CN106089808A - A kind of blade diffuser with trailing edge structures before swallow-tail form and formative method thereof - Google Patents
A kind of blade diffuser with trailing edge structures before swallow-tail form and formative method thereof Download PDFInfo
- Publication number
- CN106089808A CN106089808A CN201610608677.2A CN201610608677A CN106089808A CN 106089808 A CN106089808 A CN 106089808A CN 201610608677 A CN201610608677 A CN 201610608677A CN 106089808 A CN106089808 A CN 106089808A
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- China
- Prior art keywords
- diffuser
- blade
- tail form
- swallow
- trailing edge
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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
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic material
-
- 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
- F04D29/02—Selection of particular materials
- F04D29/023—Selection of particular materials 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
- F04D29/66—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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of blade diffuser with trailing edge structures before swallow-tail form and formative method thereof, including diffuser wheel disc, diffuser wheel cap, built-in radial diffuser vane, built-in axial diffuser vane, described radial diffuser blade and axially diffuser vane are circumferentially evenly distributed between diffuser wheel disc and diffuser wheel cap.This diffuser can be formed by the transformation of conventional leaf diffuser creativeness, there is the advantages such as moulding is convenient, cost is low, processing is simple, before its special swallow-tail form, trailing edge can improve the diffuser adaptation ability to the centrifugal impeller outlet unordered flowing of high speed, thus increases substantially high pressure ratio centrifugal compressor efficiency and steady operation nargin；The scale prevention coating of its blade is effectively reduced the generation of dirty, keep enough ventilation area, reduce flowage friction power, thus reduce the surge problems of compressor, improve the safety of compressor, Small Aeroengine high pressure ratio centrifugal compressor can be particularly well-suited to.
Description
Technical field
The invention belongs to high pressure ratio centrifugal compressor field, relate to a kind of there is the vane type of trailing edge structures before swallow-tail form expanding
Depressor and formative method thereof.
Background technology
Owing to having compact conformation, pressure ratio is high, reliability is high, easily manufactured, with low cost, good manufacturability and wider steady
Determining the advantages such as margin of operation, centrifugal compressor has obtained using widely on middle-size and small-size electromotor.Start for improving further
Thrust-weight ratio/the power to weight ratio of machine, improves the performance under the various state of flight in high-altitude, the pressure ratio requirements at the higher level to centrifugal compressor；High
Pressure ratio centrifugal compressor impeller outlet air flow velocity is high and uneven, and it is the least to add centrifugal impeller exit width, and diffuser enters
With impeller outlet closely, there is strong unsteady interaction in mouth, deteriorates centrifugal impeller and diffuser between the two
Coupling, is substantially reduced efficiency and the stable operation range of centrifugal compressor, and the diffuser Design causing compact conformation loss low is non-
The most challenging, become restriction high pressure ratio centrifugal compressor and be applied to the major technical barrier that engineering is actual.
The swallow-tail form leading edge that tubular diffuser becomes due to its adjacent two tubular diffuser wall intersecting shape can better conform to
The high speed Non-Uniform Flow of rotor outlet, and compared with conventional leaf diffuser, have less during identical flow area
Wall surface area, reduces friction loss, is conducive to improving efficiency and the steady operation nargin of high pressure ratio centrifugal compressor, and North America leads to
Tubular diffuser is successfully applied in actual model with Pu Hui company.But, for radial diffuser and axially expand
Transformer design becomes the tubular diffuser being connected, and generally there is the phenomenon that axial exit flow is the most uneven, thus
The compressor surge problem caused also brings potential safety hazard, it addition, tubular diffuser there is also difficulty of processing for compressor application
The problems such as greatly, cost is high, machining accuracy is difficult to ensure that.Therefore, need badly one not only improve control cost again be conducive to improve from
The novel diffuser structure of heart Capability of Compressor.
Summary of the invention
It is an object of the invention to provide a kind of control cost that not only improves to be conducive to again improving centrifugal compressor performance
Novel diffuser structure, and provide formative method.
For achieving the above object, a kind of have the centrifugal compressor vane diffuser of trailing edge structures before swallow-tail form, including
Axially diffuser vane, diffuser wheel disc, diffuser wheel cap, diffuser attachment bolt, radial diffuser blade, described radial direction expands
Depressor blade and axially diffuser vane are circumferentially evenly distributed between diffuser wheel disc and diffuser wheel cap, described footpath
Having swallow-tail form leading edge and swallow-tail form trailing edge structures to diffuser vane, its formative method is:
1) based on conventional leaf diffuser, scan along diffuser vane end wall profile scanning moulding conic section,
Then carry out boolean's subtraction with tradition diffuser body, obtain having the centrifugal of swallow-tail form leading edge and swallow-tail form trailing edge structures
Gas compressor blade chip diffuser；
2) end points of above-mentioned scanning moulding conic section is respectively the friendship of diffuser vane leading edge and root of blade cross section
Point, blade inlet edge and the intersection point in blade tip cross section, scan moulding conic section place plane and be perpendicular to the pressure of diffuser
Face, curve is towards blade suction surface lateral bend.
Further, described diffuser is arranged on centrifugal compressor flow outlet portion, and radial diffuser inlet radius
The ratio of R3 and centrifugal impeller exit radius R2 is 1.03-1.1.
Further, the cross-sectional area of described diffuser expanding channel can be by change conic section shape with for moulding
Conventional leaf diffuser key groove θ obtain, thus adjust diffuser import and export area ratio.
Further, the described conventional leaf diffuser key groove θ for moulding is not less than 8 °.
Further, described diffuser vane scribbles anti-scaling anti-corrosive coating, be effectively reduced diffuser vane dirty tight
Weight problem, overcomes the surge problems causing compressor to produce because the ventilation area of dirty generation diminishes.
Further, the anti-scaling anti-corrosive coating described diffuser vane scribbled is to use containing of HVOF spraying coating process spraying
There is the aluminum oxide ceramic composite coating of 1%Ti nanoparticle, the anti-scaling anti-corrosive Wear vesistance of blade can be improved.
It is an advantage of the current invention that: the described blade diffuser with swallow-tail form leading edge and trailing edge structures, at a high speed
Well adapting to property of air-flow, scale prevention coating is effectively reduced the generation of dirty, keeps enough ventilation area, reduces stream
Kinetic force of friction, thus reduce the surge problems of compressor, improve the security performance of compressor；And moulding of the present invention is convenient, cost
Low, processing is simple, safety is good, and can increase substantially centrifugal compressor efficiency and steady operation nargin, in being particularly well-suited to
Small aero high pressure ratio centrifugal compressor.
Accompanying drawing explanation
Fig. 1 is to have the structural representation of trailing edge structures blade diffuser before swallow-tail form；
Fig. 2 a and conventional wedge diffuser parameter that Fig. 2 b is the present invention and diffuser schematic three dimensional views；
Fig. 3 is the formative method structural parameters schematic diagram of the present invention；
Fig. 4 be the present invention there is the schematic three dimensional views of trailing edge structures blade diffuser before swallow-tail form；
Wherein, the axial diffuser vane of 1-；2-diffuser wheel disc；3-diffuser wheel cap；4-diffuser attachment bolt；
5-radial diffuser blade；6-swallow-tail form leading edge；7-swallow-tail form trailing edge；8-scans moulding conic section；9-tradition diffusion
Device leading edge；10-diffuser suction surface；11-diffuser pressure face；12-diffuser vane end wall profile；13-conventional wedge diffusion
Device blade.
Detailed description of the invention
Hereinafter, in conjunction with accompanying drawing 1～4 and embodiment, the detailed description of the invention of the present invention is described in detail:
As Fig. 1 illustrates that the present invention's has the embodiment of trailing edge structures blade diffuser before swallow-tail form, including diffuser
Wheel disc 2, diffuser wheel cap 3 and built-in some radial diffuser blades 5 and axially diffuser vane 1, diffuser attachment bolt 4
Being fixed between diffuser wheel disc 2 and diffuser wheel cap 3 by radial diffuser blade 5, this embodiment is applicable to high pressure ratio and is centrifuged
Compressor.Described radial diffuser blade 5 has swallow-tail form leading edge 6 and swallow-tail form trailing edge 7, is based on conventional leaf diffusion
The creative transformation of device blade 13.Scribbling anti-scaling anti-corrosive coating on described radial diffuser blade 5, described anti-scaling anti-corrosive is coated with
Layer is the aluminum oxide ceramic composite coating containing 1%Ti nanoparticle using the spraying of HVOF spraying coating process, improves blade
Anti-scaling anti-corrosive Wear vesistance, be effectively reduced diffuser vane dirty serious problems, overcome because of dirty produce air circulation
The surge problems that area diminishes and causes compressor to produce.
As Fig. 2 a and Fig. 2 b illustrates conventional wedge diffuser vane 13 modeling parameters and diffuser schematic three dimensional views, R3 and R4
Being respectively diffuser to import and export, θ is blade shape construction key groove, and α is geometry flow inlet angle；Wherein, radial diffuser inlet radius R3
Being 1.03-1.1 with the ratio of centrifugal impeller exit radius R2, key groove θ is not less than 8 °.
Described radial diffuser blade 5, its formative method is:
(1) based on conventional leaf diffuser 13, with certain scanning moulding with conic section 8 along diffuser vane end wall profile
12 scan, and then carry out boolean's subtraction with conventional leaf diffuser 13 body, are not only had swallow-tail form leading edge 6 but also have
There is the centrifugal compressor vane diffuser 5 of swallow-tail form trailing edge 7 structure；
(2) end points of above-mentioned scanning moulding conic section 8 is respectively diffuser vane leading edge 9 and root of blade cross section
Intersection point, blade inlet edge 9 and the intersection point in blade tip cross section, scan moulding conic section 8 place plane and be perpendicular to diffuser
Pressure face 11, scans moulding with conic section 8 towards blade suction surface 10 lateral bend, as shown in Figure 3 and Figure 4.
The present invention is not limited to above-mentioned embodiment, in the case of without departing substantially from the flesh and blood of the present invention, and this area skill
Art personnel it is conceivable that any deformation, improve, replace and each fall within the scope of the present invention.
Claims (6)
1. one kind has the centrifugal compressor vane diffuser of trailing edge structures before swallow-tail form, it is characterised in that include axially expanding
Depressor blade (1), diffuser wheel disc (2), diffuser wheel cap (3), diffuser attachment bolt (4), radial diffuser blade (5),
Described radial diffuser blade (5) and axial diffuser vane (1) are circumferentially evenly distributed in diffuser wheel disc (2) and diffusion
Between device wheel cap (3), described radial diffuser blade (5) has swallow-tail form leading edge (6) and swallow-tail form trailing edge (7) structure, its
Formative method is:
1) based on conventional leaf diffuser (13), to scan moulding conic section (8) along diffuser vane end wall profile
(12) scan, then carry out boolean's subtraction with tradition diffuser body (13), obtain that there is swallow-tail form leading edge (6) and dovetail
The centrifugal compressor vane diffuser of shape trailing edge (7) structure；
2) end points of above-mentioned scanning moulding conic section (8) is respectively diffuser vane leading edge (9) and root of blade cross section
Intersection point, blade inlet edge (9) and the intersection point in blade tip cross section, scan moulding conic section (8) place plane and be perpendicular to diffusion
The pressure face (11) of device, curve is towards blade suction surface (10) lateral bend.
A kind of have the centrifugal compressor vane diffuser of trailing edge structures before swallow-tail form, and it is special
Levying and be, described diffuser is arranged on centrifugal compressor flow outlet portion, and radial diffuser inlet radius R3 and centrifugal leaf
The ratio of wheel exit radius R2 is 1.03-1.1.
A kind of have the centrifugal compressor vane diffuser of trailing edge structures before swallow-tail form, and it is special
Levying and be, the cross-sectional area of described diffuser expanding channel can be by change conic section (8) shape and the tradition being used for moulding
Blade diffuser (13) key groove θ obtains.
A kind of have the centrifugal compressor vane diffuser of trailing edge structures before swallow-tail form, and it is special
Levying and be, described conventional leaf diffuser (13) the key groove θ for moulding is not less than 8 °.
A kind of have the centrifugal compressor vane diffuser of trailing edge structures before swallow-tail form, and it is special
Levy and be, described radial diffuser blade (5) scribbles anti-scaling anti-corrosive coating.
A kind of have the centrifugal compressor vane diffuser of trailing edge structures before swallow-tail form, and it is special
Levying and be, the anti-scaling anti-corrosive coating that described radial diffuser blade (5) scribbles is to use containing of HVOF spraying coating process spraying
The aluminum oxide ceramic composite coating of 1%Ti nanoparticle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610608677.2A CN106089808B (en) | 2016-07-28 | 2016-07-28 | A kind of blade diffuser and its formative method with trailing edge structures before swallow-tail form |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610608677.2A CN106089808B (en) | 2016-07-28 | 2016-07-28 | A kind of blade diffuser and its formative method with trailing edge structures before swallow-tail form |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106089808A true CN106089808A (en) | 2016-11-09 |
| CN106089808B CN106089808B (en) | 2018-11-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610608677.2A Expired - Fee Related CN106089808B (en) | 2016-07-28 | 2016-07-28 | A kind of blade diffuser and its formative method with trailing edge structures before swallow-tail form |
Country Status (1)
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| CN (1) | CN106089808B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112355571A (en) * | 2020-09-22 | 2021-02-12 | 苏州润凯机械有限公司 | Processing method of corrosion-resistant diffuser |
| CN112377268A (en) * | 2020-11-13 | 2021-02-19 | 中国航发湖南动力机械研究所 | Integrated diffuser for additive manufacturing |
| CN112901557A (en) * | 2020-12-30 | 2021-06-04 | 中南大学 | Diffuser with semi-bladeless area having self-adaptive curvature profile |
| CN113094833A (en) * | 2021-04-09 | 2021-07-09 | 中国科学院工程热物理研究所 | Method for designing diffuser with dovetail leading edge and integrated radial and axial blades |
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| CN103628018A (en) * | 2012-08-24 | 2014-03-12 | 西门子公司 | High speed oxygen fuel spraying system and metal ceramic coating prepared by the same |
| CN203500120U (en) * | 2013-09-27 | 2014-03-26 | 沈阳透平机械股份有限公司 | Centrifugal compressor diffuser blade structure |
| CN103742450A (en) * | 2013-12-22 | 2014-04-23 | 中国科学院工程热物理研究所 | Vane type diffuser with horseshoe-shaped diffuser channels |
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- 2016-07-28 CN CN201610608677.2A patent/CN106089808B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN1776025A (en) * | 2005-11-23 | 2006-05-24 | 邹志尚 | Hard composibe nlano ceramic film cladding for use on surface of turbine blade |
| EP2623794A1 (en) * | 2009-07-19 | 2013-08-07 | Cameron International Corporation | Centrifugal compressor diffuser |
| CN103635699A (en) * | 2011-12-08 | 2014-03-12 | 三菱重工业株式会社 | Centrifugal fluid machine |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112355571A (en) * | 2020-09-22 | 2021-02-12 | 苏州润凯机械有限公司 | Processing method of corrosion-resistant diffuser |
| CN112377268A (en) * | 2020-11-13 | 2021-02-19 | 中国航发湖南动力机械研究所 | Integrated diffuser for additive manufacturing |
| CN112901557A (en) * | 2020-12-30 | 2021-06-04 | 中南大学 | Diffuser with semi-bladeless area having self-adaptive curvature profile |
| CN112901557B (en) * | 2020-12-30 | 2021-12-03 | 中南大学 | Diffuser with semi-bladeless area having self-adaptive curvature profile |
| CN113094833A (en) * | 2021-04-09 | 2021-07-09 | 中国科学院工程热物理研究所 | Method for designing diffuser with dovetail leading edge and integrated radial and axial blades |
| CN113094833B (en) * | 2021-04-09 | 2023-11-14 | 中国科学院工程热物理研究所 | Diffuser design method with dovetail leading edge and radial and axial blade integration |
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| Publication number | Publication date |
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| CN106089808B (en) | 2018-11-16 |
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