CN108119405B - The design method of mixed pressure formula three dimendional blade diffuser - Google Patents
The design method of mixed pressure formula three dimendional blade diffuser Download PDFInfo
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- CN108119405B CN108119405B CN201711393228.1A CN201711393228A CN108119405B CN 108119405 B CN108119405 B CN 108119405B CN 201711393228 A CN201711393228 A CN 201711393228A CN 108119405 B CN108119405 B CN 108119405B
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Classifications
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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
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
- F04D29/444—Bladed diffusers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/124—Fluid guiding means, e.g. vanes related to the suction side of a stator vane
Abstract
The present invention relates to a kind of mixed pressure formula three dimendional blade diffuser, the area Ban Wuye blade suction surface is the multiple camber of relative ideal flow curve deviation, forms more wave system shock wave structures.Blade according to incoming flow open up to Mach number and inflow angle and reverse, formed three dimendional blade；Its design method includes the following steps: to extend diffuser passage to being divided intonA section；Determine wave system number；Determine blade angle；Determine each segmental arc length of the area Ban Wuye suction surface；Determine throat position；The design of section blades channel；Three dimendional blade whole design.Advantage: 1) efficiently using shock wave deceleration characteristic, weakens, eliminates acceleration of the supersonic flow in the area diffuser Ban Wuye；2) speed is down to subsonic speed in blade path, and continues deceleration diffusion, weakens, eliminates shock wave and the influence of Boundary Layer Interaction bring；3) diffuser efficiency and stable operation range are improved, the efficiency and pressure ratio of compressor are improved.
Description
Technical field
The present invention is a kind of mixed pressure formula three dimendional blade diffuser, belongs to radial-flow compressor technical field.
Background technique
The invention of aircraft and the development of aviation industry have important influence to All Around The World.And as the heart of aircraft
Aero-engine is the deciding factor of aeroplane performance, reliability and economy.Since half a century, aero-engine is
To high thrust ratio, the propulsion system stable development of high supercharging pressure level and high turbine inlet temperature.Therefore, centrifugal compressor is as middle-size and small-size
The main component of aircraft and helicopter turbogenerator complies with era development, increases power, and it is imperative to expand pressure ratio.At this
Under the requirement that kind is continuously improved, diffuser intake Mach number can reach 1.0 or more.If not controling effectively to it, can make to surpass
Subsonic airflow forms strong shock wave in diffuser, increases diffuser loss, declines entire centrifugal compressor performance sharply.
Flow field structure is extended to widely different at high pressure ratio centrifugal compressor impeller outlet, and Mach number and direction of flow extend
To variation.Existing diffuser mostly uses inducer to extend to the identical vertical pulling of blade angle to stretch blade.This blade is adapted to uniformly
Incoming flow, Mach number and flow angle, which are extended to the incoming flow being widely varied, greater loss.It extends and is made to different Mach numbers
At shock surface can promote flow separation with blade surface Boundary Layer Interaction, cause very big loss.Therefore control shock wave
Intensity and position to improve diffuser performance have a major impact.
Summary of the invention
Proposed by the present invention is that a kind of mixed pressure formula three dimendional blade diffuser and design method, purpose are intended to effective and reasonablely
Using shock wave deceleration characteristic, decrease even is eliminated acceleration and shock wave and attached face of the supersonic flow in the area diffuser Ban Wuye
Layer interaction bring influences, and improves the efficiency and pressure ratio of compressor.
Technical solution of the invention: a kind of mixed pressure formula three dimendional blade diffuser, mixed pressure formula three dimendional blade diffuser
Blade Ban Wuye area's suction surface is the multistage arc shaped surface of relative ideal flow curve deviation, forms more wave system shock wave structures；Blade
According to incoming flow open up to Mach number and inflow angle and reverse, formed three dimendional blade.
Its design method, includes the following steps:
(1) diffuser passage is extended to being divided intonA section；
(2) wave system number is determined；
(3) blade angle is determined；
(4) each segmental arc length of the area Ban Wuye suction surface is determined；
(5) throat position is determined；
(6) section blades channel is designed；
(7) three dimendional blade whole design.
