CN101915130A - Three-dimensional nozzle ring vane of variable geometry turbocharger and design method thereof - Google Patents
Three-dimensional nozzle ring vane of variable geometry turbocharger and design method thereof Download PDFInfo
- Publication number
- CN101915130A CN101915130A CN2010102190445A CN201010219044A CN101915130A CN 101915130 A CN101915130 A CN 101915130A CN 2010102190445 A CN2010102190445 A CN 2010102190445A CN 201010219044 A CN201010219044 A CN 201010219044A CN 101915130 A CN101915130 A CN 101915130A
- Authority
- CN
- China
- Prior art keywords
- blade
- nozzle ring
- turbine
- vane
- nozzle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Abstract
The invention relates to a three-dimensional nozzle ring vane of a variable geometry turbocharger (VGT), comprising a pressure side, a suction side, a vane leading edge and a vane trailing edge, wherein the pressure side corresponds to the concave side of the vane profile; the suction side corresponds to the convex side of the vane profile; the molding lines of the pressure side and the suction side are quadratic curves or biquadratic curves and are not the same; the leading edges of the pressure side and the suction side form the leading edge of the vane; the molding line of the leading edge of the vane is a quadratic curve and forms the three-dimensional curve leading edge; the trailing edges of the pressure side and the suction side form the trailing edge of the vane; the molding line of the trailing edge of the vane is a quadratic curve, and the height molding line of the trailing edge is identical with the inlet molding line of the turbine vane and the molding line of the trailing edge forms the three-dimensional spatial curve sharp trail. The nozzle ring vane ensures the radial-flow turbine of the VGT to develop into the mixed flow turbine, thus improving the turbine efficiency. The invention also provides a design method of the three-dimensional nozzle ring vane, and the nozzle ring vane designed by the method has higher success rate and lower cost.
Description
Technical field
The invention belongs to the mechanical designing technique field, relate to three-dimensional nozzle blade of a kind of variable geometry turbocharger and design method thereof.
Background technique
Turbosupercharging is one of main direction of internal-combustion piston engine technical development, and turbosupercharger has become the indispensable parts of contemporary advanced Vehicular internal combustion engine.Internal-combustion engine adopts the variable nozzle ring turbosupercharger (VNT) of advanced variable geometry turbocharger (VGT), especially its principal mode can further improve performance, as improve fuel economy, reduce discharging, improve the Engine torque deposit, improve acceleration etc.Turbocharger vanes formula nozzle ring is divided into fixed and adjustable, and fixed nozzle ring is mainly used in the large-sized turbo-charging device of purposes such as boats and ships, generating.Be subjected to effects limit such as application space, structure, reliability, original vehicle turbocharger does not use the blade nozzle ring, along with improving constantly of vehicle motor thermal performance, emission request, among automobile-used variable nozzle ring turbocharger design and manufacturing technology, application market are developing rapidly.
Nozzle ring is the core component of VNT, and nozzle blade is the greatest factor of decision nozzle ring assembly property, and the shape of blade, work profile design nozzle ring, VNT turbine stage performance is had material impact.The design principle one of nozzle blade is that blade should satisfy the gas flow direction and change requirement, realizes gas flowing by the effect that radially promptly has control gaseous flow direction and cross-sectional flow area to axial conversion in nozzle ring; The 2nd, reduce the flow losses of gas in nozzle ring as far as possible, at first be the bump loss that reduces the blade inlet place, the flow angle α when just requiring blade inlet structure angle to enter nozzle blade with gas
2Equating, secondly is to reduce gas by the frictional loss in the conduit of two blade working profiles formation, is the bump loss that reduces the loss of blade exit tail and enter turbine wheel at last.
The working environment of VNT nozzle ring is similar to the turbine blade of aero gas turbine engine: work in high temperature, high pressure, high-speed fuel gas, but the former working conditions change is frequent, operating temperature is lower (maximum temperature is generally less than 1050 ℃ at present), and gas flow direction changes greatly, blade can be around the running shaft rotation of oneself, to regulate and control gaseous flow direction, circulation passage area; Latter's operating mode is relatively stable, operating temperature high (maximum temperature can reach 2000 ℃ at present), and blade generally is fixed on the turbine rotor, and gas flows vertically.Aero gas turbine engine turbine blade design has at present entered the multidisciplinary optimal design stage, the coupled relation of subjects such as that design will take into full account is pneumatic, structure, material, heat transfer, vane type line generally adopts the combination of curve, but there is discontinuous curvature derivative point in build-up curve, generation speed, pressure crest have reduced turbine performance near blade.Because turbine performance depends primarily on the boundary layer flow of blade surface, and boundary layer flow is subjected to the influence of blade surface radius of curvature, reasonable for the speed and the pressure distribution that make blade surface, the aeroturbine blade adopts five order polynomials structure vane type line.
