DE1428105A1 - Mixed flow turbomachines - Google Patents

Description

DH. ING. F.WUB8THOFF ₈ MUNICH 9

DIFL. IWG. G. PUtS SCHWEIGERSTRASSE 8

DH. B. τ. PECHMANN tkmfo * aa οβ si

FBOTSCTrATSHT

1A-25 441

Biaciirilbaflg to the patent application

GENEBAL DYNAMICS GCBPCBAfIOH New York 2o, N.Y., U.S.A.

concerning mixed flow turbochargers

The present invention deals with turbo machines with mixed flow, in particular turbo machines old _O emiaohter flow, which have a special "blade * ora, old help which in comparison to conventional turbo machines with mixed flow one achieves improved performance and increased pressure and whose blades can be manufactured cheaply are·

So far developed and used door bomaschines with "aisohter flow" were mostly designed in such a way that the flow did not exit axially, that is, that the flow device of the impeller or the Botor was in an out-of-the-way direction as a consistency old of the axis of rotation of the impeller Rotors ▼ issued. The main disadvantage of this type of. Machines lay in the fact that additional energy is consumed

BATH ORIGINAL

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the aic & fe axial

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BAD ORiGiNAL

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1 * 28105

2 2 or the impeller (represented by the term W ^ «=> W ₂ ) through the stator or output line & e & fine (shown

2 2 the link 02 - O _- ^.) Is sucked ". Mao, w r $ eä.Q®h been of the opinion that it s in the case of Turtoomaschi & mixed flow in which large AblenJomge ^ i ^ lc '! The flow through the rotor was not present, a slowed flow through the lot or flow, aa this inevitably lead to a standstill ~ W ^ l & der Suler-Forffiel aeg & tiv, eo that the actual scne ^ by the effective f ogalkraft and the slowed flow && right the stator reduces the pressure. Given the vorhendeziva. Fessehleumigtaa flow through the rotor was "υ possible, higher pressures su achieve than men with direct axial flow, however, nor at the expense of a considerable decrease in the degree of efficiency" _e Ba you ReI- • «mg · - or inhibition losses within mltmT- f iirbo machine with the square of the relative speed of the flow dm * · * the rotor and the absolute speed; the flow to vary the stator "Is" s ümm ? "chmann clear, dft · the respective oelgea ßesehwlndigkeltem", af Sem * ur Braemgunf of the desired bridge setweadige ", minimum stiffenedA are musaem · With the knowledge of theJ it is possible Bot «r bucket of forbomaschiae with mixed material tamog even damm a slow sowing stri« in stasia, large angles of deflection are necessary xm <ä © a. desired

BATH ORIGINAL 80 980 9/03 12

Generate pressure su without the risk of standing still appears, you can now lead the flow means at lower speeds through the rotor and stator and thereby increase the performance of the machine, since dl *> Relief losses have been reduced. It's firm && "It that the improved performance can be achieved, if the hatred of Yerlangsasung is within the following limits holds »

Unprotected in slotted Rotorsc Freq one Rotorschaufelnt a) The ratio of the relative average output speed of the flow at the trailing edge of the airfoil or blade or vane aa rotor or impeller sur relatiren average Slngangsgeschwindigkeit the flow at the Torderkante of the airfoil or blade on the rotor or impeller must be within • in a range ron o.7 to 1, oo _t 55 to 1, o;

ORIGIfSiAL BATHROOM

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with unslotted with slotted red owl; Rotorachaufein; b) the ratio of the relative outlet speed of the flow at the rear edge of the blade profile or the blade on the rotor or impeller to the relative inlet speed of the flow at the hub at the leading edge of the blade profile or the blade on the rotor or impeller must be within a range from 0.8 to 1.1 o, S5 to 1.1)

o) the ratio of the relative initial velocity of the flow at the wing tip at the Trailing edge of the wing profile or the bucket on the rotor or impeller sor relative entry velocity of the flow at the wing tip at the leading edge of the airfoil or the blade on the rotor must be within one Range from o.6o to o.85 o.45 to o.85

lie.