Beneficial effects of the present invention:
1) shock wave deceleration characteristic is efficiently used, weakens and even is eliminated supersonic flow adding in the area diffuser Ban Wuye
Speed；
2) speed is down to subsonic speed in blade path, and continues deceleration diffusion, can weaken and even be eliminated shock wave and attached face
Layer interaction bring influences；
3) diffuser efficiency and stable operation range are improved, the efficiency and pressure ratio of compressor are improved.
Detailed description of the invention
Attached drawing 1 is that prismatic blade diffuser intake section difference is opened up to position flow schematic diagram.
Attached drawing 2 is that centrifugal compressor diffuser inlet air flow angle and inflow Mach number are extended to distribution in twisted blade diffuser
(distribution of stream air angle) schematic diagram.
Attached drawing 3 is the area Ban Wuye blade suction surface multiple camber and throat's position view.
Attached drawing 4 is section blade profile schematic diagram.
Attached drawing 5 is mixed pressure formula three dimendional blade diffuser schematic diagram.
In figure,For oblique shock angle,OO'For air-flow in radial direction without ideal flow curve initial in leaf section, A, B are venturi position
It sets,lIt is curved surface in the section lower curve.
Specific embodiment
Mixed pressure formula three dimendional blade diffuser, the area Ban Wuye suction surface are the multiple camber of relative ideal flow curve deviation,
Form more wave system shock wave structures；Blade according to incoming flow open up to Mach number and inflow angle and reverse, formed three dimendional blade.
The design method of the mixed pressure formula three dimendional blade diffuser, includes the following steps:
(1) diffuser passage is extended to being divided intonA section；
(2) wave system number is determined；
(3) blade angle is determined；
(4) each segmental arc length of the area Ban Wuye suction surface is determined；
(5) throat position is determined；
(6) section blades channel is designed；
(7) three dimendional blade whole design.
The step (1) extends diffuser passage to being divided intonA section: determining the overall dimensions of diffuser, by diffusion
Device meridional channel is extended to being divided intonA section:n≥2。
The step (2) determines wave system number: shock wave number ism,m>=2, weak oblique shock wave number ism- 1, normal shock wave number
It is 1.
The step (3) determines blade angle: according to different cross section free stream Mach numberM i0 Determine the initial angle of wedge i1 (1°≤ ij≤15°,1≤i≤n,1≤j<m,n>=2), oblique shock angle i1And Mach number M after wavei1, successively take the angle of wedge ij, acquire
Thereafter corresponding ijAnd Mij。
The step (4) determines each segmental arc length of the area Ban Wuye suction surface: ignoring boundary-layer and increases influence, according to continuity
Equation and conservation of angular momentum equation, determine the free stream Mach number in each sectionM i0 And flow angle i0 The ideal flow of downstream
CurveAs initial designs benchmark；ByOPoint starting is according to each angle of wedge ij (1≤j≤m- 1) successively make curvel ij (1
≤j≤m- 1), curve relative datum curveDeflection, and adjust curvel ij (1≤j≤m- 2) length,
So that each oblique shock wave extension meets at a point, it is denoted as point A.
The step (5) determines throat position: using oblique shock wave extension intersection point A point as the pressure face leading edge point of adjacent blades,
Determine that its blade pressure surface molded line originates tangent line and radial angle at A point i01 ,,
A point work is crossed perpendicular to the vertical line of pressure face molded line, with curvel i(m-1)Point B is met at, thereby determines that the last item curvel i(m-1)It is long
Degree and venturi position A, B.
Step (6) design section blade path: to originate corner cut i01 On the basis of, it crosses venturi A point and makees pressure face type
Line, taking equivalent divergent angle is 2 ° ~ 35 °, makees corresponding suction surface molded line after venturi B point, keeps the expansion of venturi rear blade channel logical
Road obtains the vane type line at section according to the annulus area difference of the period area of blade path and section, completes blade and sets
Meter.