The nozzle blade shape has experienced the evolution from island blade profile, Thin Blade, symmetric profile to pneumatic blade profile.The island blade profile is a kind of asymmetrical wedge shape blade profile, and the pressure distribution on this blade profile profile is not ideal enough, and flow losses are higher, velocity coefficient
Generally can only reach 0.94～0.95, and reduction is more when low mach, so this blade profile is not suitable for the low mach operating mode.The pneumatic effect of Thin Blade is relatively poor, but cheap for manufacturing cost, modification is simple.At present, people no longer adopt island blade profile and Thin Blade, are in from using symmetric profile to pneumatic blade profile transition period.The mean camber line of symmetric form blade is a straight line, and the back of the body, abdomen two sides are generally arc-shaped curved surface, also can be the plane, and its advantage is to be easy to oppositely regulate.Pneumatic blade profile is according to the gas dynamics principle design, for reducing flow losses, its blade face molded lines is designed to smooth no flex point, single order, the continuous curve of second dervative, therefore the blade profile molded lines generally adopts simple quadratic curve, as circle, ellipse, parabola, also can adopt twisted-pair cable, log spiral, hyperbola and biquadratic curve etc.In general, when radial turbine used the nozzle blade of this air-driven type, the efficient of turbine will improve 1%～2% than the turbine efficiency that uses non-pneumatic blade profile.Therefore, use the pneumatic blade profile through developing meticulously mostly in the radial turbine of small-power gas turbine, at this moment, the requirement of aspects such as technology, cost has been withdrawn to second.
Degree of reaction ρ is expression static energy shared ratio in total energy, and in field of turbochargers, it is one of major parameter of turbine design, is to be used for weighing the parameter that the expansion work of combustion gas in movable vane accounts for the percentage of full primitive level overall expansion merit.In general, medium imports and exports that speed on the cross section differs and not quite (particularly axial flow) at impeller, the variation of medium energy mainly shows in the variation of pressure or enthalpy, and medium obtains the kinetic energy part of (exchange) from impeller, finally still must rely on static part to be converted to the variation of static energy.Because it is different that degree of reaction makes that the impeller pressure inside distributes, its variation can cause the variation of various losses.When reducing as degree of reaction, the frictional loss of nozzle ring internal loss and hub disk increases, but the impeller internal loss reduces, and the outlet leaving loss of impeller also reduces.The design turbine is when selecting degree of reaction ρ value, and total trend is to tend to adopt less degree of reaction.It can make impeller work under lower temperature field, and work is favourable to impeller.But degree of reaction can not reduce arbitrarily, avoid occurring in the impeller passage diffusion and flow.Because blade shape is very big to the influence of degree of reaction, therefore, wish a kind of nozzle ring blade profile of design, make degree of reaction in smaller or equal to 0.5 optimum value scope.
At present, existing many pieces of patents have related to the design of VNT nozzle blade, improvement blade as patent 02800079.X variable nozzle turbocharger, 02819327.X variable-vane manufacture method and variable-vane in the VGS type turbosupercharger, 02819329.6VGS variable-vane manufacture method and variable-vane in the type turbosupercharger, 03824627.9 be used for the curved vane of improved turbosupercharger, 03809928.4 be used for the improved Blade Design of the turbosupercharger of geometry-variable, 200380111024.4 be used for the curved surface bucket of turbosupercharger etc., but the working surface of the blade that they are related is not three-dimensional blade face, be ruled surface blade profile developable surface, its forming method is comparatively simple.
Summary of the invention
One of purpose of the present invention is the defective at prior art, provides a kind of variable geometry turbocharger three-dimensional nozzle blade.
The variable geometry turbine supercharger nozzle ring three dimendional blade that the present invention is designed, comprise pressure side, suction surface, blade inlet edge, blade trailing edge, wherein, the corresponding blade profile concave surface of pressure side, the corresponding blade profile convex surface of suction surface, suction surface and pressure side constitute vane thickness.Pressure side and suction surface form wire are quadratic curve or biquadratic curve, and pressure side and suction surface form wire are not same curve; Blade pressure surface and suction surface forward position constitute blade inlet edge, and the blade inlet edge form wire is a quadratic curve, form the three-dimension curved surface leading edge; Blade pressure surface and suction surface tail are along constituting blade trailing edge, and the blade trailing edge form wire is that quadratic curve and trailing edge height molded lines are consistent with turbine blade import molded lines, form the three-dimensional space curved surface fine stern.
The designed three-dimensional nozzle blade of variable geometry turbocharger of the present invention is installed on the turbine box end, thereby widens the range of flow of turbosupercharger, improves the highest turbine efficiency.
