CN108561187A - Cage is laid out aero-engine impeller - Google Patents
Cage is laid out aero-engine impeller Download PDFInfo
- Publication number
- CN108561187A CN108561187A CN201810252036.7A CN201810252036A CN108561187A CN 108561187 A CN108561187 A CN 108561187A CN 201810252036 A CN201810252036 A CN 201810252036A CN 108561187 A CN108561187 A CN 108561187A
- Authority
- CN
- China
- Prior art keywords
- aero
- engine
- primary blades
- wheel body
- impeller
- 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.)
- Pending
Links
Classifications
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
Abstract
Cage of the present invention is laid out aero-engine impeller, is related to aero-engine field, more particularly to a kind of aero-engine impeller comprising：Primary blades (1), wheel body (2) account for gas coning (3), bottom end blade (4)., in the case where not increasing impeller circular cross-section, the contact area of length and air by increasing primary blades (1) increases air dielectric decrement for it；Utilize circular motion, the highest characteristic of peripheral speed that primary blades is allowed to be in highest working efficiency simultaneously；And reduce wheel in vivo, accommodate the spatial volume of air dielectric accounts for gas coning (3) design, and the atmospheric pressure conduction in its impeller is allowed to have more efficiency.Allow engine using this impeller, have that more high thrust, internal core temperature is lower, more fuel-efficient, flight promotion limit for height, etc. characteristics.
Description
Technical field
The present invention relates to aero-engine field, more particularly to a kind of aero-engine impeller.
Background technology
In aero-engine field, turbine, turbofan, turboshaft engine air compression, rely primarily on aeroplane engine
Machine impeller is completed.
Every difference of its impeller size, appearance design, material, technique etc., keeps the power of its aero-engine defeated
Go out, thrust, DIE Temperature, service ceiling, oil consumption rate etc. performance it is also different.
Invention content
The invention mainly solves the technical problem of providing a kind of aero-engine impellers, can solve the problems, such as follows：
Further increase the working efficiency of the blade of engine impeller.
The radial flabellum in traditional center of circle is avoided, each portion of blade is different to circle center distance when because rotating, caused point of speed
Uneven, the height pressure difference of formation is spent, and is caused under the limit speed of Impeller Design in the area of low pressure close to the center of circle
There is the phenomenon that leakage pressure, the influence to engine performance loss in the spilling of high pressure.
The compression ratio for improving aero-engine inlet air allows engine to obtain the thrust of bigger.
Under the premise of the circular cross-section for not increasing engine impeller, engine performance is improved, aviation aircraft is more advantageous to
Flow profile designs.
The influence for enabling impeller that rarefaction of air, High aititude to be overcome to bring the power output and thrust of engine increases
The ceiling of operation height.
High compression ratio air is inputted using to engine, makes the burning fuel of engine that gas hot expanding type temperature requirements be made to subtract
It is small, it is more fuel-efficient.
The purpose of the present invention is inventing a kind of performance that existing aero-engine can be substantially improved, especially more than solution
Described the problem of mentioning, and enrich existing aero-engine category, design scheme a kind of novel aero-engine impeller.
The present invention is to solve above-mentioned technical problem by the following technical programs：
The present invention provides a kind of aero-engine impeller and design methods, which is characterized in that including：Primary blades (1), wheel
Body (2) accounts for gas coning (3), bottom end blade (4).
Primary blades (1) both ends are connected with wheel body (2), and the side at primary blades (1) edge is in the impeller center of circle and makees to justify
On the outside of Zhou Yundong.It in the case of within the unit interval with rotating speed, moves in a circle, the highest characteristic of peripheral speed makes leaf
When piece moves in a circle around wheel body, in the highest region of speed can be obtained, to improve the work of engine impeller blade
Make efficiency.
Because the side for using primary blades (1) edge be in the impeller center of circle circle on the outside of layout, blade so
The radial flabellum in traditional center of circle is avoided, to circle center distance difference, caused component velocity is uneven in blade each portion when because of rotation,
The height pressure difference of formation, and in the area of low pressure close to the center of circle, under the limit speed of Impeller Design, cause overflowing for high pressure
Go out or exist the phenomenon that leakage pressure, the influence to engine performance loss.