Step (7) the three dimendional blade whole design: it is completed according to step (5)nIt is right after a cross-sectional passage designnA section
Face channel carries out three-dimensional leading edge product and folds, and obtains a series of blade profiles comprising torsional characteristics；To at blade suction surface venturi position into
The processing of row rounding realizes that suction surface molded line smoothly transits；To sum up complete mixed pressure formula three dimendional blade diffuser Design.
Technical solution of the present invention is further described with reference to the accompanying drawing:
Attached drawing 1 is compareed, diffuser intake section difference is opened up to position flow schematic diagram, and prismatic blade is only adapted to uniform incoming flow,
Mach number and flow angle, which are extended to the incoming flow being widely varied, greater loss.
Attached drawing 2 is compareed, diffuser passage is extended to (leaf Gao Fangxiang) and is divided intonA section,n≥2.Each section obtains phase
The inlet air flow angle answered and inflow Mach number.
Attached drawing 3 is compareed, determines wave system numberm,m≥2.Wherein weak oblique shock wave coefficient ism- 1, normal shock wave number is 1.It is designing
Under state, according to stream air angle extend to different distributions, determine each corresponding blade angle of section entrance.Origin stream horse
Conspicuous several Mi0Determine the initial angle of wedge i1 (1°≤ ij≤15°,1≤i≤n,1≤j<m,n>=2), oblique shock angle i1And wave
Mach number M afterwardsi1, successively take the angle of wedge ij, acquire corresponding thereafter ijAnd Mij。
Ignore boundary-layer and increase influence, according to continuity equation and conservation of angular momentum equation, determines coming for each section
StreamM i0 And flow angle i0 The ideal flow curve of downstream, in this, as initial designs benchmark；ByOPoint starting basis
Each angle of wedge ij (1≤j≤m- 1) successively make curvel ij (1≤j≤m- 1), curve relative datum curveDeflection, and adjust curvel ij (1≤j≤m- 2) length is denoted as a little so that the extension of each oblique shock wave meets at a point
A。
Using A point as the pressure face leading edge point of adjacent blades, determine that its blade pressure surface molded line originates tangent line and diameter at A point
To angle i01 ,, A point work is crossed perpendicular to the vertical line of pressure face molded line, with curvel i(m-1)
Point B is met at, thereby determines that the last item curvel i(m-1)Length and venturi position A, B.
Attached drawing 4 is compareed, to originate corner cut i01On the basis of, it crosses venturi A point and does pressure face molded line, taking equivalent divergent angle is 2 °
~ 35 °, makees corresponding suction surface molded line after venturi B point, make venturi rear blade channel expanding channel, according to the week of blade path
The annulus area difference in phase area and section obtains the vane type line at section, completes blade design.
Attached drawing 5 is compareed, is completednIt is right after a cross-sectional passage designnA cross-sectional passage carries out three-dimensional leading edge product and folds, and is wrapped
A series of blade profiles containing torsional characteristics.Meanwhile to rounding processing is carried out at blade suction surface venturi position, suction surface molded line is realized
It smoothly transits.Mixed pressure formula three dimendional blade moulding has been determined after above-mentioned processing.
Mixed pressure formula three dimendional blade diffuser, structure are that the area Ban Wuye blade suction surface molded line is bent in multiple camber,
Make up to the purpose of more wave system shock wave tissues.
Embodiment 1
Diffuser vane is extended to being divided intonA section；The area blade Ban Wuye is completed by inlet air flow angle and Mach number
The design of suction surface multistage arcwall face；Pass through the folded design for completing blade twist of each section blades molded line three-dimensional leading edge product；It will be with
Upper design method is implemented in combination with the diffuser Design of mixed pressure formula three dimendional blade.
1) overall dimensions of diffuser, including inlet diameter 300mm, inlet vane height 15mm, maximum gauge are determined
450mm, design meridional channel are contour meridian plane.Diffuser meridional channel is extended to (blade height direction) and is divided into 5 sections
Face.