The present invention also provides the design method of described three-dimensional nozzle blade, may further comprise the steps:
The own geometric parameter design of step 2, nozzle ring, determine import structure angle, the angle of attack, go out the outlet structure angle, the little circle radius of front and rear edge, blade chord length, highly, the selection of maximum blade thickness and blade profile molded lines;
Step 6, nozzle blade is carried out the checking of performance and reliability trial;
Step 7, the three-dimensional nozzle blade engineering drawing design of variable geometry turbocharger.
Beneficial effect
Three-dimensional nozzle blade of variable geometry turbocharger of the present invention and design method thereof have following beneficial effect:
1) designed a variable geometry turbocharger or the constant cross-section of being applicable to the three-dimensional nozzle blade of air-driven type of leaf turbosupercharger has been arranged, compare with other nozzle ring, three-dimensional nozzle blade of the present invention is housed have been realized prewhirling, (ρ reduces to have adjusted degree of reaction ρ according to designing requirement, then the frictional loss of nozzle ring internal loss and hub disk increases, but the impeller internal loss reduces), the radial-flow turbine of variable geometry turbocharger is developed to the mixed flow turbine direction, thereby improve turbine efficiency (general mixed flow turbine efficient is higher than radial-flow turbine efficient more than 5%), the cylinder type leading edge can adapt to the different flow path directions that comes, the three-dimensional space curved surface fine stern has reduced the whirlpool loss of blade back air-flow (entering before the turbine wheel), reduce the flow losses of whole turbine stage, and then improved turbine efficiency;
2) provide the design method of the three-dimensional nozzle blade of a kind of comparatively comprehensively variable geometry turbocharger, not only consider the peak efficiency of nozzle ring itself and blade itself, and take all factors into consideration the turbine box in the place ahead, the turbine wheel design at rear, and realize above-mentioned three's optimum Match.Nozzle blade success rate by this method design is higher, and cost is lower.
Description of drawings
The geometric parameter of Fig. 1 VNT blade;
The VNT blade that Fig. 2 the present invention is designed;
The original air-driven type VNT of Fig. 3 blade
Fig. 4 turbocharger rotor system and intermediate sectional drawing
The front end face figure of Fig. 5 nozzle ring and mounting disc
The rear ends figure of Fig. 6 nozzle ring and mounting disc
The installation diagram of Fig. 7 nozzle ring and shift fork
Fig. 8 efficiency characteristic figure
Fig. 9 turbine flow performance plot
Figure 10 nozzle ring design flow diagram
Among the figure, 1 is pressure side, and 2 is suction surface, and 3 is blade inlet edge, and 4 is blade trailing edge, and 5 is the turbocharger rotor system, and 6 is intermediate, and 7 for rotating shaft, 8 is a compressor impeller, and 9 is turbine wheel, and 10 are mounting disc, and 11 is shift fork, and 12 is nozzle ring.
Embodiment
The present invention is described in further detail below in conjunction with accompanying drawing and embodiment.
Variable geometry turbine supercharger nozzle ring three dimendional blade of the present invention includes but are not limited to variable geometry turbocharger (VGT).For explaining conveniently, adopt VGT to be described in this specification as example.
The present invention designed to the basis of the axial flow compressor cascade test between nineteen sixty at NASA according to pneumatic principle in 1940.The design of nozzle blade mainly is radially to amass folded forming by the blade profile in some cross sections by certain rule.Used geometric parameter and flow parameter when accompanying drawing 1 has shown blade forming: leading edge structure angle β
q, trailing edge structure angle β
h, flow inlet angle β
1, efflux angles β
2, angle of attack i, trailing edge bending angle δ, blade profile established angle γ, leading-edge radius R
q, the trailing edge radius R
h, chord length b, pitch t, blade profile axial width S, blade profile maximum ga(u)ge C
MaxWith width a of throat etc.During the design blade, each parameter of blade all must be carried out according to certain design rule.According to the design method of said nozzle ring vane foil parameter, and guarantee the continuous smooth transition of the adjacent circular arc of each section of nozzle ring cross-sectional profiles, accomplish how much tangent, the jointing place single order can be led continuously.
Variable geometry turbine supercharger nozzle ring three dimendional blade designed according to this invention as shown in Figure 2, comprise pressure side, suction surface, wherein, the corresponding blade profile concave surface 1 of pressure side, i.e. face ABCD, the corresponding blade profile convex surface 2 of suction surface, be face EFGH, pressure side and suction surface form wire are circle, oval, parabola, quadratic curve or biquadratic curves such as twisted-pair cable, log spiral, hyperbola, and pressure side and suction surface form wire are not same curve.Blade pressure surface and suction surface forward position constitute blade inlet edge, i.e. face ABEF, and blade import leading edge form wire is a quadratic curve, forms the three-dimension curved surface leading edge, line AB is the intersecting line of suction surface ABCD and leading edge ABEF; Blade pressure surface and suction surface tail be along constituting blade trailing edge, i.e. face CDGH, and blade exit trailing edge form wire is that quadratic curve and trailing edge height molded lines are consistent with turbine blade import molded lines, formation three-dimensional space curved surface fine stern.Three-dimensional nozzle blade height equals the turbine blade entrance width; Maximum blade thickness is smaller or equal to 40% length of blade (chord length), and its maximum ga(u)ge place is apart from leading edge 20%～30% length of blade (chord length), and the denseness of blade is 0.5～0.8.