_mJ £ _m BAD ORIGINAL

80980S / 03 1

In karkösuiliGhan turbo machine! * With direct axial flow does the use of sea? Kl ^ in @ r relafcirer strömtragsa ± tfceleinle.3wink # I (B ^) to stop because of the extraordinarily great slowing down of the flow, but it has been recognized that with a certain design it is possible to have the impeller, even with large relative values StrÖÄi2agsmitt © l © inlaßwinl £ elB (B ^), a. Range of very specific values of slowed flow through the impeller noticeable «The bddsut ^ t ^ that la fall Ton Turbomasohin®a ait mixed flow Now the Kögilökxeit exists, special» Laristaagascaema. with the help of 3 © "? Receives @ Brück ι flow fpet ^ Bl ^ gen" This fisrfeältais is aiii «swisonen flea apezif iecMem We ^ t vmd dem

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Winkel «, M @ & ^ caam j et st <ti, ia> far ^ oaaa-shiae alt Strönmog k23ieti-iiier®a ₉ al® ®Sb. #. Brusfe »cia ^ mEiiMig jswieuh © n that of the laid B @ ^ ri $ bap! 2a ^^ uad

having"

As already erwälwt _f is the G "s ^ & i.t. or Tom the Äab" - -.-; des Laui'araäiäe voa Bsdeutiiagpwenn an ia-®Iä # »« rodynafliseiae Setorlfälcfettüä efrsiofet aeMea asoll. In order to achieve the degree of aerodynamic enhancement, the shape of the hub should -od «r _? ,,. _t,. «Beselileunigang. cut the rotor in a s # st® «, ert®n sudden fluctuation®®, a & nh ®h && © d« r_

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BATH

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Ια the change ratio. How to accomplish this can earn is known to those skilled in the art.

01 · Recognition that a moderate area of slowed fluid flow through the rotor of a turbomachine old mixed flow _{can be admitted to any relative flow medium inlet angle (B 1} ), without the fact that the machine stops "in connection with the fact that the effect of reducing the cross-sectional area rom the rotor inlet sum Eo cor outlet a reduced change of the turning angle at the various Piimktftu along the blade height with it, leads to an approximation of a constant curvature · It is therefore possible to choose a suitable, decreasing cross-section! one chooses the correct labenfora, which under certain circumstances can be designed in such a way that a wing profile or a sehaafel with a constant curvature can be used. The status of this constant curvature feature is very important, since the use of a blade with the same curvature does not have a noticeably detrimental effect on the overall performance of the turbomachine with mixed flow with variable curvature. Tone of the same ability is the recognition that it is possible to use a rlfgelfrofll or a scoop which has no load over its entire height. foraalerwelse comb a not twisted without any significant loss of performance

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& ur «lana te® with st turn« w @ md @ r staffeluagewi or SiAfollwinlml << T) constant is «It is ever ^ öofe feetgeeiwllt i ^ prdea that the St®ff« laiig8wlisfeal (0 whatsoever pi der WiBlE «! ₉ oatcr in the d®a S @ t @ r entrance and et fi® aaeii ä © a B © tffi «feedfe ^ © E de® of the respective wing up to gn, 25 ° ^" © a des g «säß the feokaaatem Aiäslsguag free vortex # rreoJiaet®BW @ i? t © a

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invention, an impeller or a rotor efficiency of 93 % can be obtained, which is significantly higher than the efficiency of any known mixed flow turbomachine and such an efficiency is achieved with blades or vanes that are simple in construction and inexpensive in of manufacture are.

It is the main aim of the present invention an inexpensive mixed flow turbo machine au create that significantly improved efficiency achieved in operation.

It is another object of the invention to provide a mixed flow, axial flow flow structure . create in the respective relative. Velocities through impeller and outlet guide vanes for I3? R $ ienu & g the desired pressure on a minimum genaliiöa. will.

Another object of the invention is dari & ₉ a -turbo- * machine to create in which the Sohäufeln or vanes on the impeller or the rotor have a constant curvature, and the ratio of the relative average output speed aa <i # r trailing edge of each vane or mixed flow of each vane to the relative constant entry velocity of the flow at the leading edge of each vane or vane is less than "1" 1.