2) each section incoming flow angle is respectively 10~ 50With inflow Mach number M10~M50, determine 5 section entrance leaves
The initial angle of wedge of piece suction surface 11~ 51With initial Angle of Shock Waves 11~ 51.Then it has been determined that first curve of respective cross-section is opposite
Ideal flow perspective curve is 11~ 51, determine that shock wave number is 4, oblique shock wave number is 3.In section 1, according to import horse
Conspicuous several M10=1.41, initial flow angle 10=50 o, determine the initial angle of wedge 11It is 3 o, then corresponding Angle of Shock Waves 11=49 o, after wave
Mach 2 ship M11=1.306, next curvel 12Relative angle is=6 o.Determine next angle of wedge 12=3 oAfterwards
To corresponding Angle of Shock Waves 12=54.9o, thus can determine arcwall facel 11Length is 11.74mm, is made 12Oblique shock wave line and inhale
The initial Angle of Shock Waves in power face 11Oblique shock wave line extend near same point A, can similarly obtain 13=3 oWith 13=65.62 o, together
Sample makes Angle of Shock Waves 13Corresponding oblique shock wave line extends to A point and nearby obtains curvel 12Length is 13.17mm, initially to carry out gas
Flow angle 10=50 oThe vertical line of the tangent line is done using A point as adjacent blades leading edge point for the initial corner cut of adjacent blades pressure face molded line
With the last item curvel 13Intersection points B determines curve with thisl 13Length is 15.73mm.Determine that venturi position AB, venturi are long simultaneously
Degree is 28.17mm.2 ~ section of section 5 is same as above.The area each section blades Ban Wuye multistage arcwall face shape and venturi has then been determined
Shape (Fig. 3).
3) on section 1, making pressure face molded line by adjacent blades leading edge point of A point in A point and radial angle is initial gas
Flow 50 ° of angle.It takes equivalent divergent angle to be 10 ° and does suction surface molded line after venturi B point, so that venturi rear blade channel is become an expansion logical
Road, last one of normal shock wave generates naturally in the somewhere of expanding channel at this time, and fluid continues in expanding channel to slow down behind to increase
Pressure.The design of 1 channel of section is completed at this time.Section can be obtained in the period area in channel 1 and the annulus area difference in section 1 at this time
Vane type line at 1 completes blade design.It is same as above with 2 ~ section of section 5.All section blade profiles (Fig. 4) can finally be obtained.
4) after obtaining all section blade profiles, according to costa O1O5It is folded to carry out leading edge product, then suction surface at venturi B point is turned
Dog-ear larger part carries out rounding processing, so that suction surface molded line is smoothly transitted, this makes it possible to obtain a series of leaves comprising torsional characteristics
Type.
The diffuser mixed pressure formula three dimendional blade (Fig. 5) makes blade and air-flow by adjusting the established angle of different location
It is always maintained at suitable positive incidence state, the area blade Ban Wuye suction can compress shock wave.Blade adapt to incoming flow open up to
Different Mach numbers and reverse.For supersonic speed inflow condition in the case where unavoidably generating shock wave, effective and reasonable land productivity
With shock wave deceleration characteristic, decrease even is eliminated acceleration situation of the supersonic flow in the area diffuser Ban Wuye；In blade path
Speed is down to subsonic speed after interior last one of normal shock wave, can weaken and even be eliminated shock wave and Boundary Layer Interaction bring shadow
It rings；Diffuser expanding ability and stable operation range are improved, the whole grade performance of centrifugal compressor is promoted to improve.