Accompanying drawing 4 is the sectional drawing of turbocharger rotor system 5 and intermediate 6, and rotor-support-foundation system comprises rotating shaft 7, compressor impeller 8 and turbine wheel 9, and compressor impeller 8 is connected by rotating shaft 7 with turbine wheel 9.Accompanying drawing 5 is the front end face of nozzle ring 12 and mounting disc 10, and nozzle ring 12 and mounting disc 10 are installed in the turbine box of turbine end.Nozzle ring 9 is installed in the mounting disc 10 by shift fork 11, shown in the accompanying drawing 6,7.Their common gas flows that flows into turbine wheel 9 of regulating.
At present, mainly estimate the quality of nozzle ring blade profile by the turbine characteristic curve, respectively original nozzle ring and the designed three-dimensional blade profile of nozzle ring of the present invention are installed on certain variable geometry turbocharger, obtain efficiency characteristic figure (accompanying drawing 8) and turbine flow performance plot (accompanying drawing 9), by accompanying drawing as can be seen, the designed more former air-driven type nozzle ring of its efficient of nozzle ring of the present invention has had raising by a relatively large margin, and range of flow is also expanded to some extent than former air-driven type nozzle ring.
Comprehensively above-mentioned, and shown in Figure 10, during to the design of nozzle blade, at first the structure to nozzle ring designs, and mainly is key elements such as blade quantity, cascade solidity, blade axis of rotation position, nozzle ring passage maximum area and blade minimax aperture are carried out calculation Design (step 200).Then to the geometric parameter design of nozzle ring own.Be embodied in import structure angle, the angle of attack, go out the outlet structure angle, the little circle radius of front and rear edge, blade chord length, highly, the selection (step 201) of maximum blade thickness and blade profile molded lines.After various parameters are determined, whole turbine stage is carried out three-dimensional modeling and CFD analysis, use 3 d modeling software that it is carried out modeling, assembling, utilize the CFD analysis software that its interior flow field is analyzed, find out flow losses zone and damnous reason in the model, determine to optimize the position, return step 201 again, redefine the geometric parameter (step 202) of nozzle ring itself.On the basis of above step, nozzle blade blade profile and nozzle ring structure are optimized design.The nozzle blade molded lines is done further improvement, and further optimization is done between nozzle blade rotating shaft position, blade and the turbine box and the gap of blade axis hole, and the slewing area of definite nozzle ring and best corner (step 203).Utilize multidisciplinary coupling optimal design theory, nozzle blade and turbine stage are carried out the Coupling Design of fluid mechanics, solid mechanics, structural mechanics, thermal conduction study and materials science.Comprehensive Design (step 204) is carried out in manufactured materials, heat radiation and protection etc. to nozzle ring and turbine stage.After proving that in theory designed nozzle blade is reasonable in design, make the nozzle ring material object, nozzle blade is carried out performance and reliability trial checking (step 205).At last the three-dimensional nozzle blade of variable geometry turbocharger is carried out engineering drawing design (step 206).
Three-dimensional nozzle blade of variable geometry turbocharger of the present invention and design method thereof, its application include but not limited to turbosupercharger, miniature gas turbine and other turbomachines.
Claims (4)
1. variable geometry turbine supercharger nozzle ring three dimendional blade, comprise pressure side, suction surface, blade inlet edge, blade trailing edge, the corresponding blade profile concave surface of pressure side, the corresponding blade profile convex surface of suction surface, blade pressure surface and suction surface forward position constitute blade inlet edge, and blade pressure surface and suction surface tail is characterized in that along constituting blade trailing edge, pressure side and suction surface form wire are quadratic curve or biquadratic curve, and pressure side and suction surface form wire are not same curve; The blade inlet edge form wire is a quadratic curve, forms the three-dimension curved surface leading edge; The blade trailing edge form wire is that quadratic curve and trailing edge height molded lines are consistent with turbine blade import molded lines, forms the three-dimensional space curved surface fine stern.
2. blade according to claim 1 is characterized in that: the smooth no flex point of blade pressure surface and suction surface form wire.