The present invention, primary blades (1) length of impeller, there is no limit relationships with the diameter of impeller wheel body, only with impeller wheel body
Limited length relationship.
So can be in the case where not increasing impeller circular cross-section, by the length and air that increase primary blades (1)
Contact area improves the compression ratio of air by more air dielectrics within the unit interval, and engine is allowed to obtain pushing away for bigger
Power.
Equally in the contact area of the length and air that increase primary blades (1), the circular cross-section of impeller will not be increased, more
Be conducive to the design of aviation aircraft flow profile.
In the case of rarefaction of air, the reason of forcing engine to be not normally functioning is cannot to be drawn into enough skies
Gas, burning fuel cannot be such that the air drawn is expanded into need pressure, and thrust can be generated or maintain fortune by having broken engine
Action edge recycles.So engine in the case of rarefaction of air, be supplied to threshold engine run rotating speed be it is certain,
So in the case where not increasing rotating speed, by increasing the contact area of impeller primary blades (1) and air, reinforce engine in sky
Efficiency is drawn in the case of gas is thin, obtains enough air.To make the engine using the impeller, rarefaction of air can be overcome
The influence that power output and thrust to engine are brought increases the ceiling of operation height.
The operational efficiency height brought using impeller in summary, the compression sky for obtaining a large amount of air, exporting high pressure ratio
Gas, it is only necessary to less temperature, you can the expansion pressure for forming demand is obtained, motor power is formed, it is more fuel-efficient.
It is bigger for the inner space of impeller, to reach specified normal pressure (pressure for being more than zero), need gas volume
It is more, account for gas coning (3), be by wheel body (2) one end, or by primary blades (1) bottom end be starting, until the wheel body other side or bottom
It is cut-off to hold the root of blade (4), does the pyramidal structure body of straight line plane or camber line curved surface.Effective reduce accommodates gas in impeller
The conduction efficiency of pressure is improved in the space of body.
Gas coning (3) is accounted for, the advantageous effect that impeller primary blades (1) are brought effectively is strengthened.
Bottom end blade (4), one of effect be the other end with the fixed primary blades (1) of wheel body (2).Effect is to utilize bottom end
The gas of the difference in areas that blade (4) primary blades (1) are contacted with attaching space, formation forms impeller internal by leading by difference in flow
Blade (1) wheel body (2), accounts for gas coning (3), the gas pressure intensity raising in the wheel chamber that bottom end blade (4) is constituted.
Bottom end blade (4) has both the function of the compressed gas into rear class compression impeller delivery wheel.
Bottom end blade (4), one of effect be the other end with the fixed primary blades (1) of wheel body (2).Play primary blades (1)
Firm effect.
The impeller is a kind of novel aero-engine impeller that can enrich Aeroengine Design scheme.
The positive effect of the present invention is that：
A kind of impeller that aero-engine performance can be substantially improved has been invented, has allowed engine using this impeller, has been had
More high thrust, internal core temperature are lower, more fuel-efficient, flight promotion limit for height, etc. characteristics.There is abundant existing aeroplane engine simultaneously
A kind of novel aero-engine impeller of machine category, design scheme.
Description of the drawings
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 what is become is easy to understand, identical reference numeral always shows identical feature in the accompanying drawings, wherein：
Fig. 1 is the main body that cage of the present invention is laid out aero-engine impeller, squints schematic diagram.
Fig. 2 is main center's section that cage of the present invention is laid out aero-engine impeller, squints schematic diagram.
Specific implementation mode
For the above objects, features and advantages of the present invention can be clearer and more comprehensible, below in conjunction with attached drawing to the tool of the present invention
Body embodiment elaborates.
Many details are elaborated in the following description to facilitate a thorough understanding of the present invention, still the present invention can be with
Using it is other different from this description by the way of implement, therefore the present invention do not limited by following public specific embodiment.
Fig. 1 is the strabismus main body that cage of the present invention is laid out aero-engine impeller, distribution schematic diagram.Fig. 2 is cage of the present invention
Formula is laid out the oblique view section of aero-engine impeller, distribution schematic diagram.