Claims (1)
1. the design method of mixed pressure formula three dimendional blade diffuser, diffuser Ban Wuye area's blade suction surface is relative ideal stream
The multiple camber of moving curve deviation, forms more wave system shock wave structures, blade according to incoming flow open up to Mach number and inflow angle and turn round
Turn, forms three dimendional blade；
It is characterized in that its design method includes the following steps:
(1) diffuser passage number of cross-sections are determined；
(2) wave system number is determined；
(3) blade angle is determined；
(4) each segmental arc length of the area Ban Wuye suction surface is determined；
(5) throat position is determined；
(6) design section blade path；
(7) design three dimendional blade is whole；
The step (1) determines diffuser passage number of cross-sections: determining the overall dimensions of diffuser, diffuser meridional channel is extended
To being divided intonA section,n≥2；
The step (2) determines wave system number: shock wave number ism,m>=2, wherein weak oblique shock wave number ism- 1, normal shock wave number
Mesh is 1；
The step (3) determines blade angle: according to different cross section free stream Mach numberM i0 Determine the initial angle of wedge i1 (1°≤ ij ≤
15°,1≤i≤n,1≤j<m,n>=2), oblique shock angle ij And Mach number after waveM i1 , the angle of wedge is successively taken thereafter ij , acquire
Thereafter corresponding oblique shock angle ij With Mach number after waveM ij ；
The step (4) determines each segmental arc length of the area Ban Wuye suction surface: ignoring boundary-layer and increases influence, according to continuity equation
With conservation of angular momentum equation, the free stream Mach number in each section is determinedM i0 And flow angle i0 The ideal flow curve of downstream
As initial designs benchmark；ByOPoint starting is according to each angle of wedge ij (1≤j≤m- 1) successively make curvel ij (1≤j≤m-
1), relative datum curve --- ideal flow curve veering, and adjust curvel ij (1≤j≤m- 2) length, so that each oblique
Shock wave extension meets at a point, is denoted as point A；
The step (5) determines throat position: extending intersection point A point as the pressure face leading edge point of adjacent blades using oblique shock wave, determines
Its blade pressure surface molded line originates tangent line and radial angle at A point i01 , cross A point and make hanging down perpendicular to pressure face molded line
Line, with curvel i(m-1)Point B is met at, thereby determines that the last item curvel i(m-1)Length and venturi position A, B；
Step (6) design section blade path: to originate tangent line and radial angle i01 On the basis of, it crosses venturi A point and does
Pressure face molded line, taking equivalent divergent angle is 2 ° ~ 35 °, makees corresponding suction surface molded line after venturi B point, makes venturi rear blade channel
For expanding channel, the vane type line at section is obtained according to the annulus area difference of the period area of blade path and section, it is complete
At blade design；
Step (7) the design three dimendional blade is whole: completingnIt is right after a cross-sectional passage designnBefore a cross-sectional passage carries out three-dimensional
Edge product is folded, obtains a series of blade profiles comprising torsional characteristics；To rounding processing is carried out at blade suction surface venturi position, realizes and inhale
Power face molded line smoothly transits；To sum up complete mixed pressure formula three dimendional blade diffuser Design.
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| CN110878768A (en) * | 2019-12-20 | 2020-03-13 | 中国北方发动机研究所(天津) | Vaned diffuser structure with variable inlet vane angle type guide vanes |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1384794A (en) * | 1999-08-25 | 2002-12-11 | 波音公司 | Supersonic external-compression diffuser and method for designing same |
| CN103775388A (en) * | 2014-01-08 | 2014-05-07 | 南京航空航天大学 | Sweeping and twisting type three-dimensional blade diffuser and design method thereof |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US6506023B1 (en) * | 2000-09-05 | 2003-01-14 | Industrial Technology Research Institute | Integrally formed stamping sheet-metal blades having 3D structure |
| US9546625B2 (en) * | 2014-10-06 | 2017-01-17 | Hamilton Sundstrand Corporation | Volute for engine-mounted boost stage fuel pump |
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2017
- 2017-12-21 CN CN201711393228.1A patent/CN108119405B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1384794A (en) * | 1999-08-25 | 2002-12-11 | 波音公司 | Supersonic external-compression diffuser and method for designing same |
| CN103775388A (en) * | 2014-01-08 | 2014-05-07 | 南京航空航天大学 | Sweeping and twisting type three-dimensional blade diffuser and design method thereof |
Non-Patent Citations (1)
| Title |
|---|
| 《保形通道式扩压器在微型涡喷发动机中的应用》;宣建光等;《南京航空航天大学学报》;20101231;第42卷(第6期);全文 |
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