CN108119406A - Axial flow compressor circumferential direction large-spacing small through hole casing - Google Patents
Axial flow compressor circumferential direction large-spacing small through hole casing Download PDFInfo
- Publication number
- CN108119406A CN108119406A CN201810027169.4A CN201810027169A CN108119406A CN 108119406 A CN108119406 A CN 108119406A CN 201810027169 A CN201810027169 A CN 201810027169A CN 108119406 A CN108119406 A CN 108119406A
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- Prior art keywords
- hole
- axial flow
- casing
- flow compressor
- circumferential direction
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to a kind of axial flow compressor circumferential direction large-spacing small through hole casing, structure includes casing, through hole, rotor；Wherein through hole is arranged on the outer surface of casing, is directly connected with casing external ambient atmosphere, and rotor is arranged on the inside of casing；Using the pressure difference inside and outside the relative motion of casing and rotor and through hole casing, driving through hole gas flowing, and through hole interior air-flow acts on the periodic excitation flowed in compressor to realize by periodically scanning compressor rotor runner.Advantage：1）It can inhibit the coverage and intensity of the unfavorable low energy stream near axial flow compressor blade tip, so as to be significantly expanded the steady operation nargin of axial flow compressor；2）Using unsteady excitation effect, the influence to axial flow compressor efficiency is smaller；3）It is simple in structure, facilitate application implementation.
Description
Technical field
The present invention relates to a kind of axial flow compressor circumferential direction large-spacing small through hole casings, belong to compressor design field.
Background technology
With requirement of the modern aeroengine to high thrust-weight ratio, low consumption oil cut rate, small front face area, compressor needs more
High grade pressure ratio could meet these performance requirements.But the grade pressure ratio of compressor is higher, load will become larger, and be susceptible to
The unstable periods such as rotating stall, surge.The unstable periods such as rotating stall, surge can bring the drastically decline of engine performance
With serious vibration problem, have a negative impact to the service life of engine.Therefore, it is necessary to develop effective flow control means
To expanding the stability margin of compressor.
Blade tip flow field is since Mach number is higher, and also end-wall boundary layer, tip leakage stream, the interaction shape of mainstream
Into complicated nonstationary flow field structure, it is easiest to become stall inception position, therefore can to the control and improvement in blade tip flow field
More efficiently to increase stable operation range.The characteristics of encouraging is applied according to stream field, can be divided into based on permanent excitation
Control method and the control method based on unsteady excitation.The former has had numerous scholars to expand research, devises a variety of controls
Method processed can be effectively increased stability margin, such as permanent jet of blade tip etc.；But it is disadvantage is that the excitation density applied
Very big, the influence to mainstream is apparent, can reduce the efficiency of compressor while expanding stability margin, and needs complicated pipe
Line structure and control valve add the weight and cost of engine.Control means based on unsteady excitation can be with stream field
Apply the excitation of certain frequency, when driving frequency is near the dominant frequency of flow field, it is possible to certain relevant effect occur, change stream
Quasi-ordering mechanism be allowed to more in order, generation phenomena such as so as to delay rotating stall surge expands stability margin.It is unsteady
Encourage required excitation density more much smaller than permanent excitation, the influence to mainstream is also small, realizes that expand steady obtain may be used also simultaneously
To reduce the influence to efficiency.Therefore, the control mode based on unsteady excitation has very big superiority, it is necessary to a kind of simple
The reliable specific implementation for meeting engineering reality.
The content of the invention
Proposed by the present invention is a kind of axial flow compressor circumferential direction large-spacing small through hole casing, and the purpose is to reduce to the greatest extent pair
On the premise of the influence of the efficiency of compressor and the complexity of simplify control method, it is abundant to expand stablizing for compressor to greatest extent
Degree.