As depicted in figs. 1 and 2, a kind of aero-engine impeller, main portion are disclosed in one embodiment of the present of invention
Divide and includes：Primary blades (1), wheel body (2) account for gas coning (3), bottom end blade (4).Wherein primary blades (1) both ends with wheel body (2) phase
Connection, and the side of blade edge circle outside in the impeller center of circle.Wheel body (2) is two-part structure, a part
With primary blades (1), account for gas coning (3), the root of bottom end blade (4) is connect, another part is for primary blades (1) and bottom end blade
(4) connection.Account for gas coning (3), be by wheel body (2) one end, or by primary blades (1) bottom end be starting, until the wheel body other side or bottom
It is cut-off to hold the root of blade (4), does the pyramidal structure body of straight line plane or camber line curved surface.Bottom end blade (4), both ends are taken turns respectively
Body (2) two parts are connected.
There is no limit length is more more growing the air under same rotating speed, it then follows demand principle is answered for the length of primary blades (1)
With.
Wheel body (2) is connected with shaft rotation, minimum diameter, be the interior diameter of impeller, the maximum gauge of wheel body (2) is
The overall diameter of impeller is same as or slightly smaller than with the largest outer diameter of engine design requirement.
To mitigate weight, accounts for gas coning (2) and can be designed as hollow structure.
The length of blade of bottom end blade (4) is that the overall diameter of impeller subtracts interior diameter, subtracts the thickness that wheel body is fixedly connected
Degree.
One of the effect of bottom end blade (4) is the other end with the fixed primary blades (1) of wheel body (2).It is steady to play primary blades (1)
Solid effect.
On practicing, to ensure the robustness implemented and Rapid Implementation, this impeller is replaced or is made an addition to compression section
Before original mover blade, become the first order of turbine, turbofan, turboshaft engine inlet air compressor.
The cage of the above present invention is laid out aero-engine impeller, and primary blades (1) described in impeller, account for gas at wheel body (2)
Bore (3), bottom end blade (4) feature, each section can independently become part splice or install, can also by any two,
And more than two parts are combined into an entirety, can also be two and more than two parts and zero by a partial resolution
Part.
Same arbitrary part carries out local change, nor affects in the technical characteristic for possessing technical solution of the present invention
Using effect.
The above embodiment is merely illustrative of the invention's technical idea, and protection scope of the present invention cannot be limited with this, this
The protection domain of invention is that the appended claims limit.It is every according to technological thought proposed by the present invention, in technical solution
On the basis of any change for being done, each fall within protection scope of the present invention.
Claims (10)
1. a kind of aero-engine impeller, which is characterized in that including：Primary blades (1), account for gas coning (3), bottom end blade at wheel body (2)
(4)。
2. aero-engine impeller according to claim 1, it is characterised in that：Primary blades (1) both ends with wheel body (2) phase
Connection, and the side of blade edge circle outside in the impeller center of circle.
3. aero-engine impeller according to claim 1, it is characterised in that：Wheel body (2), be two-part structure, one
Point with primary blades (1), account for gas coning (3), the root of bottom end blade (4) connect, another part is used for primary blades (1) and bottom end blade
(4) connection.
4. aero-engine impeller according to claim 1, it is characterised in that：Account for gas coning (3), be by wheel body (2) one end,
Or by primary blades (1) bottom end to originate, until the wheel body other side or the root of bottom end blade (4) are cut-off, straight line plane or arc are done
The pyramidal structure body of line curved surface.
5. aero-engine impeller according to claim 1, it is characterised in that：Wheel body is distinguished at bottom end blade (4), both ends
(2) two parts are connected.
6. aero-engine impeller according to claim 1, it is characterised in that：Primary blades (1) are not increasing wheel body (2)
In the case of circular cross section diameter, the contact area with air can be increased by the design of extension blade.
7. aero-engine impeller according to claim 1, it is characterised in that：Bottom end blade (4), one of effect be with
The other end of the fixed primary blades (1) of wheel body (2).
8. aero-engine impeller according to claim 1, it is characterised in that：Account for gas coning (3), effect be reduce impeller
The interior space for accommodating gas, improves the transduction efficiency of pressure.
