guide vane；
Fig. 4 shows the schematic diagram of 5 section blade profiles from blade root to blade tip；
Fig. 5 shows the schematic diagram of the speed triangle with the two-way fan guide vane prewhirled.
For clarity, the brief description of reference given below：
20：Fan layout structure
201、301：Fan guide vane
202：Fan propeller
203：Wheel hub
204：The outer casing of fan
221：The page footing molded line of fan guide vane
222：The page footing molded line of fan propeller
302：The section blade profile of the blade tip of fan guide vane
303：The blade root section blade profile of fan guide vane
311：The mean camber line of blade tip section blade profile
312：The mean camber line of blade root section blade profile
401：Chord length
402：Established angle
403：Blade profile bent angle
501：Just prewhirling the speed triangle at place
502：Speed triangle without place of prewhirling
503：The speed triangle at negative place of prewhirling
Embodiment
Technical solutions of the utility model are different from prior art, and fan inlet stator is designed by mean camber line, are that fan is moved
Blade tip is provided and just prewhirled, to reduce shock strength；For fan rotor blade root provide it is counter prewhirl, to improve acting
Amount.
Wherein, just prewhirl：The circumferential component of the absolute velocity of fan blade inlet air flow and fan blade direction of rotation phase
Together；It is counter to prewhirl：The circumferential component of the absolute velocity of fan blade inlet air flow is opposite with fan blade direction of rotation to be referred to as instead
Prewhirl.
Existing fan structure refer to Fig. 2, and Fig. 2 shows the signal of the fan layout structure of traditional aero-engine
Figure.Traditional fan structure 20 includes the fan guide vane 201 and the fan propeller positioned at the downstream of fan guide vane 201 positioned at upstream
202。
Traditional fan layout structure 20 also includes the outer casing 204 of wheel hub 203, fan.Fan guide vane 201 and fan propeller
202 are located between wheel hub 203 and the outer casing 204 of fan.
The page footing molded line 221 of fan guide vane 201 is fixedly connected with wheel hub 203, the page footing molded line 222 of fan propeller 202 with
Wheel hub 203 is fixedly connected.Wherein, fan propeller 202 can move in a circle around with the identical axle of wheel hub 203.Air-flow is successively
Fan guide vane 201 and fan propeller 202 are flowed through, so as to realize the supercharging to balloon.
Key point of the present utility model is the improvement of the moulding to fan guide vane 201.Fig. 3 is refer to, Fig. 3 shows this
The structural representation of utility model fan guide vane.
The blade tip section blade profile 302 of fan guide vane 301, the root of blade section blade profile 303 of fan guide vane 301 is bent
It is in opposite direction, that is, produce different directions and prewhirl.
It can be seen that the bending direction of the mean camber line 311 of blade tip section blade profile 302 is towards inside paper, and blade root
The bending direction of the mean camber line 312 of portion section blade profile 303 is so achieved that fan guide vane blade tip and blade root towards paper outside
Different directions are prewhirled.
In one embodiment, the middle part of blade section blade profile 304 of fan guide vane 301 is without prewhirling.
In order to become apparent from showing double fan guide vane designs of prewhirling of the present utility model, Fig. 4 is refer to, Fig. 4 is provided respectively
The schematic diagram of 5 section blade profiles from blade root to blade tip.
Fan inlet stator blade profile metal angular dimensions is prewhirled with reference to 1 pair, table and 2 pairs, table fan inlet stator blade of prewhirling is made
Double designs of prewhirling of the present utility model are further illustrated, its middle period height refers to the blade height of fan guide vane by shape parameter.
1 pair, table is prewhirled fan inlet stator blade profile metal angular dimensions
2 pairs, table is prewhirled fan inlet stator blade shape construction parameter
Each parameter is provided to be defined as follows：
Chord length：In the blade profile of section, from blade profile costa to blade profile trailing edge line air line distance, the chord length in Fig. 4 refer to
401；
Established angle：The angle of section blade profile in the vertical direction and engine axis, refers to the established angle 402 in Fig. 4；
Blade profile bent angle：In the blade profile of section, the angle of costa tangent line and trailing edge line tangent line, the blade profile referred in Fig. 4 is curved
Angle 403；
Metal angle：The angle of mean camber line tangent line and engine axis.