The technical solution of the present invention：Axial flow compressor circumferential direction large-spacing small through hole casing, structure include casing 1,
Through hole 2, rotor 3；Through hole 2 is arranged on the outer surface of casing 1, is directly connected with 1 external ambient atmosphere of casing, and rotor 3 is arranged on casing 1
Inside.
Advantages of the present invention：
1）It can inhibit the unfavorable low energy stream near axial flow compressor blade tip（Leakage vortex, blade back separation whirlpool etc.）Coverage and
Intensity, so as to be significantly expanded the steady operation nargin of axial flow compressor；
2）Using unsteady excitation effect, it is more than total via area an order of magnitude smaller than general processor box on casing,
Influence to axial flow compressor efficiency is smaller；
3）It is simple in structure, facilitate application implementation.
Description of the drawings
Attached drawing 1 is axial flow compressor circumferential direction large-spacing small through hole casing partial structural diagram.
Attached drawing 2-1,2-2 are axial flow compressor circumferential direction large-spacing small through hole casing energisation mode schematic diagrames, and wherein Fig. 2-1 is
Jet-action schematic diagram, Fig. 2-2 are swabbing action schematic diagrames.
Attached drawing 3 is axial flow compressor circumferential direction large-spacing small through hole casing through hole distribution schematic diagram.
Attached drawing 4-1,4-2,4-3 are axial flow compressor circumferential direction large-spacing small through hole casing shape of through holes schematic diagram, wherein scheming
4-1 is rectangular through-hole schematic diagram, and Fig. 4-2 is ellipse hole schematic diagram, and Fig. 4-3 is hyperelliptic through hole schematic diagram.
Attached drawing 5-1,5-2 are the position views of the through hole under different incentive action modes, and wherein Fig. 5-1 is jet-action
Schematic diagram, Fig. 5-2 are swabbing action schematic diagrames.
Wherein 1 be casing, 2 be through hole, 3 be rotor, L1 and L2 be distance of the through hole away from leading edge, b is axial-flow compressor
Axial chord length, R1 are casing radius（Casing thickness is disregarded）, R2 be hub radius, A is oval（Hyperelliptic）Long axis length, B are
It is oval（Hyperelliptic）Minor axis length, C are rectangle length, D is rectangle width, r is radius of corner.
Specific embodiment
As shown in Figure 1, axial flow compressor circumferential direction large-spacing small through hole casing, structure includes casing 1, through hole 2, rotor 3；
Through hole 2 is arranged on the surface of casing 1, is directly connected with 1 external ambient atmosphere of casing, and rotor 3 is arranged on the inside of casing 1；Utilize machine
Pressure difference inside and outside the relative motion of casket and rotor and through hole casing, driving through hole gas flowing, and through hole interior air-flow passes through
It periodically scans compressor rotor runner and the periodic excitation flowed in compressor is acted on to realize.
As shown in Fig. 2-1,2-2, according to the gauge pressure Pb for the through hole opened（Interior flow field pressure and external environment atmospheric pressure
The difference of power）Difference, ambient atmosphere is divided into the excitation in blade tip flow field periodically injection excitation and periodical suction activation, if logical
Hole location compressor interior flow field gauge pressure is negative, then energisation mode is periodical jet-action；If compressor at lead to the hole site
Interior flow field gauge pressure is just, then energisation mode is periodical swabbing action.
As shown in figure 3, the through hole 2 has N1, the machine at impeller of rotor import and blade inlet edge short spacing L1
1 surface of casket is set for one week or 1 surface of casing at impeller of rotor import and blade inlet edge long spacing L2 is set for one week；
The quantity of through hole 2 is chosen with reference to axial flow compressor blade quantity, if compressor blade quantity is Z, Z is by existing axial flow compressor
The model number of blade determines that the scope of N1/Z is 0.4-0.7, and wherein ratio is optimal for 0.5 control effect.