3. blade according to claim 1 is characterized in that: nozzle ring three dimendional blade height equals the turbine blade entrance width; Maximum blade thickness is smaller or equal to 40% blade chord length, and its maximum ga(u)ge place is apart from leading edge 20%～30% blade chord length, and the denseness of blade is 0.5～0.8.
4. the design method of the described blade of claim 1 may further comprise the steps:
Step 1, nozzle ring structural design are determined blade quantity, cascade solidity, blade axis of rotation position, nozzle ring passage maximum area and blade minimax aperture;
The own geometric parameter design of step 2, nozzle ring, determine import structure angle, the angle of attack, go out the outlet structure angle, the little circle radius of front and rear edge, blade chord length, highly, the selection of maximum blade thickness and blade profile molded lines;
Step 3, whole turbine stage is carried out three-dimensional modeling and CFD analyze, turbine stage comprises turbine case, nozzle ring and turbine, use 3 d modeling software that it is carried out modeling, assembling, utilize the CFD analysis software that its interior flow field is analyzed, find out flow losses zone and damnous reason in the model, determine to optimize the position, and the geometric parameter of nozzle ring in the step 2 itself is improved and optimizated;
Step 4, nozzle blade blade profile and nozzle ring structure are optimized design, on the basis of step 3, the nozzle blade molded lines is done further improvement, and between nozzle blade rotating shaft position, blade and the turbine box and the gap of blade axis hole done further optimization, and the slewing area of definite nozzle ring and best corner;
Step 5, utilize multidisciplinary coupling optimal design theory, nozzle blade and turbine stage are carried out the Coupling Design of fluid mechanics, solid mechanics, structural mechanics, thermal conduction study and materials science, comprehensive Design is carried out in manufactured materials, the heat radiation of nozzle ring and turbine stage and protecting etc.;
Step 6, nozzle blade is carried out the checking of performance and reliability trial;
Step 7, the three-dimensional nozzle blade engineering drawing design of variable geometry turbocharger.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010219044 CN101915130B (en) | 2010-06-25 | 2010-06-25 | Three-dimensional nozzle ring vane of variable geometry turbocharger and design method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010219044 CN101915130B (en) | 2010-06-25 | 2010-06-25 | Three-dimensional nozzle ring vane of variable geometry turbocharger and design method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101915130A true CN101915130A (en) | 2010-12-15 |
| CN101915130B CN101915130B (en) | 2013-04-03 |
Family
ID=43322740
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010219044 Active CN101915130B (en) | 2010-06-25 | 2010-06-25 | Three-dimensional nozzle ring vane of variable geometry turbocharger and design method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101915130B (en) |
Cited By (26)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102182546A (en) * | 2011-04-22 | 2011-09-14 | 北京理工大学 | Mixed flow turbocharger with variable nozzle ring |
| CN102562173A (en) * | 2012-02-01 | 2012-07-11 | 大同北方天力增压技术有限公司 | Structure integrally comprising three-dimensional guiding type pneumatic blade and flow mixing turbine |
| CN102608914A (en) * | 2011-12-22 | 2012-07-25 | 西安交通大学 | Optimization design method of radial-flow-type hydraulic turbine |
| WO2013091222A1 (en) * | 2011-12-22 | 2013-06-27 | 西安交通大学 | Optimized design method for radial-flow-type hydraulic turbine |
| CN103711528A (en) * | 2013-10-22 | 2014-04-09 | 萍乡市慧成精密机电有限公司 | Mixed-flow turbocharger variable nozzle ring |
| CN105089635A (en) * | 2015-07-01 | 2015-11-25 | 中国石油天然气股份有限公司 | Design method and system of rear turbine of underground camera |
| CN106471216A (en) * | 2014-07-10 | 2017-03-01 | 赛峰飞机发动机公司 | Method for being modeled to the sunken groove portion of blade |
| CN106570213A (en) * | 2016-10-11 | 2017-04-19 | 北京航空航天大学 | Design method of variable inlet guide vane, and blade and compressor |
