CN115899760A - Method for matching blade layout and nozzle of blade type radial swirler - Google Patents
Method for matching blade layout and nozzle of blade type radial swirler Download PDFInfo
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- CN115899760A CN115899760A CN202211062699.5A CN202211062699A CN115899760A CN 115899760 A CN115899760 A CN 115899760A CN 202211062699 A CN202211062699 A CN 202211062699A CN 115899760 A CN115899760 A CN 115899760A
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- 238000000034 method Methods 0.000 title claims abstract description 29
- 238000002485 combustion reaction Methods 0.000 claims abstract description 15
- 230000008021 deposition Effects 0.000 claims abstract description 6
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 5
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 5
- 239000003595 mist Substances 0.000 claims description 28
- 238000009434 installation Methods 0.000 claims description 7
- 229910052793 cadmium Inorganic materials 0.000 claims description 2
- BDOSMKKIYDKNTQ-UHFFFAOYSA-N cadmium atom Chemical compound [Cd] BDOSMKKIYDKNTQ-UHFFFAOYSA-N 0.000 claims description 2
- 238000011144 upstream manufacturing Methods 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 2
- 230000008520 organization Effects 0.000 abstract description 2
- 230000008569 process Effects 0.000 description 4
- 238000005457 optimization Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000004071 soot Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Abstract
The invention discloses a method for matching the vane layout and a nozzle of a vane type radial swirler, belongs to the technical field of aero-engines and gas turbines, and at least partially solves the technical problem of low design efficiency in the prior art. Determining the effective flow area ACds of the radial swirler according to the aerodynamic design value of the engine combustion chamber; the relationship among the effective flow area ACds, the width B of the blades of the swirler, the number n of the blades and the minimum throat spacing S of the blades satisfies the following conditions: ACd s ＝n*B*S*Cd s Wherein: cd _ s is the air flow coefficient of the radial swirler; the distance L between the nozzle and the throat of the Venturi tube of the vane type radial swirler and the diameter D of the throat meet the design criteria of carbon deposition of the Venturi tube and the nozzle so as to match the layout of the vanes with the position of the nozzle, and the vane type radial swirler can realize good effect after matching the relationship with the nozzleLight-off performance and organization of combustion.
Description
Technical Field
The invention belongs to the technical field of aero-engines and gas turbines, and relates to a vane layout of a vane type radial swirler and a method for matching the vane layout with a nozzle.
Background
The radial swirler is a head device for a backflow area generated by a main combustion chamber of a common aero-engine, wherein the blade layout of the blade radial swirler does not form a uniform method at present, the blade layout is generally performed by given blade characteristic parameters, but for an optimization iteration process brought by characteristic parameter changes, the optimization iteration process is often adjusted by a CAD drawing mode, great effort and time cost are consumed, and parametric design cannot be carried out.
Disclosure of Invention
The present invention provides a method for matching vane layout with nozzle of vane radial swirler, which at least partially solves the technical problem of low design efficiency in the prior art.
A method of vane radial swirler vane layout to nozzle matching is provided, the method comprising:
determining the effective flow area ACds of the radial swirler according to the aerodynamic design value of the engine combustion chamber;
the relationship among the effective flow area ACds, the width B of the blades of the swirler, the number n of the blades and the minimum throat spacing S of the blades satisfies the following conditions: ACd s ＝n*B*S*Cd s Wherein: cd [ Cd ] s Is the air flow coefficient of the radial swirler;
the distance L between the nozzle and the blade type radial swirler Venturi throat and the diameter D of the throat meet the Venturi and nozzle carbon deposition design criteria so as to match the layout of the blades with the position of the nozzle.
In a preferred or alternative embodiment, each blade is mounted in the same manner and the method of determining the minimum throat spacing S of the blades comprises:
obtaining a blade installation angle gamma (an included angle with the vertical direction), a blade thickness t and a radial swirler inner diameter circle radius r;
determining the relationship between the minimum throat spacing S of the blades and the mounting angle gamma of the blades, the thickness t of the blades and the radius r of the inner diameter circle of the radial swirler according to the geometric principle and meeting the following requirements:
S＝2rsinα/2sin(90°+(α+β)/2-γ)。
the invention has the technical beneficial effects that:
in the process of arranging the vanes of the swirler, characteristic parameters such as the width B of the swirler, the minimum throat interval S, the mounting angle gamma of the vanes, the diameter of an inner diameter circle of the swirler and the like are required to be iterated frequently according to the requirement of the effective flow area of the swirler.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the drawings needed to be used in the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present disclosure, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic view of a vane type radial swirler vane layout and its nozzle matching;
FIG. 2 is a partial enlarged view of a vane layout of a vane-type radial swirler;
wherein:
11-nozzle, 12-first stage vane radial swirler, 13-second stage vane radial swirler, 14-head transition section, 15-venturi tube, 16-venturi tube throat section, 17-first stage vane radial swirler air, 18-limit oil mist cone, 19-actual oil mist cone, 20-design oil mist cone, 21-first stage vane radial swirler vane, 22-first stage vane radial swirler flow channel, 23-vane center line, 24-vane minimum throat section, 25-first stage vane radial swirler inside diameter radius of circle, 26-first stage vane radial swirler inside diameter.