In Fig. 4, A-A, B-B, C-C, D-D, E-E section are respectively the leaf of fan guide vane 10%, 30%, 50%, 70%, 90%
The cross section that piece is highly located.
Very intuitively it can be seen that coming, the yawing moment of section blade profile is from progressively being deflected to a deflecting facet to another side
, the deflection angle of the Section A-A blade profile of blade tip is in opposite direction with blade root E-E deflection angle, that is, realizes blade tip and blade root
Design of prewhirling with different directions.
In one embodiment, the blade tip of fan guide vane has and just prewhirled, and blade root has counter prewhirl.Prewhirling for fan guide vane be
Determined by the metal angle of section blade profile.
Reference table 1, wherein metal angle 1-7 are the metal angles corresponded on mean camber line at chord length projection percentage.
It can be seen that fan guide vane is all negative with the metal angle of the symmetrical top half section blade profiles of its leaf middle section C-C
Number, it is all design of just prewhirling to represent top half section blade profile.And fan guide vane is with its leaf middle section symmetrical the latter half of C-C
The metal angle of section blade profile is all positive number, and it is all negative design of prewhirling to represent the latter half section blade profile.
And without design of prewhirling on the C-C of leaf middle section.
In one embodiment, blade profile of the fan guide vane on symmetrical two sections of its leaf middle section C-C is identical
Blade profile line position there is the metal angle of negative each other.Identical blade profile position refers to, in respective chord length line on respective blade profile line
On the length of projection account for the equal position of total chord length length ratio.Now, fan guide vane is symmetrical.
In one embodiment, the metal angle at the trailing edge of the blade profile at the Section A-A of fan guide vane is -15~-25 degree, its
Metal angle at the trailing edge of blade profile at E-E sections is 15~25 degree.
In one embodiment, the metal angle at the trailing edge of the blade profile at the section B-B of fan guide vane is -5~-15 degree, D-D
Metal angle at the trailing edge of blade profile at section is 5~15 degree.
Table 2 is refer to, the chord length of the blade profile on each cross section is essentially identical, the length of chord length characterizes the whole of blade profile
Body size.The length of chord length is determined generally according to the size of engine existing structure in practice, to enable fan guide vane
It is installed into existing motor mechanisms.
In one embodiment, the section blade profile of top half is upwardly biased along engine axis, the section of the latter half
Blade profile is along engine axis biased downward.More preferably, fan guide vane is on symmetrical two sections of its leaf middle section C-C
On blade profile there is the mutual and equal bent angle of the established angle of negative each other.
Referring to table 2, in one embodiment, the established angle of Section A-A blade profile is 5~25 degree, the established angle of E-E sections blade profile
For -5~-25 degree, more preferably, the established angle of Section A-A blade profile is 7.11 degree, and the established angle of E-E sections blade profile is -10.13 degree.
In one embodiment, the established angle of section B-B blade profile is 0.5~15 degree, and the established angle of D-D sections blade profile is -0.5
~-15 degree, more preferably, the established angle of section B-B blade profile is 1.21 degree, and the established angle of D-D sections blade profile is -2.29 degree.
In one embodiment, fan guide vane is equal with the blade profile bent angle on the symmetrical sections of C-C of its leaf middle section, and blade profile is curved
Angle represents the degree of crook of section blade profile.
In one embodiment, the blade profile bent angle of Section A-A blade profile is 8~30 degree, and E-E sections blade profile bent angle is 8~30 degree,
More preferably, Section A-A blade profile bent angle is 14.34 degree, and E-E sections blade profile bent angle is 14.34 degree.