As shown in Fig. 4-1,4-2,4-3, one kind in following several shapes may be selected in the shape of the through hole 2：
1. ellipse, major axis A and the ratio range of short axle B are 1.0-5.0, the area A1 of single through hole is 1/4πAB；
2. rectangle, the ratio range of long side C and short side D is 1.0-5.0, this class rectangle can be with there are one minor radius fillet, circles
Angular radius r is the 1/5 of short side, and the area A3 of round rectangle is (CD- π r at this time2)；
3. the hyperelliptic generated according to the following formula：（x/A）n+（y/B）n=1；Its major axis A and the ratio range of short axle B are
The value range of 1.0-5.0, index n are 2.0-10.0, and area is 4ab (Γ (1+1/n)) 2/ Γ (1+2/n), Γ (z) are
Tz-1/et makees t from 0 to just infinite integration, Γ (z)=(z-1) when z is integer!.
As shown in fig. 5-1, if incentive action mode is to carry out periodical injection to compressor inside, lead to the hole site can be pressed
Following criterion design：On meridian plane, the position at through hole center and blade inlet edge distance are L1 on casing, if axial flow compressor
The scope of shaft orientation string a length of b, L1/b are -0.1- 0.1.Wherein L1/b is negative, then it represents that through hole is opened in before blade inlet edge；L1/
B is just, then it represents that through hole is opened in the blade grid passage after blade inlet edge；As shown in Fig. 5-2, if incentive action mode is to pressure
Periodical suction is carried out inside mechanism of qi, then lead to the hole site can be designed by following criterion：On meridian plane, through hole center on casing
Position is L2 with blade inlet edge distance, and the scope of the shaft orientation string a length of b, L2/b of axial flow compressor are 0.0-0.4.
If incentive action mode is to carry out periodical injection to compressor inside, via area can be set by following criterion
Meter：The emitted dose of casing through hole depends on the area of through hole on casing, and the area of single through hole is A1, if compressor inlet area
For A2, the area of A2 isπR12-πR22, the scope of A1/A2 is 0.01%-0.1%.During actual design, calm the anger if needing to be promoted simultaneously
The stability margin of machine and the influence to efficiency is reduced as far as possible, then A1/A2 takes median；If be partial to consider compressor stablize it is abundant
The promotion of degree and the influence to efficiency can be larger, then A1/A2 can be bigger than normal；If only it is partial to consider the shadow to the efficiency of compressor
Ring degree and can be smaller to the promotion of stability margin, then A1/A2 can be less than normal.
If incentive action mode is that periodical suction is carried out to compressor inside, via area can be set by following criterion
Meter：The rate of air sucked in required of casing through hole depends on the area of through hole on casing, and the area of single through hole is A3, and compressor inlet area is
The scope of A2, A3/A2 are 0.01%-0.05%.During actual design, if needing to be promoted the stability margin and as far as possible of compressor simultaneously
The influence to efficiency is reduced, then A3/A2 takes median；If being partial to the promotion of consideration compressor stability margin to the shadow of efficiency
Sound can be larger, then A3/A2 can be bigger than normal；If it is partial to consider to put forward stability margin the influence degree of the efficiency of compressor
Rising can be smaller, then A3/A2 can be less than normal.
Embodiment 1（By taking Rotor37 rotor parameters as an example）
Axial flow compressor circumferential direction large-spacing small through hole casing, structure include casing 1, through hole 2, rotor 3；Wherein casing 1 is in circle
Cylindricality, through hole 2 are arranged on the outer surface of casing 1, are directly connected with 1 external ambient atmosphere of casing, and several rotors 3 are arranged on casing 1
Hollow interior.
The through hole 2 has N1,1 surface of casing at impeller of rotor import and blade inlet edge short spacing L1 one week
It sets, the quantity of through hole 2 is chosen with reference to axial flow compressor blade quantity, and compressor blade quantity is Z, it is known that Z=36, N1/Z take
0.5, then N1=18.