Detailed Description
The embodiments of the present disclosure are described in detail below with reference to the accompanying drawings.
The embodiments of the present disclosure are described below with specific examples, and other advantages and effects of the present disclosure will be readily apparent to those skilled in the art from the disclosure in the specification. It is to be understood that the described embodiments are merely illustrative of some, and not restrictive, of the embodiments of the disclosure. The disclosure may be embodied or carried out in various other specific embodiments, and various modifications and changes may be made in the details within the description without departing from the spirit of the disclosure. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments, which can be derived by a person skilled in the art from the embodiments disclosed herein without making any creative effort, shall fall within the protection scope of the present disclosure.
It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the disclosure, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. Additionally, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
The invention provides a method for matching the vane layout and a nozzle of a vane type radial swirler, which comprises the following steps:
determining the effective flow area ACds of the radial swirler according to the aerodynamic design value of the engine combustion chamber;
the relationship between the effective flow area ACds, the width B of the blades of the swirler, the number n of the blades and the minimum throat spacing S of the blades satisfies the following conditions: ACd s ＝n*B*S*Cd s Wherein: cd (cadmium-doped cadmium) s Is the air flow coefficient of the radial swirler;
the distance L between the nozzle and the blade type radial swirler Venturi throat and the diameter D of the throat meet the Venturi and nozzle carbon deposition design criteria so as to match the layout of the blades with the position of the nozzle.
The effective flow area ACds is taken as a technical basis, and the relation between the effective flow area ACds and the width B of the blades of the swirler, the number n of the blades and the minimum throat interval S of the blades is determined, so that repeated iteration drawing is needed in the CAD drawing process.
Furthermore, the matching relation between the venturi tube of the vane type radial swirler and the nozzle is determined according to the relation between the axial speed of the vanes and the spraying speed of the oil mist cone and the comprehensive relation between the expansion angles of the venturi tube. Good flameout performance and organization of combustion can be realized after the vane type radial swirler is matched with the nozzle.
Specifically, 1) determining the minimum throat spacing S of the blades, wherein the installation mode of each blade is the same, and obtaining a blade installation angle gamma (an included angle with the vertical direction), a blade thickness t and an inner diameter circular radius r of the radial swirler; determining the relationship between the minimum throat spacing S of the blades and the mounting angle gamma of the blades, the thickness t of the blades and the radius r of the inner diameter circle of the radial swirler according to the geometric principle and meeting the following requirements:
further, the method also comprises the following steps: determining a nozzle design oil mist taper angle psi and a limit oil mist taper angle phi according to design requirements, wherein the nozzle oil mist taper angle psi is matched with the flow velocity of upstream incoming air;
satisfies the following conditions: the actual oil mist cone angle ω is between the design oil mist cone angle ψ and the limit oil mist cone angle Φ, and at an intermediate position between the design oil mist cone angle ψ and the limit oil mist cone angle Φ.
2) The method for setting the blade mounting angle gamma comprises the following steps:
acquiring a design value of the main combustion chamber tissue combustion, and correspondingly selecting or matching the swirl strength of the blades according to the design value;
the rotational flow strength determines the blade installation angle gamma (the included angle with the vertical direction) according to a rotational flow strength formula.
As a specific embodiment provided by the scheme, the engine comprises a main combustion chamber, and the thickness value of the swirler vane is selected between 0.8 mm and 1.5 mm.
As a specific embodiment provided by the present disclosure, a characteristic angle β corresponding to a chord length of each blade root of adjacent blades, and a radian corresponding to a distance between adjacent blades is α, both of which are satisfied according to a geometric triangle matching relationship:
α =360/n- β, the characteristic angle β is matched according to a geometric triangle to obtain a relation with the blade thickness t, the swirler inner diameter circle radius r and the blade installation angle γ, and the relation satisfies:
Examples
Aiming at the vane type radial swirler, the thickness of the vane is t, and the included angle between the vane and the vertical direction is gamma. The radius of the inner diameter circle of the vane type radial swirler is r; the blade center line 23 and the blade radial swirler inner diameter circle 26 intersect at A, B two points, and the chord length AB corresponding to the thickness is obtained through calculation according to the blade thickness;
AB＝L t ＝t/cos(γ)；
the radian corresponding to the chord length AB is as follows:
thus, the arc length corresponding to the chord length AB
Is composed of
The vane type radial swirler has N vanes, the vane central line (23) and the vane type radial swirler inner diameter circle (26) are intersected at N points, and then the arc lengths of the two vanes (21)
In order to realize the purpose of the method,
due to the arc length
So->
Thus the arc length can be obtained
Arc length
The corresponding radian is
Therefore, the corresponding chord length PA is,
obtaining an included angle lambda between the blade (21) and the inner diameter circle (26) according to the geometrical relation:
λ = τ has been demonstrated, and therefore the angle θ between the chord length PA and the blade (21) can be obtained:
and finally, obtaining the minimum throat interval S of the blade according to the trigonometric function relationship:
wherein, the relation between the characteristic angle α and β can also be obtained according to geometric triangle matching:
in addition, the actual oil mist cone 19 is estimated according to the air flow speed Va of the first-stage blade type radial swirler air 17 and the injection speed Vf of the designed oil mist cone 20 of the nozzle 11;
according to the design experience of point flameout and tissue combustion, the actual oil mist cone 19 is ensured to be between the design oil mist cone 20 and the limit oil mist cone 18, namely the oil mist cone angle phi < the oil mist cone angle omega < the oil mist cone angle psi, and omega ≈ 2 (phi + psi) is ensured as much as possible.