9. aero-engine impeller according to claim 1, which is characterized in that the primary blades (1), account for wheel body (2)
The feature of gas coning (3), bottom end blade (4), each section can independently become part and splice or install, can also be by arbitrary two
A and more than two parts are combined into an entirety, can also be by a partial resolution two and more than two part and
Part.
10. aero-engine impeller according to claim 1, which is characterized in that the primary blades (1), wheel body (2),
Gas coning (3), bottom end blade (4) are accounted for, same arbitrary part carries out part in the technical characteristic for possessing technical solution of the present invention
Change, nor affect on using effect.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810252036.7A CN108561187A (en) | 2018-03-26 | 2018-03-26 | Cage is laid out aero-engine impeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810252036.7A CN108561187A (en) | 2018-03-26 | 2018-03-26 | Cage is laid out aero-engine impeller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108561187A true CN108561187A (en) | 2018-09-21 |
Family
ID=63533270
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810252036.7A Pending CN108561187A (en) | 2018-03-26 | 2018-03-26 | Cage is laid out aero-engine impeller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108561187A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109681464A (en) * | 2018-11-27 | 2019-04-26 | 上海万泽精密铸造有限公司 | It is preset with the fire-resistant impeller of deformation slot |
Citations (9)
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|---|---|---|---|---|
| US4485888A (en) * | 1983-06-10 | 1984-12-04 | General Motors Corporation | Vehicle engine cooling apparatus |
| CN2216595Y (en) * | 1995-05-29 | 1996-01-03 | 徐盛东 | Air rotary starter |
| CN201896763U (en) * | 2009-09-30 | 2011-07-13 | 曼涡轮机股份公司 | Compressor |
| CN202301197U (en) * | 2011-08-19 | 2012-07-04 | 李晨 | Mouse-cage type gas-gathering flow guide device |
| CN202991622U (en) * | 2012-07-30 | 2013-06-12 | 福建省江南电器制造有限公司 | Extractor hood flap wheel |
| CN203384097U (en) * | 2013-03-28 | 2014-01-08 | 无锡小天鹅股份有限公司 | Centrifugal fan and clothes drying machine provided with same |
| CN103807189A (en) * | 2012-11-09 | 2014-05-21 | 辉达公司 | Turbine fan and display card with same |
| CN204253391U (en) * | 2013-10-31 | 2015-04-08 | 马勒贝洱两合公司 | Radial blower |
| CN105782117A (en) * | 2016-03-07 | 2016-07-20 | 合肥通用机械研究院 | Stability extending device of centrifugal compressor |
-
2018
- 2018-03-26 CN CN201810252036.7A patent/CN108561187A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4485888A (en) * | 1983-06-10 | 1984-12-04 | General Motors Corporation | Vehicle engine cooling apparatus |
| CN2216595Y (en) * | 1995-05-29 | 1996-01-03 | 徐盛东 | Air rotary starter |
| CN201896763U (en) * | 2009-09-30 | 2011-07-13 | 曼涡轮机股份公司 | Compressor |
| CN202301197U (en) * | 2011-08-19 | 2012-07-04 | 李晨 | Mouse-cage type gas-gathering flow guide device |
| CN202991622U (en) * | 2012-07-30 | 2013-06-12 | 福建省江南电器制造有限公司 | Extractor hood flap wheel |
| CN103807189A (en) * | 2012-11-09 | 2014-05-21 | 辉达公司 | Turbine fan and display card with same |
| CN203384097U (en) * | 2013-03-28 | 2014-01-08 | 无锡小天鹅股份有限公司 | Centrifugal fan and clothes drying machine provided with same |
| CN204253391U (en) * | 2013-10-31 | 2015-04-08 | 马勒贝洱两合公司 | Radial blower |
| CN105782117A (en) * | 2016-03-07 | 2016-07-20 | 合肥通用机械研究院 | Stability extending device of centrifugal compressor |
Non-Patent Citations (1)
| Title |
|---|
| 李俊超等: "《轴流压缩机原理与气动设计》", 30 September 1987 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109681464A (en) * | 2018-11-27 | 2019-04-26 | 上海万泽精密铸造有限公司 | It is preset with the fire-resistant impeller of deformation slot |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180921 |