| CN107398746A (en) * | 2017-09-22 | 2017-11-28 | 重庆江增船舶重工有限公司 | A kind of cutting tool and processing method of nozzle outer shroud |
| CN109356666A (en) * | 2018-12-14 | 2019-02-19 | 中国航发沈阳发动机研究所 | A kind of Blade Design Method of axial-flow turbine big and small blade combination cascade |
| CN109458359A (en) * | 2018-12-26 | 2019-03-12 | 中国船舶重工集团公司第七0三研究所 | A kind of blade profile improving helium compressor single-stage pressure ratio |
| CN109477417A (en) * | 2016-12-21 | 2019-03-15 | 三菱重工发动机和增压器株式会社 | The nozzle vane and turbine of turbocharger, turbocharger |
| CN109977513A (en) * | 2019-03-18 | 2019-07-05 | 北京理工大学 | A kind of suction surface three-arc blade shape construction method for fan and compressor |
| CN110135059A (en) * | 2019-05-14 | 2019-08-16 | 中国航发沈阳发动机研究所 | A kind of blade profile thickness location mode and blade |
| CN110907118A (en) * | 2019-12-12 | 2020-03-24 | 西北工业大学 | Plane blade grid experimental device with variable installation angle and experimental method |
| CN111460571A (en) * | 2019-01-02 | 2020-07-28 | 中国航发商用航空发动机有限责任公司 | Method and device for constructing molded line of intermediate casing component and computer readable storage medium |
| CN112065588A (en) * | 2020-09-02 | 2020-12-11 | 中国航发沈阳黎明航空发动机有限责任公司 | Flow adjusting method of swirl vane type prewhirl nozzle for aircraft engine |
| CN112065737A (en) * | 2020-09-09 | 2020-12-11 | 上海尚实能源科技有限公司 | Ultrahigh pressure ratio single-stage axial flow compressor based on super-large aspect ratio |
| CN113051688A (en) * | 2021-04-09 | 2021-06-29 | 中山大学 | Blade profile shape geometry calculation method, device and equipment |
| CN113177281A (en) * | 2021-05-21 | 2021-07-27 | 清华大学 | Design method and system for aero-engine near-net-shape blade clamp |
| CN113958519A (en) * | 2021-10-14 | 2022-01-21 | 西安交通大学 | Method for automatically generating blades with different shapes of centrifugal impeller based on middle surface |
| CN114542207A (en) * | 2022-02-22 | 2022-05-27 | 中国航发沈阳发动机研究所 | Design method for outer surface modeling of turbine rear casing support plate |
| CN115059516A (en) * | 2022-05-29 | 2022-09-16 | 中国船舶重工集团公司第七0三研究所 | Wicker-shaped guide vane of power turbine of gas turbine |
| CN115203833A (en) * | 2022-05-29 | 2022-10-18 | 中国船舶重工集团公司第七0三研究所 | Method for shaping air-cooled turbine rotor blade exhausting at suction side |
| CN115982892A (en) * | 2023-03-17 | 2023-04-18 | 潍柴动力股份有限公司 | Blade design method, blade and related equipment |
| CN115977746A (en) * | 2023-03-17 | 2023-04-18 | 潍柴动力股份有限公司 | Circumferential asymmetric nozzle ring, design method, volute and turbocharger |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3605398B2 (en) * | 2002-02-26 | 2004-12-22 | 三菱重工業株式会社 | Variable capacity turbocharger |
| CN1629450A (en) * | 2003-12-17 | 2005-06-22 | 联合工艺公司 | Airfoil with shaped trailing edge pedestals |
| CN1840859A (en) * | 2005-04-01 | 2006-10-04 | 通用电气公司 | Turbine airfoil with trailing edge convection |
| CN1890455A (en) * | 2003-12-05 | 2007-01-03 | 诺沃皮尼奥内控股有限公司 | Variable nozzle for a gas turbine |
| CN2900356Y (en) * | 2006-04-29 | 2007-05-16 | 申振华 | Blunt tail edge wing |
| US20090104023A1 (en) * | 2005-07-19 | 2009-04-23 | Frederic Favray | Variable Nozzle Turbocharger |
| CN101549332A (en) * | 2008-04-03 | 2009-10-07 | 通用电气公司 | Airfoil for nozzle of forming the machined contoured passage therein |
-
2010
- 2010-06-25 CN CN 201010219044 patent/CN101915130B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3605398B2 (en) * | 2002-02-26 | 2004-12-22 | 三菱重工業株式会社 | Variable capacity turbocharger |
| CN1890455A (en) * | 2003-12-05 | 2007-01-03 | 诺沃皮尼奥内控股有限公司 | Variable nozzle for a gas turbine |
| CN1629450A (en) * | 2003-12-17 | 2005-06-22 | 联合工艺公司 | Airfoil with shaped trailing edge pedestals |
| CN1840859A (en) * | 2005-04-01 | 2006-10-04 | 通用电气公司 | Turbine airfoil with trailing edge convection |
| US20090104023A1 (en) * | 2005-07-19 | 2009-04-23 | Frederic Favray | Variable Nozzle Turbocharger |
| CN2900356Y (en) * | 2006-04-29 | 2007-05-16 | 申振华 | Blunt tail edge wing |
| CN101549332A (en) * | 2008-04-03 | 2009-10-07 | 通用电气公司 | Airfoil for nozzle of forming the machined contoured passage therein |