In one embodiment, the blade profile bent angle of section B-B blade profile is 0.5~20 degree, D-D sections blade profile bent angle for 0.5~
20 degree, more preferably, section B-B blade profile bent angle is 4.64 degree, and D-D sections blade profile bent angle is 4.64 degree.
In aerial engine fan level design, for the import relative velocity of fan rotor blade, have：
From formula (1), import relative velocity w1With flowing axial velocity c1a, peripheral speed u and to flow circumferential speed c1u
It is related.Flowing axial velocity c1aWith rotating speed it is certain in the case of, tangential velocity u and the high radial location linear correlation of leaf.Due to
Blade tip position tangential velocity is maximum, therefore higher to flow relative velocity.In order to reduce import relative velocity w1, generally using increase
To flow tangential velocity c1uMethod, i.e., design of just prewhirling.
For motion reaction degree ΩK, have：
From formula (2), as u and Δ wuOne timing (thus blade adds work(amount also certain), if increase c1u, then reaction degree
ΩKReduction, if reducing c1u, then ΩKIncrease.The too small trouble of fan leaf root reaction degree is commonly encountered when compressor is designed, so that it may
To flow tangential velocity c by reducing1u, i.e., it is designed to deal with using counter prewhirl.
Fig. 5 is refer to, Fig. 5 is shown zero in the schematic diagram of the speed triangle with the two-way fan guide vane prewhirled, Fig. 5
Design of prewhirling is represented by dashed line, using the indicated by the solid line of design of prewhirling.It can be seen that, it is designed with the speed at place of just prewhirling in blade tip
Spend the c of triangle 5011u＞ 0, the c for the speed triangle 502 at design of being prewhirled in Ye Zhongwu1u=0, it is designed with blade root negative pre-
The c of speed triangle 503 at rotation1u＜ 0.
According to formula (1), formula (2), fan blade tip, which is just being prewhirled, can reduce to flow relative velocity w1, so that it is strong to reduce tip shock wave
Degree, improves efficiency and reduces shock wave noise intensity.Counter prewhirl of blade root can improve blade root reaction degree, solve compressor inlet root anti-
The problem of dynamics is too small.
It is for so that any person skilled in the art all can make or use this public affairs to provide of this disclosure be previously described
Open.Various modifications of this disclosure all will be apparent for a person skilled in the art, and as defined herein general
Suitable principle can be applied to spirit or scope of other variants without departing from the disclosure.Thus, the disclosure is not intended to be limited
Due to example described herein and design, but it should be awarded and principle disclosed herein and novel features phase one
The widest scope of cause.
Claims (10)
1. a kind of fan structure for aero-engine, it is characterised in that the fan structure includes：The outer casing of fan, wheel
Hub, fan and fan guide vane, the fan are located between the wheel hub and the outer casing of the fan, fix and connect with the wheel hub
Connect, the fan guide vane is located at the upstream of the fan, it is solid with the wheel hub between casing outside the wheel hub and the fan
Fixed link, the blade tip of the fan guide vane, which has, just prewhirls, and blade root has counter prewhirl.
2. fan structure as claimed in claim 1, it is characterised in that blade profile in the leaf of the fan guide vane is without prewhirling.
3. fan structure as claimed in claim 2, it is characterised in that the fan guide vane is symmetrical on its leaf middle section
Blade profile on two sections has the metal angle of negative each other in identical blade profile line position.
4. fan structure as claimed in claim 2, it is characterised in that the fan guide vane is symmetrical on its leaf middle section
Blade profile on two sections has the mutual and equal bent angle of the established angle of negative each other.
5. fan structure as claimed in claim 3, it is characterised in that the tail of the blade profile of 90% leaf eminence of the fan guide vane
Metal angle at edge is that the metal angle at -15~-25 degree, the trailing edge of the blade profile of its 10% leaf eminence is 15~25 degree.
6. fan structure as claimed in claim 3, it is characterised in that the blade profile of 90% leaf eminence of the fan guide vane
Metal angle at 50% blade profile line is the metal angle at -5~-15 degree, 50% blade profile line of the blade profile of its 10% leaf eminence for 5~
15 degree.