BATH ORIGINAL

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Ss Ist £ © ra (S® Siel ä @ r Erfiaäusg, sia impeller for mixed flow au

@r ss @ Jto Flügaiprofll © © des? Scäaaf @ la siafweisfc, <äi si © i \ Im allgeoeineii. radial ψ & μ iasfif ^ ad € 5 ^ @

«Ϊα @ Γ, every St? Iiaöfsl -eis © lölbiiag mad Ssiia © aa'fe mid iia

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the end of flight flow at the leading edge of each airfoil is less than 0.85 and the ratio of relative output balance of the flow on the property aa of the trailing edge of each airfoil sur the relative entry speed of the flow at the leading edge of each airfoil is less than 1.1 "

Another object of the invention is to create an impeller for Yurboasehinen old mixed flow which has airfoils which extend substantially radially from the impeller and at which the ratio of the relative constant high flow at the trailing edge of each airfoil sur relative average entrance pitch at the leading edge of each airfoil within a range of O ₉ ? varies up to o.95

The above aspects of the invention are based on the means shown in the attached drawings.

Fig. 1 is a traditional longitudinal section thereafter

fnreoaasshine old stabbed Sfcroaung uniquely Bot or «ad stator old shovel geaäder

Vif · Z 1st a saheaati »« h »r longitudinal» cut through «ine

furtoaa "4hiae old feaischttr st ^ ösung © iasehlieS-IUk Rttor und Spaltsehauf" lsteior, in a "

BATH ORIGINAL

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a growing axial flow zone lies ι old blades according to the Erfinäojag; flg .. 3 is a snowcat © !? Longitudinal edge duroJi a Turbcaasciiia? " with a mixed flow including the rotor and stator, which lies in an S-shaped axial flow zone, is a flight from the result.

Fig * 4 is a Yefctors & roffliuageoiagsaisEi a tjpisöh © ß Turboaasahine with gemiaaiites? Flow according to the invention ₉ the toe u $ f Hate® is shown from ^ Fig. 5 isfe «in the tekt'öretröaaagsdisgraaini a typical Giisn

with mixed flow geaäß the , which is shown f @ m Fliigeleade aae

Figures 1 · = ■ 3 zelg # n one Tarbomascaima with geiaieehter Strömaag 1o "which" has in eylissdrisclies Ssiiäiise 12, -S7 «.lcnoc £ an ed®r S © tor 1% impeller with scoops or

16 _t an inner GeMdse 18 with Aasgangsl®it8eliau-> s ^ like an electr © is © toi? 22 ₉ the sleä ianeriialb des düMiisee 18 beflM @ t and email © im® Well® alt dem Β © gate 14 wr & ii & den ist- _e angeoämst elmd »Xn the figure 2 and iat, like the inm # re Exact 16 a downstream suneismeiid® axial® strösmagßsene releases * The Botorsonau »f®l 16 in figure; 1 aid di @ lasgangsl ^ itachaofel 2o in figure

old ViZA ?. Gap 24 rdraehen, des? la "eeontlichea L & ngssrle & timg str @ £ downwards in Besmg ais-C die Seim" der '16 vmä Lsitseia auf ^ l 2a gate of the Unterselt ©

8 0 9809/0312

Upper side of the wing profile extends; «, whose Aastritt; at the top is due to the dimensions of the gap and overlay i ». essential to the German patent application 6 32 61? (filed on October 29, 1961) Specifications correspond. In Figures 1 and 2 are the Airfoils or blades with an eseiiwongenem outline and essentially constant curvature and tendon as well without significant distortion over the entire wing profile or oohaufelhöhe shown. In Figure 5 are the wings 16 and guide vanes 2o with constant thickness, such as it usually when using ^ metal bisohaahaufel is the case, and with constant oilftimg and tendon as well as without significant distortion in the Flügalhö & e. Figures 4 and 5 line vector diagrams for typical turbo machines raifc mixed atröauag according to the present invention. They used in this fi ^ aran Syaboles have the following meanings:

^C a1 " ^{the aD80iut} · Bingattge speed represents the loft in

Point 1. ^G a2 designates the absolute

speed when leaving the impeller ia point W ^ denotes the relateirs Strömaltüelges ^ liwindig geoMseen in Besag on the impeller blade in

Point 1 and W ₂ the relative flow against the initial start-up measured in Besag on the impeller heap «! in poiikt

ORIGINAL BATHROOM

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Energy inside the rotor and stator of the turbomachine, namely:

A. 2gH - (o | - U ₁ ) ♦ (V ₁ - V |) ♦ (O ₂ - O ₀₂ )

can be brought to the following form:

B. 2gH · 2Oo AO _n ♦ 0? -. - 0_o

^^ c. Up an o <£

From this equation sti it can be seen that the singing indication speed (Uj ₁₂ ) can be changed without the induced droak (E) being directly impaired; However, every change in the input hub total (Uw ₁ ) promotes a corresponding change in the absolute fluid _{inlet speed (C b1} ) a decrease toa 0 _m * an increase τοη Δθ »is necessary. This reduction toa 0 _{b1 leads} to a corresponding reduction τοη f} _ft1 gives «ine Herabaetsoag τοη V _q1 · However m« S for the same pressure ^{generation (H) A c} u greater weraea »waa s« buckets corresponding decrease in size V ^ ₂ fükrt . On this softly it is seen that the coldness V _{2 to} V _{1 can be} streamed and so chosen “Aam aa remains within the ordained Qrensen.

Ba 1 ·% farner can be seen from FIGS. 4 and 5, there it is about the initial determination of suitable proportions

BATH ORIGINAL 809809/0312 -16-

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speed (W ^) and this in turn a reduction in the relative output speed (Wj ₄₂ ) * The decrease in (W ^) *** & doroh causes the increase in the vortex initial speed ζ AC _TT ) necessary to create the desired bracket (H). These

"h2

An increase in Δ C ₁ actually causes a change

^ü h2

in the deflection of the flow stop means durcii dao I during © β the impeller dureiiflI®Btr * A © from C _a > j requires eiü «• ntsgr-eofeamde Veriainderiäeg des lingangenabeiidurohaesaera (B ^) s, ^ ob © i dl © Schaofelgeseb-win» speed (U ^) constant; remains "@odaE aiii® ve" iad®rfce relative EingaiigagöBonwindigkeit on FX @% @ l3Bd (but MUS Aö "Gröbe ^ Werdes _s äaMt; -the

^ü t2
Druok (H) scores wisd. Bieae Wlx * kong

The flow deflection in the Baroleli de ineia other Yeriiältnis than in the Bsrelsii f olgedes3 «B can be controlled the relative« Abloaku & g (^) s © woSil la area of possessions like the Flügoleßdes üuzoh äi @ S "iolitig9 choice of Sinüaügsnaböadurciiiaesetsrs on the Gablet dar Turboma ^ siiiaoakonstrLilr.tlQa known that öchaufelprofil © ,, which cause a beatimrate Äbl8.TikaBg d @ a Htröaiungaaiittele, (in teeaonderer fei © ©) sms the Vereuohsergeltaissen, which won like the NASS *. (National Aeronautics and Spaoe ^ erddn informed. Polglicn advertises the rieiitig © selection of Siiigauganubeadiiroiiaessers in ä & ü® which an impeller blade Aiit gleleiibl ©! bsa & er

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Sl * τατϋ · β «α <1 · Er * Ladung was · la wt *« ntlicia * n under Slav ·! «On lAufrmfi- or Rofcor * ehauX« ln, si «kaaa jedooh auoh b« i festeteiitoden od * r Leltayhaufeln Τ · ηΝΐιιΑαοβ tiaäwn »Xm Ztummatmhang old uaiaufeMsa anS 41 · Bttwtgtiag & * r Fluldstraaung In a look at the btv« e «nd« n Sohaof · Ia berüolwloisitlst! «« Rd «a _t wälir« iid with r «fl ^« t »h« od * a soaauf «Ia or Flug · In only dlo absolutely · Struaaag> altt« lbewegtuie la Betraoht tu draw 1st.

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Claims (1)

2ο Α-25 rüeli pmskfe @ IS © fößS®i © fe t ₈ that ee aiw @ i mash siaiisn © _& ; ■ · -. Sofeaisf © la. sufwel © fe _? wob @ i ό lia @ gaisSDsQ © © liwiB.i.Igl £ @ £ t dsr Steöiaisg ate the as 1 o@tea.gt9 © k ο © M a © Joä.® ^ umß. öaß 809809/0312 the BAD GRJGfMAL -21- -25 441 average Auaganga speed of the current at the rear edge of every soiia on # 1 * ur relative average Singing speed of the flow at the gate edge each blade within a range of 0.7 varies to 1, o. 5 x Surbomaschinenlaufrad old mixed flow, characterized gekennseichne t, that the impeller swel flights lprojTile which extend substantially from the impeller radially outward, Jed # s Flügalprof 11 such arm shows the impeller & eht is _t that the Ifabendurchmesser dea Laujpfradee aa Sohnittpuakt swiseli @in the impeller and the door edge of each wing profile is smaller than the ifabendurehaesser of the impeller at the Belmltfcpunkt "between the impeller and the Hintörsaato Jadeii wing profile, and that the flow rate ara Inde each wing profile runs essentially kösaeütrisöh m, U the axis of rotation of the impeller; and the FlaiäströmaiuQg. in the properties of each wing profile there is a substantial mixture of axial and radial flow, and the ratio of the relative flow rate of the flow & n the trailing edge of the wing profile sar relative durohschnittli ^ aem total speed of the road at the door edge is less than 1, imd that j # d® @ Flügalprofil an essentially? gl @ iehblsibande has curvature. -22- BAD OR'GfNAL 809809/031 2 gg © I2 Q © k e a © H ₉ "S @ hae Is © a © s © i & © m a s & ο t ₉ WQKlLB Slffi ?. ate (ta am the Hab © am dos BATH 80 980 9/03 1A-25W 142 δ 105 9 »Turbomachine old mixed flow * thereby g · k · a η χ β i η · t» that it «is impeller old ta has lattice-shaped arranged blades, the essential το» impeller extend radially outwards, as well as middle son drive the impeller «• chäuf" in and a la main housing "in which the impeller and are arranged DI® eehmufein, each hill on the impeller is mounted such ₉ that the Habendurchm <$ s @ he of the impeller aa intersection between the LaufrM mad the door edge of each impeller & wing is & smaller than the * «Haesser des L ^ ifrades aa sehaittpaakfe mwim & hmn. Impeller and the trailing edge of every Laraf reif lügels, usd daä the relation of relmtirsa by @ clmittl £ © ben Auz »gfcagsgcschwladigkelt der EtrHnimg an de? : <?. * ■>: ^ λ: λϊ ;. Te j «of the impeller wing on the relative through-haittli © fe © a Singangsgesehwiadigkeit of the flow at the leading edge of each impeller wing · is less than 1« and that each of the impeller wing ·! has a substantially constant curvature " 1o. Turbomachine according to Claim 9, characterized in that each wing on the impeller Ib is formed over the entire wing height without any significant difference. «» 24- BATH ORIGINAL 809809/0312 .1 β ι £ ι @ i © la. ε. ® t _s that J «the hill on L & saf ^ si. «La® at the as "© 985 SteSwiBg mm, umr I®fe® aa d © i? linter came J®dee mm Lw & Sw & M. w @ jai (g «r as 1 _fi 1 thereby g the «A at 14- «f aarfeoffiaeeteila« mmh ta-nprsaete 9 «dadurdb g« Si ® si m. S .- · £ β Jt η ® ·. t- _e d & £ each wing on ORfGlMAL -25- 809809/03 12 15 · Turboasehinen runner old mixed flow, thereby geke η η ζ ei ch α β t _t that the impeller «w # i has split vane profiles, which extend essentially«!} Radially from the impeller, whereby each split vane profile is attached to the impeller in such a way that the diameter of the impeller at the Sennit tptrnfet between the impeller and the front edge of each joint profile is smaller than the diameter of the impeller as the intersection between the impeller and the rear edge of each split vane profile , and that the fluid flow at the Does the fluid flow run along the surface of each wing profile in a w ^ ssBtilsSiea »in a mixture of axial and radial? ₄ is flow wan that the Terhältnis the relative durohsohnifctliciiss Ausgaogsgeschwindigkeit the stroaung at the hiatus-e ^ Each kaat® Spaltflägelprofils for relative durchaehnittliehen lingaagsgeschwindigkeit the flow at the Tordtrkant® each airfoil within a range toh o _T 55 to 1 o 'varies, and that every split flight profile has an essentially constant curvature 16. TurboaaachineniaiAfrad to Inspruah 15 »dadureh geicena "verifies" that every space is lying "! profile la essentially without twisting over the entire height of the tile profile is trained. 17 · furboaasohlnenlauf wheel »according to claim 16» dadorah ORIGINAL BATHROOM 809809/0312 © ft, © 555 Ms 1g © Imo® Bg = » g © © Im © 809809/0312