Compressor interior flow field gauge pressure is negative at lead to the hole site, and energisation mode is periodical jet-action, through hole on casing
The position at center and blade inlet edge distance are L1, and shaft orientation string a length of b of axial flow compressor, L1/b take -0.1, be opened in blade inlet edge
Before, it is known that axial chord length b=84mm of blade tip（Rounding）, then L1=8.4mm.
The area of single through hole be A1, compressor inlet area be A2, A1/A2=0.01%, A2=πR12-πR22, it is known that into
Mouthful tip radlus R1=152.86mm, hub radius R2=107.02mm, then A2=37420mm2（Rounding）, A1=3.742mm2。
The shape of through hole 2 takes ellipse, and major axis A and the ratio of short axle B are 3.0, and the area A1 of single through hole is 1/4π
AB, it is known that A1=3.742mm2, then A=3.642mm, B=1.214mm.
Embodiment 2（By taking Rotor37 rotor parameters as an example）
Axial flow compressor circumferential direction large-spacing small through hole casing, structure include casing 1, through hole 2, rotor 3；Wherein casing 1 is in circle
Cylindricality, through hole 2 are arranged on the outer surface of casing 1, are directly connected with 1 external ambient atmosphere of casing, and several rotors 3 are arranged on casing 1
Hollow interior.
The through hole 2 has N1,1 surface of casing at impeller of rotor import and blade inlet edge long spacing L2 one week
It sets, the quantity of through hole 2 is chosen with reference to axial flow compressor blade quantity, and compressor blade quantity is Z, it is known that Z=36, N1/Z take
0.5, then N1=18.
Compressor interior flow field gauge pressure is just, then energisation mode is periodical swabbing action, is led on casing at lead to the hole site
The position at hole center and blade inlet edge distance are L2, and shaft orientation string a length of b of axial flow compressor, L2/b take 0.2, be opened in blade inlet edge
In blade grid passage afterwards, it is known that blade tip axial direction chord length b=84mm（Rounding）, then L2=16.8mm.
The area of single through hole is A3, if compressor inlet area is A2, A3/A2 0.01%, A2=πR12-πR22, it is known that
Import tip radlus R1=152.86mm, hub radius R2=107.02mm, then A2=37420mm2（Rounding）, A3=3.742mm2。
The shape of through hole 2 takes ellipse, and major axis A and the ratio of short axle B are 3.0, and the area A3 of single through hole is 1/4π
AB, it is known that A3=3.742mm2, then A=3.642mm, B=1.214mm.
Claims (8)
1. axial flow compressor circumferential direction large-spacing small through hole casing, it is characterized in that including casing, through hole, rotor；Wherein through hole is arranged on
The outer surface of casing, rotor are arranged on the inside of casing.
2. axial flow compressor circumferential direction large-spacing small through hole casing according to claim 1, it is characterized in that the through hole has
N1, the casing surface at impeller of rotor import and blade inlet edge short spacing L1 is set or around impeller of rotor for one week
Import is set for one week with the casing surface at blade inlet edge long spacing L2.
3. axial flow compressor circumferential direction large-spacing small through hole casing according to claim 2, it is characterized in that the through hole
Quantity N1 chooses with reference to axial flow compressor blade quantity Z, and Z determines that N1/Z is by the existing axial flow compressor model number of blade
0.4-0.7。
4. axial flow compressor circumferential direction large-spacing small through hole casing according to claim 1, it is characterized in that the through hole
Shape is ellipse, one kind in rectangle, hyperelliptic；The ratio of the ellipse, major axis A and short axle B are 1.0-5.0；
The rectangle, the ratio of long side C and short side D is 1.0-5.0, and there are one minor radius fillets for band；The hyperelliptic according to
The following formula generates：(x/A)n+(y/B)n=1, major axis A and the ratio of short axle B are 1.0-5.0, and the value of index n is
2.0-10.0。
5. axial flow compressor circumferential direction large-spacing small through hole casing according to claim 2, it is characterized in that before the blade
The ratio L1/b of edge short spacing L1 and axial flow compressor axial direction chord length b is -0.1- 0.1.