The relationship between the length L of the nozzle 11 and the venturi throat section 16 and the venturi throat diameter D is ensured to be within a reasonable range, depending on the soot deposition requirements of the nozzle 11, the venturi 15.
In summary, the present invention provides a vane layout of vane type radial swirler and a method for matching the vane layout with a nozzle, which can quickly and accurately complete the vane layout of vane type radial swirler and the matching between the nozzle and the swirler, and is only a specific embodiment of the present disclosure, but the scope of the present disclosure is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present disclosure should be covered within the scope of the present disclosure. Therefore, the protection scope of the present disclosure shall be subject to the protection scope of the claims.
Claims (7)
1. A method of vane radial swirler vane layout to nozzle matching, the method comprising:
determining the effective flow area ACds of the radial swirler according to the aerodynamic design value of the engine combustion chamber;
the relationship among the effective flow area ACds, the width B of the blades of the swirler, the number n of the blades and the minimum throat spacing S of the blades satisfies the following conditions: ACd s ＝n*B*S*Cd s Wherein: cd (cadmium-doped cadmium) s Is the air flow coefficient of the radial swirler;
the distance L between the nozzle and the blade type radial swirler Venturi throat and the diameter D of the throat meet the Venturi and nozzle carbon deposition design criteria so as to match the layout of the blades with the position of the nozzle.
2. A method according to claim 1, wherein each blade is mounted in the same manner and the method of determining the minimum throat spacing S of the blades comprises:
obtaining a blade installation angle gamma, a blade thickness t and a radial swirler inner diameter circle radius r;
determining the relationship between the minimum throat spacing S of the blades and the mounting angle gamma of the blades, the thickness t of the blades and the radius r of the inner diameter circle of the radial swirler according to the geometric principle and meeting the following requirements:
3. the method of claim 2, the nozzle being mounted in a combustion chamber of an engine, further comprising:
determining a nozzle design oil mist taper angle psi and a limit oil mist taper angle phi according to design requirements, wherein the nozzle oil mist taper angle psi is matched with the flow velocity of upstream incoming air;
satisfies the following conditions: the actual oil mist cone angle omega is between the design oil mist cone angle psi and the limit oil mist cone angle phi, and is at an intermediate position between the design oil mist cone angle psi and the limit oil mist cone angle phi.
4. The method of claim 2, wherein determining the blade setting angle γ comprises:
acquiring a design value of the main combustion chamber tissue combustion, and correspondingly selecting or matching the swirl strength of the blades according to the design value;
and determining the blade mounting angle gamma according to the swirl strength formula by using the swirl strength.
5. The method of claim 1, the engine including a main combustion chamber, wherein the swirler vane thickness value is selected between 0.8 mm and 1.5 mm.
6. The method according to claim 2, wherein a characteristic angle β corresponding to a chord length formed by each blade of adjacent blades and an inner diameter circle of the radial swirler, and a radian corresponding to a distance between adjacent blades is α satisfy both of the following requirements according to a geometric triangle matching relationship:
α＝360/n-β。
7. the method according to claim 2, wherein the characteristic angle β is matched according to a geometric triangle to obtain a relation between the blade thickness t, the swirler inner diameter circle radius r and the blade installation angle γ, and satisfies:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211062699.5A CN115899760A (en) | 2022-08-31 | 2022-08-31 | Method for matching blade layout and nozzle of blade type radial swirler |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211062699.5A CN115899760A (en) | 2022-08-31 | 2022-08-31 | Method for matching blade layout and nozzle of blade type radial swirler |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2728261A1 (en) * | 2012-11-06 | 2014-05-07 | Alstom Technology Ltd | Axial swirler |
| CN113757724A (en) * | 2021-08-30 | 2021-12-07 | 上海和兰透平动力技术有限公司 | Flow guiding type rotational flow atomizing nozzle |
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2022
- 2022-08-31 CN CN202211062699.5A patent/CN115899760A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2728261A1 (en) * | 2012-11-06 | 2014-05-07 | Alstom Technology Ltd | Axial swirler |
| CN113757724A (en) * | 2021-08-30 | 2021-12-07 | 上海和兰透平动力技术有限公司 | Flow guiding type rotational flow atomizing nozzle |
Non-Patent Citations (2)
| Title |
|---|
| A.H.勒菲沃 等: "《燃气涡轮发动机燃烧》", vol. 3, 30 June 2016, 航天工业出版社, pages: 119 * |
| 林宇震 等: "《燃气轮机燃烧室》", vol. 1, 31 May 2008, 国防工业出版社, pages: 42 - 47 * |
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