Cited By (37)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102182546A (en) * | 2011-04-22 | 2011-09-14 | 北京理工大学 | Mixed flow turbocharger with variable nozzle ring |
| CN102608914A (en) * | 2011-12-22 | 2012-07-25 | 西安交通大学 | Optimization design method of radial-flow-type hydraulic turbine |
| WO2013091222A1 (en) * | 2011-12-22 | 2013-06-27 | 西安交通大学 | Optimized design method for radial-flow-type hydraulic turbine |
| CN102608914B (en) * | 2011-12-22 | 2014-03-12 | 西安交通大学 | Optimization design method of radial-flow-type hydraulic turbine |
| CN102562173A (en) * | 2012-02-01 | 2012-07-11 | 大同北方天力增压技术有限公司 | Structure integrally comprising three-dimensional guiding type pneumatic blade and flow mixing turbine |
| CN103711528A (en) * | 2013-10-22 | 2014-04-09 | 萍乡市慧成精密机电有限公司 | Mixed-flow turbocharger variable nozzle ring |
| CN106471216A (en) * | 2014-07-10 | 2017-03-01 | 赛峰飞机发动机公司 | Method for being modeled to the sunken groove portion of blade |
| CN105089635A (en) * | 2015-07-01 | 2015-11-25 | 中国石油天然气股份有限公司 | Design method and system of rear turbine of underground camera |
| CN106570213A (en) * | 2016-10-11 | 2017-04-19 | 北京航空航天大学 | Design method of variable inlet guide vane, and blade and compressor |
| CN106570213B (en) * | 2016-10-11 | 2019-07-16 | 北京航空航天大学 | The design method and blade of variable inlet guide vane, compressor |
| CN109477417A (en) * | 2016-12-21 | 2019-03-15 | 三菱重工发动机和增压器株式会社 | The nozzle vane and turbine of turbocharger, turbocharger |
| CN109477417B (en) * | 2016-12-21 | 2021-12-24 | 三菱重工发动机和增压器株式会社 | Turbocharger, nozzle vane of turbocharger, and turbine |
| CN107398746A (en) * | 2017-09-22 | 2017-11-28 | 重庆江增船舶重工有限公司 | A kind of cutting tool and processing method of nozzle outer shroud |
| CN109356666A (en) * | 2018-12-14 | 2019-02-19 | 中国航发沈阳发动机研究所 | A kind of Blade Design Method of axial-flow turbine big and small blade combination cascade |
| CN109356666B (en) * | 2018-12-14 | 2021-05-25 | 中国航发沈阳发动机研究所 | Blade profile design method for large and small blade combined blade cascade of axial flow turbine |
| CN109458359A (en) * | 2018-12-26 | 2019-03-12 | 中国船舶重工集团公司第七0三研究所 | A kind of blade profile improving helium compressor single-stage pressure ratio |
| CN111460571B (en) * | 2019-01-02 | 2023-07-21 | 中国航发商用航空发动机有限责任公司 | Construction method and construction device for molded line of intermediate case component and computer readable storage medium |
| CN111460571A (en) * | 2019-01-02 | 2020-07-28 | 中国航发商用航空发动机有限责任公司 | Method and device for constructing molded line of intermediate casing component and computer readable storage medium |
| CN109977513B (en) * | 2019-03-18 | 2020-09-18 | 北京理工大学 | Suction surface three-arc blade molding method for fan and gas compressor |
| CN109977513A (en) * | 2019-03-18 | 2019-07-05 | 北京理工大学 | A kind of suction surface three-arc blade shape construction method for fan and compressor |
| CN110135059B (en) * | 2019-05-14 | 2023-01-17 | 中国航发沈阳发动机研究所 | Blade profile thickness distribution method and blade |
| CN110135059A (en) * | 2019-05-14 | 2019-08-16 | 中国航发沈阳发动机研究所 | A kind of blade profile thickness location mode and blade |
| CN110907118A (en) * | 2019-12-12 | 2020-03-24 | 西北工业大学 | Plane blade grid experimental device with variable installation angle and experimental method |
| CN112065588A (en) * | 2020-09-02 | 2020-12-11 | 中国航发沈阳黎明航空发动机有限责任公司 | Flow adjusting method of swirl vane type prewhirl nozzle for aircraft engine |
| CN112065588B (en) * | 2020-09-02 | 2021-08-03 | 中国航发沈阳黎明航空发动机有限责任公司 | Flow adjusting method of swirl vane type prewhirl nozzle for aircraft engine |
| CN112065737A (en) * | 2020-09-09 | 2020-12-11 | 上海尚实能源科技有限公司 | Ultrahigh pressure ratio single-stage axial flow compressor based on super-large aspect ratio |
| CN113051688A (en) * | 2021-04-09 | 2021-06-29 | 中山大学 | Blade profile shape geometry calculation method, device and equipment |
| CN113051688B (en) * | 2021-04-09 | 2022-04-19 | 中山大学 | Blade profile shape geometry calculation method, device and equipment |
| CN113177281A (en) * | 2021-05-21 | 2021-07-27 | 清华大学 | Design method and system for aero-engine near-net-shape blade clamp |