6. axial flow compressor circumferential direction large-spacing small through hole casing according to claim 5, it is characterized in that the through-hole face
The ratio A1/A2 of product A1 and axial flow compressor inlet -duct area A2 is 0.01%-0.1%.
7. axial flow compressor circumferential direction large-spacing small through hole casing according to claim 2, it is characterized in that before the blade
The ratio L2/b of edge long spacing L2 and axial flow compressor axial direction chord length b is 0.0-0.4.
8. axial flow compressor circumferential direction large-spacing small through hole casing according to claim 7, it is characterized in that the through-hole face
The ratio A3/A2 of product A3 and axial flow compressor inlet -duct area A2 is 0.01%-0.05%.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810027169.4A CN108119406B (en) | 2018-01-11 | 2018-01-11 | Axial compressor circumferential large-interval small-through-hole casing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810027169.4A CN108119406B (en) | 2018-01-11 | 2018-01-11 | Axial compressor circumferential large-interval small-through-hole casing |
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| Publication Number | Publication Date |
|---|---|
| CN108119406A true CN108119406A (en) | 2018-06-05 |
| CN108119406B CN108119406B (en) | 2020-11-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810027169.4A Active CN108119406B (en) | 2018-01-11 | 2018-01-11 | Axial compressor circumferential large-interval small-through-hole casing |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111520355A (en) * | 2020-05-18 | 2020-08-11 | 南京航空航天大学 | Adjustable phase and frequency unsteady flow control device based on bevel gear transmission |
| CN111734679A (en) * | 2020-07-02 | 2020-10-02 | 中国航发常州兰翔机械有限责任公司 | Aeroengine compressor inner casing with air vent and machining method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3993414A (en) * | 1973-10-23 | 1976-11-23 | Office National D'etudes Et De Recherches Aerospatiales (O.N.E.R.A.) | Supersonic compressors |
| CN1840864A (en) * | 2005-02-16 | 2006-10-04 | 斯奈克玛 | Bleeding air from the tip of the rotating blades in a high pressure compressor of a turbine engine |
| CN102817865A (en) * | 2011-06-08 | 2012-12-12 | 西门子公司 | Axial turbo compressor |
| CN103299084A (en) * | 2011-01-11 | 2013-09-11 | 斯奈克玛 | Turbofan engine |
| US9726084B2 (en) * | 2013-03-14 | 2017-08-08 | Pratt & Whitney Canada Corp. | Compressor bleed self-recirculating system |
-
2018
- 2018-01-11 CN CN201810027169.4A patent/CN108119406B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3993414A (en) * | 1973-10-23 | 1976-11-23 | Office National D'etudes Et De Recherches Aerospatiales (O.N.E.R.A.) | Supersonic compressors |
| CN1840864A (en) * | 2005-02-16 | 2006-10-04 | 斯奈克玛 | Bleeding air from the tip of the rotating blades in a high pressure compressor of a turbine engine |
| CN103299084A (en) * | 2011-01-11 | 2013-09-11 | 斯奈克玛 | Turbofan engine |
| CN102817865A (en) * | 2011-06-08 | 2012-12-12 | 西门子公司 | Axial turbo compressor |
| US9726084B2 (en) * | 2013-03-14 | 2017-08-08 | Pratt & Whitney Canada Corp. | Compressor bleed self-recirculating system |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111520355A (en) * | 2020-05-18 | 2020-08-11 | 南京航空航天大学 | Adjustable phase and frequency unsteady flow control device based on bevel gear transmission |
| CN111734679A (en) * | 2020-07-02 | 2020-10-02 | 中国航发常州兰翔机械有限责任公司 | Aeroengine compressor inner casing with air vent and machining method thereof |
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| CN108119406B (en) | 2020-11-27 |
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