7. fan structure as claimed in claim 4, it is characterised in that the peace of the blade profile of 90% leaf eminence of the fan guide vane
It is 5~25 degree to fill angle, and the established angle of the blade profile of its 10% leaf eminence is -5~-25 degree.
8. fan structure as claimed in claim 4, it is characterised in that the peace of the blade profile of 70% leaf eminence of the fan guide vane
It is 0.5~15 degree to fill angle, and the established angle of the blade profile of its 30% leaf eminence is -0.5~-15 degree.
9. fan structure as claimed in claim 4, it is characterised in that 90% leaf eminence of the fan guide vane and 10% leaf are high
The bent angle of the blade profile at place is 8~30 degree.
10. fan structure as claimed in claim 4, it is characterised in that 70% leaf eminence of the fan guide vane and 30% leaf
The bent angle of the blade profile of eminence is 0.5~20 degree.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621344186.3U CN206397816U (en) | 2016-12-08 | 2016-12-08 | A kind of fan structure for aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621344186.3U CN206397816U (en) | 2016-12-08 | 2016-12-08 | A kind of fan structure for aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206397816U true CN206397816U (en) | 2017-08-11 |
Family
ID=59509445
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621344186.3U Active CN206397816U (en) | 2016-12-08 | 2016-12-08 | A kind of fan structure for aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206397816U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107725477A (en) * | 2017-10-10 | 2018-02-23 | 北京航空航天大学 | A kind of leading edge design method for optimizing suction surface wave system and suppressing fan shock wave noise |
-
2016
- 2016-12-08 CN CN201621344186.3U patent/CN206397816U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107725477A (en) * | 2017-10-10 | 2018-02-23 | 北京航空航天大学 | A kind of leading edge design method for optimizing suction surface wave system and suppressing fan shock wave noise |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP0622526B1 (en) | Rotor assembly | |
| CN101915130B (en) | Three-dimensional nozzle ring vane of variable geometry turbocharger and design method thereof | |
| CN109139257B (en) | Inlet pre-swirl gas turbine engine | |
| US8186962B2 (en) | Fan rotating blade for turbofan engine | |
| CN107269583B (en) | A kind of super or transonic speed axial fan designs method based on high-order moment | |
| JP2753217B2 (en) | Wings for gas turbine engines | |
| US8967967B2 (en) | Propfan engine | |
| CN109139259A (en) | Entrance preswirl gas-turbine unit | |
| CN102852857B (en) | High-load super transonic axial gas compressor aerodynamic design method | |
| CN103906895B (en) | Oblique-flow turbine | |
| CN104854325B (en) | Radial turbine movable vane piece | |
| CN108729952A (en) | More turbine vane frames | |
| JPH10502150A (en) | Flow orientation assembly for the compression region of rotating machinery | |
| CN108644152A (en) | Diffuser twisted blade and design method, diffuser and centrifugation/inclined flow air compressor | |
| US20220106907A1 (en) | Turbine engine with struts | |
| CN111435399A (en) | Molding method of fan assembly | |
| CN106939902B (en) | Energy-saving straight-wall front and rear disk variable-curvature curve element ternary impeller and centrifugal fan adopting same | |
| CN109844263B (en) | Turbine wheel, turbine and turbocharger | |
| CN206397816U (en) | A kind of fan structure for aero-engine | |
| CN105257590A (en) | Semi-serial blade and design method thereof | |
| CN106089799A (en) | Compression rotor based on Scramjet Inlet compress technique | |
| CN206738198U (en) | A kind of axial flow blower | |
| JP2013015035A (en) | Radial turbine and turbocharger including the same | |
| CN111043081A (en) | Axial fan and application thereof in remote mist sprayer | |
| CN104895618A (en) | Super-high load low pressure turbine blade, high load low pressure turbine and aviation gas turbine engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |