CN108386389A - A kind of centrifugal compressor diffuser structure that blade is blended with casing and wheel hub - Google Patents

A kind of centrifugal compressor diffuser structure that blade is blended with casing and wheel hub Download PDF

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Publication number
CN108386389A
CN108386389A CN201810128459.8A CN201810128459A CN108386389A CN 108386389 A CN108386389 A CN 108386389A CN 201810128459 A CN201810128459 A CN 201810128459A CN 108386389 A CN108386389 A CN 108386389A
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China
Prior art keywords
diffuser
blade
gas channel
radial
axial
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CN201810128459.8A
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Chinese (zh)
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CN108386389B (en
Inventor
韩戈
龚建波
郭磊
胡春艳
穆勇
卢新根
徐纲
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Institute of Engineering Thermophysics of CAS
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Institute of Engineering Thermophysics of CAS
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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/40Casings; Connections of working fluid
    • F04D29/42Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44Fluid-guiding means, e.g. diffusers
    • F04D29/441Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F04D29/444Bladed diffusers
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/08Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
    • F02C3/085Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage the turbine being of the radial-flow type (radial-radial)
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/40Casings; Connections of working fluid
    • F04D29/42Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44Fluid-guiding means, e.g. diffusers
    • F04D29/46Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/462Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
    • F04D29/464Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps adjusting flow cross-section, otherwise than by using adjustable stator blades

Abstract

The invention discloses the centrifugal compressor diffuser structures that a kind of blade and casing and wheel hub blend, belong to Small Aeroengine compressor technical field, its key is to reduce loss by the way that radial diffuser is connected with axial diffuser and leading edge is designed as sharp edge, reduce diffuser outer diameter, and further blend blade and diffuser casing and wheel hub to reduce the degreeof tortuosity of diffuser vane, facilitate blade design and processing.The invention may be directly applied to small aero, can reduce engine outer diameter under the premise of not increasing processing cost and not reducing Capability of Compressor, improve engine thrust-weight ratio.

Description

A kind of centrifugal compressor diffuser structure that blade is blended with casing and wheel hub
Technical field
The invention belongs to Small Aeroengine compressor technical fields, are related to a kind of centrifugal compressor diffuser knot The centrifugal compressor diffuser structure that structure more particularly to a kind of blade are blended with casing and wheel hub, can be in diffuser intake Reduce diffuser maximum outside diameter under conditions of diameter is constant, while reducing the distortion journey of diffuser blade pressure face and suction surface Degree, especially suitable for Small Aeroengine high pressure ratio centrifugal compressor.
Background technology
Centrifugal compressor is due to single-stage pressure ratio is high, working range is wide, simple in structure, high reliability is small-sized It is widely used in gas turbine and Small Aeroengine.With the raising of centrifugal compressor pressure ratio, leaf is centrifuged It takes turns exit flow degree of irregularity to improve, and air velocity also increases, and radial diffuser inflow Mach number is made to reach Gao Ya Sound even Supersonic, forms shock wave in diffuser intake or channel, influences the performance of centrifugal compressor.Start simultaneously in order to reduce The front face area of machine, improve engine thrust-weight ratio, need the radial dimension for reducing engine to the maximum extent, with engine outside The length of the reduction of diameter, centrifugal compressor radial diffuser reduces, and the diffusion load of diffuser sharply increases, makes in blade path Runner separation easily occurs, causes diffuser internal loss to increase, keeps diffuser Design more difficult.
In the prior art, by the way that radial diffuser and axial diffuser are made of one structure (such as CN201410453415.4, CN200810196137.3 etc.), to reduce turnaround section between radial diffuser and axial diffuser Mixing loss is conducive to the maximum outside diameter for reducing diffuser under the premise of compressor characteristics are constant, but integrated diffusion Device blade from it is radial go to axial direction during simultaneously can also from pressure towards suction surface deflection, diffuser radial height compared with Hour, diffuser vane distortion can be made more serious, diffuser vane design, moulding and processing is caused all to there is larger difficulty.
Invention content
For the disadvantages mentioned above and deficiency of the prior art, the present invention is intended to provide a kind of blade is blended with casing and wheel hub Centrifugal compressor diffuser structure, complete to expand by blending the casing and wheel hub of diffuser vane and diffuser runner The moulding of depressor blade both ensure that reduction diffuser maximum outside diameter under conditions of diffuser intake diameter is constant, while can Effectively reduce degreeof tortuosity of the diffuser vane under smaller radial direction to axial turning radius.
The present invention is that technical solution used by realizing its technical purpose is:
A kind of centrifugal compressor diffuser structure that blade is blended with casing and wheel hub, including diffuser disk and one It is formed in the diffuser disk circumferential edge part and equally distributed multiple diffuser vanes, adjacent two diffuser vane Between space be formed as diffuser gas channel, each diffuser vane includes being formed in the diffuser side surface Radial blade section and the axial blade section being formed on diffuser disk edge, each diffuser gas channel includes diameter To diffuser gas channel section and axial diffuser gas channel section, which is characterized in that
The diffuser vane includes being formed in the diffuser leading edge of radial blade section front end and being formed in described The diffuser trailing edge of axial blade section tail end,
The blade pressure surface of the radial blade section is from the diffuser leading edge under the diffuser gas channel Trip development is gradually converted into the wheel hub of the axial diffuser gas channel section,
The blade suction surface of the radial blade section is from the diffuser leading edge under the diffuser gas channel Trip development is gradually converted into a part for the casing of the axial diffuser gas channel section,
Wheel hub positioned at the radial diffuser gas channel section is along the diffuser gas channel downstream, gradually It is changed into the blade suction surface of the axial blade section,
Casing positioned at the radial diffuser gas channel section is along the diffuser gas channel downstream, in institute State axial diffuser gas channel section with by the radial blade section blade suction surface change Lai casing part collectively constitute The casing of the axial direction diffuser gas channel section,
From the blade pressure surface intersection weight of the casing and the radial blade section of the radial diffuser gas channel section A newly-generated curved surface, the curved surface are gradually increased along the diffuser gas channel downstream, width by zero, are formed as institute State the pressure face of axial blade section.
Further, the blade pressure surface with blade suction surface of the radial blade section phase at the diffuser leading edge It hands over, is formed as the diffuser leading edge of a sharp edge form, to adapt to High Mach number incoming.
Further, blade pressure surface and the radial diffusion of the curved surface regenerated in the radial blade section The casing intersection width of device gas channel section is zero, and as its downstream constantly reverses, and its width gradually increases, shape As the pressure face of the axial blade section.
Further, the throat section shape at the radial diffuser gas channel section is quadrangle.
Further, the cross sectional shape of the radial diffuser gas channel section and axial diffuser gas channel section is five Side shape.
Further, the diffuser vane number is between 10 to 35.
Further, the diffuser maximum outside diameter and the diffuser intake diameter ratio preferentially 1.3 or less selection.
Compared with existing blade diffuser, centrifugal compressor diffusion that blade of the invention and casing and wheel hub blend Device structure has significant technique effect:(1) radial diffuser blade and axial diffuser vane are linked to be one by diffuser vane Body is beneficial to reduce the mixing loss in diffuser passage, can be further decreased under the premise of compressor total losses is constant Diffuser outer diameter;(2) the sharp leading edge formed in diffuser leading edge by the blade pressure surface of radial blade section and blade suction surface It can better adapt to High Mach number incoming;(3) by the structure for blending diffuser vane and casing and wheel hub, both ensured Reduce diffuser maximum outside diameter under conditions of diffuser intake diameter is constant, at the same can effectively reduce diffuser vane compared with Degreeof tortuosity under small radial direction to axial turning radius, is easy to blade design and processing, may be directly applied to middle-size and small-size aviation Engine centrifugal formula compressor can reduce under the premise of not increasing processing cost and not reducing Capability of Compressor outside engine Diameter improves engine thrust-weight ratio.
Description of the drawings
Fig. 1 is the blade of the present invention and the centrifugal compressor diffuser front view that casing and wheel hub blend;
Fig. 2 is the rearview of the diffuser structure of the present invention;
Fig. 3 is the 3-D view of the diffuser structure of the present invention;
Fig. 4 is another 3-D view of the diffuser structure of the present invention;
Fig. 5 is the meridian plane view of the diffuser structure of the present invention.
Specific implementation mode
With reference to embodiment, the present invention is described in further detail, and following embodiment is explanation of the invention, And the invention is not limited in following embodiments.
As shown in Figures 1 to 5, the centrifugal compressor diffuser structure that blade of the invention is blended with casing and wheel hub, Including diffuser ontology 1, diffuser ontology 1 is made of diffuser vane and diffuser disk, diffuser vane number 10 to 35 it Between, when processing, can complete the processing of diffuser vane by milling out diffuser gas channel 9 on diffuser disk.Multiple diffusions Device blade is integrally formed and is evenly distributed on the diffuser disk circumferential edge part, the space between adjacent two diffuser vane Be formed as diffuser gas channel 9, each diffuser vane includes the radial blade section and shape being formed in diffuser side surface At the axial blade section on diffuser disk edge, each diffuser gas channel 9 includes radial diffuser gas channel section and axis To diffuser gas channel section, diffuser vane channel 9 directly goes to axial direction from radial.Diffuser vane includes being formed in radial direction The diffuser leading edge 5 of blade sections front end and the diffuser trailing edge 8 for being formed in axial blade section tail end.Close to diffuser leading edge 5 The blade pressure surface 6 at place intersects with the blade suction surface 2 at diffuser leading edge 5 in diffuser vane edge, forms one Sharp edge 5, the i.e. leading edge 5 of diffuser vane.
The integral blade of diffuser completes blade shape construction by blending pressure face, suction surface, casing and wheel hub. Blade pressure surface 6 at diffuser leading edge is not re-used as the pressure of blade during to diffuser passage downstream development Face, but it is gradually converted into the wheel hub of diffuser passage.Blade suction surface 2 at the diffuser leading edge is under diffuser passage The suction surface of blade is not re-used as during trip development, but width is gradually reduced and is changed into one of diffuser casing yet Point.Curved surface 7 is zero in diffuser leading edge pressure face and casing intersection width, and with 7 downstream of curved surface, width is gradual Increase, forms the pressure face of diffuser passage latter half.Positioned at diffuser passage entrance wheel hub 3 along diffuser passage to Downstream development, is not re-used as the wheel hub of diffuser passage, is gradually changed into the suction surface of diffuser vane.At diffuser intake Casing develops backward along diffuser passage, the diffuser second half section with by diffuser leading edge suction surface change Lai part casing face 2 collectively constitute the casing of diffuser passage.By the curved surface 6 of fusion diffuser pressure face and wheel hub, fusion diffuser suction surface with The curved surface 2 of casing, the curved surface 7 for forming diffuser latter half pressure face, expands the curved surface 3 of fusion diffuser wheel hub and suction surface Depressor blade and blade top curved surface 4 and diffuser vane trailing edge plane 8 this six curved surfaces finally form diffuser vane, complete diffusion Device blade shape construction.For diffuser gas channel 9 in addition to throat section shape is quadrangle, the cross sectional shape of rest part is five sides Shape.
Since air-flow directly can be gone to axial direction by diffuser gas channel 9 from radial, reduce radial diffuser and axial direction Mixing loss between diffuser, therefore compared with conventional radial diffuser adds the diffusion system of axial diffuser, this diffusion Device can further reduce diffuser outer diameter, and diffuser load is made to increase, while can also reach identical as traditional diffuser Performance.This kind of diffuser leading edge 5 is sharp edge, can better adapt to High Mach number incoming.Since maximum outside diameter reduces so that Radius at diffuser trailing edge leaf top 10 reduces with the radius ratio at diffuser intake leading edge 5, and diffuser passage turning radius subtracts It is small, while diffuser vane will also be deflected from pressure towards suction surface, therefore the degreeof tortuosity of diffuser vane increases.The present invention In diffuser vane by the way that pressure face to be divided into the curved surface 6 of upstream and the curved surface 7 in downstream and is divided into suction surface The curved surface 2 of trip and the curved surface 3 in downstream, substantially reduce the degreeof tortuosity of diffuser vane, reduce design and difficulty of processing.
Furthermore, it is necessary to illustrate, only to diffuser blade pressure face and suction surface are divided into upstream in this specification It is described with two sections of downstream and the case where mutually being merged with casing and wheel hub, for by diffuser blade pressure face and suction Face is from upstream to downstream and divides equally applicable to the blade shape construction pattern of multistage, and the shape of its blade, named title etc. can be with It is different.The equivalent or simple change that all structure, feature and principles according to described in inventional idea of the present invention are done, is included in this hair In the protection domain of bright patent.Those skilled in the art can do described specific embodiment various The modify or supplement or adopt similar mode of various kinds substitutes, and without departing from structure of the invention or surmounts present claims Range defined in book, is within the scope of protection of the invention.

Claims (8)

1. the centrifugal compressor diffuser structure that a kind of blade is blended with casing and wheel hub, which is characterized in that including diffuser Disk and it is integrally formed in the diffuser disk circumferential edge part and equally distributed multiple diffuser vanes, described in adjacent two Space between diffuser vane is formed as diffuser gas channel, and each diffuser vane includes being formed in the diffuser Radial blade section in side surface and the axial blade section being formed on diffuser disk edge, each diffuser air-flow Channel includes radial diffuser gas channel section and axial diffuser gas channel section, and air-flow is directly gone to axial direction from radial, Reduce the mixing loss between radial diffuser and axial diffuser.
2. diffuser structure according to claim 1, which is characterized in that the diffuser vane includes being formed in the diameter To blade sections front end diffuser leading edge and be formed in the diffuser trailing edge of the axial blade section tail end,
The blade pressure surface of the radial blade section is sent out from the diffuser leading edge to the downstream of the diffuser gas channel Exhibition is gradually converted into the wheel hub of the axial diffuser gas channel section,
The blade suction surface of the radial blade section is sent out from the diffuser leading edge to the downstream of the diffuser gas channel Exhibition is gradually converted into a part for the casing of the axial diffuser gas channel section,
Wheel hub positioned at the radial diffuser gas channel section gradually changes along the diffuser gas channel downstream For the blade suction surface of the axial blade section,
Casing positioned at the radial diffuser gas channel section is along the diffuser gas channel downstream, in the axis To diffuser gas channel section with by the radial blade section blade suction surface transformation come casing part collectively constitute described in The casing of axial diffuser gas channel section,
It is given birth to again from the casing of the radial diffuser gas channel section and the blade pressure surface intersection of the radial blade section At a curved surface, which is gradually increased along the diffuser gas channel downstream, width by zero, is formed as the axis To the pressure face of blade sections.
3. according to the diffuser structure described in claim 1,2, which is characterized in that the blade pressure surface of the radial blade section with Blade suction surface intersects at the diffuser leading edge, is formed as the diffuser leading edge of a sharp edge form, to adapt to high Mach Number incoming.
4. according to the diffuser structure described in claim 1,2,3, which is characterized in that the curved surface regenerated is in the diameter It is zero to the blade pressure surface and the casing intersection width of the radial diffuser gas channel section of blade sections, downwards with it Trip development constantly torsion, and its width gradually increases, and is formed as the pressure face of the axial blade section.
5. the diffuser structure according to Claims 1-4, which is characterized in that at the radial diffuser gas channel section Throat section shape be quadrangle.
6. according to the diffuser structure described in claim 1 to 5, which is characterized in that the radial diffuser gas channel section and The cross sectional shape of axial diffuser gas channel section is pentagon.
7. according to the diffuser structure described in claim 1 to 6, which is characterized in that the diffuser vane number 10 to 35 it Between.
8. according to the diffuser structure described in claim 1 to 7, which is characterized in that the diffuser maximum outside diameter and the expansion Preferentially 1.3 or less the selection of the ratio between depressor inlet diameter.
CN201810128459.8A 2018-02-08 2018-02-08 Centrifugal compressor diffuser structure with blades, casing and hub fused Active CN108386389B (en)

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CN108386389B CN108386389B (en) 2020-03-24

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110005525A (en) * 2019-03-01 2019-07-12 南京航空航天大学 It is a kind of to go the compressor of whirl spraying mouth to subtract vortex structure with cascade-type
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
CN113756951A (en) * 2021-09-30 2021-12-07 大连理工大学 Shape-preserving diffuser with radial diffuser and axial diffuser fused

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101363452A (en) * 2008-09-16 2009-02-11 南京航空航天大学 Conformality passage type diffuser and three-dimensional design method thereof
CN201281045Y (en) * 2008-09-16 2009-07-29 南京航空航天大学 Conformal passage type diffuser
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
CN104343734A (en) * 2014-09-05 2015-02-11 北京动力机械研究所 Centrifugal compressor
CN104884810A (en) * 2012-11-06 2015-09-02 诺沃皮尼奥内股份有限公司 Centrifugal compressor with twisted return channel vane

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101363452A (en) * 2008-09-16 2009-02-11 南京航空航天大学 Conformality passage type diffuser and three-dimensional design method thereof
CN201281045Y (en) * 2008-09-16 2009-07-29 南京航空航天大学 Conformal passage type diffuser
CN104884810A (en) * 2012-11-06 2015-09-02 诺沃皮尼奥内股份有限公司 Centrifugal compressor with twisted return channel vane
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
CN104343734A (en) * 2014-09-05 2015-02-11 北京动力机械研究所 Centrifugal compressor

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110005525A (en) * 2019-03-01 2019-07-12 南京航空航天大学 It is a kind of to go the compressor of whirl spraying mouth to subtract vortex structure with cascade-type
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
CN113756951A (en) * 2021-09-30 2021-12-07 大连理工大学 Shape-preserving diffuser with radial diffuser and axial diffuser fused

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