| WO2022242709A1 (en) * | 2021-05-21 | 2022-11-24 | 清华大学 | Design method and system for near-net shape blade clamp of aero-engine |
| CN113958519A (en) * | 2021-10-14 | 2022-01-21 | 西安交通大学 | Method for automatically generating blades with different shapes of centrifugal impeller based on middle surface |
| CN113958519B (en) * | 2021-10-14 | 2024-03-29 | 西安交通大学 | Automatic generation method for blades in different shapes of centrifugal impeller based on intermediate surface |
| CN114542207A (en) * | 2022-02-22 | 2022-05-27 | 中国航发沈阳发动机研究所 | Design method for outer surface modeling of turbine rear casing support plate |
| CN115059516A (en) * | 2022-05-29 | 2022-09-16 | 中国船舶重工集团公司第七0三研究所 | Wicker-shaped guide vane of power turbine of gas turbine |
| CN115203833A (en) * | 2022-05-29 | 2022-10-18 | 中国船舶重工集团公司第七0三研究所 | Method for shaping air-cooled turbine rotor blade exhausting at suction side |
| CN115982892A (en) * | 2023-03-17 | 2023-04-18 | 潍柴动力股份有限公司 | Blade design method, blade and related equipment |
| CN115977746A (en) * | 2023-03-17 | 2023-04-18 | 潍柴动力股份有限公司 | Circumferential asymmetric nozzle ring, design method, volute and turbocharger |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101915130B (en) | 2013-04-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101915130B (en) | Three-dimensional nozzle ring vane of variable geometry turbocharger and design method thereof | |
| US7255530B2 (en) | Vane and throat shaping | |
| JP4460538B2 (en) | Camber wings for use in turbochargers | |
| JP6001999B2 (en) | Airfoil, compressor, vane, gas turbine engine, and stator row | |
| JP5179161B2 (en) | Gas turbine engine including multiple curved stator vanes and method of assembling the same | |
| US6709233B2 (en) | Aerofoil for an axial flow turbomachine | |
| US9334744B2 (en) | Vane assembly for an axial flow turbine | |
| CN104514631A (en) | Turbocharger with mixed flow turbine stage | |
| US9200518B2 (en) | Axial turbine wheel with curved leading edge | |
| CN101113678A (en) | Outlet flowing intersecting surface changing adjustable turbo nozzle ring | |
| CN101050722A (en) | Changeable outlet flow section turbine jet nozzle ring | |
| CN106907185B (en) | Protruding nozzle for controlling secondary flow and optimum diffuser performance | |
| CN112974734B (en) | Manufacturing method of integrally formed swept combined blade | |
| CN203756591U (en) | Compressor impeller for small-sized turbine booster | |
| CN114165477B (en) | Axial ultrasonic through-flow fan serial configuration and serial configuration optimization method | |
| CN114151195A (en) | Novel exhaust diffuser structure capable of improving pneumatic performance | |
| CN115263436A (en) | Transonic turbine rotor blade, turbine rotor and turbine | |
| CN117329147A (en) | Impeller integrated structure and design method thereof | |
| CN110608196B (en) | Wedge-shaped diffuser with half-blade high and small blades | |
| CN218760034U (en) | Impeller of turbocharger | |
| CN206397816U (en) | A kind of fan structure for aero-engine | |
| Zhang et al. | Design of turbocharger variable nozzle | |
| CN115982892B (en) | Blade design method, blade and related equipment | |
| CN115059518B (en) | Air-cooled turbine guide vane trailing edge structure of suction side exhaust | |
| CN116044514B (en) | Turbine and turbocharger |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| ASS | Succession or assignment of patent right |
Owner name: PINGXIANG HUICHENG PRECISION MACHINERY + ELECTRONI Free format text: FORMER OWNER: BEIJING LIGONG UNIVERSITY Effective date: 20131113 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| COR | Change of bibliographic data |
Free format text: CORRECT: ADDRESS; FROM: 100081 HAIDIAN, BEIJING TO: 337000 PINGXIANG, JIANGXI PROVINCE |
|
| TR01 | Transfer of patent right |
Effective date of registration: 20131113 Address after: 337000, No. 85, West Avenue, Pingxiang economic and Technological Development Zone, Jiangxi, Anyuan Patentee after: Pingxiang Huicheng Precision Machinery & Electronic Co., Ltd. Address before: 100081 No. 5, Zhongguancun South Street, Haidian District, Beijing Patentee before: BEIJING INSTITUTE OF TECHNOLOGY |