1030:. Tesla attacked this problem by substituting a series of closely spaced disks for the blades of the rotor. The working fluid flows between the disks and transfers its energy to the rotor by means of the boundary layer effect or adhesion and viscosity rather than by impulse or reaction. Tesla stated his turbine could realize incredibly high efficiencies by steam. There has been no documented evidence of Tesla turbines achieving the efficiencies Tesla claimed. They have been found to have low overall efficiencies in the role of a turbine or pump. In recent decades there has been further research into bladeless turbine and development of patented designs that work with corrosive/abrasive and hard to pump material such as ethylene glycol, fly ash, blood, rocks, and even live fish.
94:
970:
707:
64:, a radial turbine can employ a relatively higher pressure ratio (â4) per stage with lower flow rates. Thus these machines fall in the lower specific speed and power ranges. For high temperature applications rotor blade cooling in radial stages is not as easy as in axial turbine stages. Variable angle nozzle blades can give higher stage efficiencies in a radial turbine stage even at off-design point operation. In the family of water turbines, the
80:
261:
800:
646:
430:
35:
and radial turbines consists in the way the fluid flows through the components (compressor and turbine). Whereas for an axial turbine the rotor is 'impacted' by the fluid flow, for a radial turbine, the flow is smoothly orientated perpendicular to the rotation axis, and it drives the turbine in the
48:
40:. The result is less mechanical stress (and less thermal stress, in case of hot working fluids) which enables a radial turbine to be simpler, more robust, and more efficient (in a similar power range) when compared to axial turbines. When it comes to high power ranges (above 5
410:
1000:. It consists of rings of cantilever blades projecting from two discs rotating in opposite directions. The relative peripheral velocity of blades in two adjacent rows, with respect to each other, is high. This gives a higher value of enthalpy drop per stage.
992:
In outward flow radial turbine stages, the flow of the gas or steam occurs from smaller to larger diameters. The stage consists of a pair of fixed and moving blades. The increasing area of cross-section at larger diameters accommodates the expanding gas.
694:
786:
At off-design operation, there are additional losses in the nozzle and rotor blade rings on account of incidence at the leading edges of the blades. This loss is conventionally referred to as shock loss though it has nothing to do with the shock
1081:
Osterle, J.F., âThermodynamic considerations in the use of gasified coal as a fuel for power conversion systemsâ, Frontiers of power technology conference proceedings, Oklahoma State
University, Carnegie-Mellon University, Pittsburgh, Oct.
93:
723:
The stage work is less than the isentropic stage enthalpy drop on account of aerodynamic losses in the stage. The actual output at the turbine shaft is equal to the stage work minus the losses due to rotor disc and bearing friction.
641:{\displaystyle {\begin{aligned}\eta _{\text{ts}}&={\frac {h_{01}-h_{03}}{h_{01}-h_{3ss}}}={\frac {\psi \,u_{2}^{2}}{C_{p}\,T_{01}\left(1-\left({\frac {p_{3}}{p_{01}}}\right)^{\frac {\gamma -1}{\gamma }}\right)}}\end{aligned}}}
281:) known as the isentropic velocity, spouting velocity or stage terminal velocity is defined as that velocity which will be obtained during an isentropic expansion of the gas between the entry and exit pressures of the stage.
211:
945:
1050:"Author, Harikishan Gupta E., & Author, Shyam P. Kodali (2013). Design and Operation of Tesla Turbo machine - A state of the art review. International Journal of Advanced Transport Phenomena, 2(1), 2-3"
1022:. One of the difficulties with bladed turbines is the complex and highly precise requirements for balancing and manufacturing the bladed rotor which has to be very well balanced. The blades are subject to
287:
699:
The two quantities within the parentheses in the numerator may have the same or opposite signs. This, besides other factors, would also govern the value of reaction. The stage reaction decreases as C
764:
These are due to circulatory flows developing into the various flow passages and are principally governed by the aerodynamic loading of the blades. The main parameters governing these losses are b
435:
1103:
Hurst, J.N. and
Mottram, A.W.T., âIntegrated Nuclear Gas turbinesâ, Paper No. EN-1/41, Symposium on the technology of integrated primary circuits for power reactors, ENEA, Paris, May 1968.
666:
1088:
Stasa, F.L. and
Osterle, F., âThe thermodynamic performance of two combined cycle power plants integrated with two coal gasification systemsâ, ASME J. Eng. Power, July 1981.
1121:
Mcdonald, C.F. and Boland, C.R., âThe nuclear closed-cycle gas turbine (HTGR-GT) dry cooled commercial power plant studiesâ, ASME J. Eng. Power, 80-GT-82, Jan. 1981.
79:
44:) the radial turbine is no longer competitive (due to its heavy and expensive rotor) and the efficiency becomes similar to that of the axial turbines.
1100:
Hubert, F.W.L. et al., Large combined cycles for utilitiesâ, Combustion, Vol. I, ASME gas turbine conference and products show, Brussels, May 1970.
749:. In the ninety degree IFR turbine stage, the losses occurring in the radial and axial sections of the rotor are sometimes separately considered.
1118:
Mcdonald, C.F. and Smith, M.J., âTurbomachinery design considerations for nuclear HTGR-GT power plantâ, ASME J. Eng. Power, 80-GT-80, Jan. 1981.
132:
826:
221:
The stagnation state of the gas at the nozzle entry is represented by point 01. The gas expands adiabatically in the nozzles from a pressure
1109:
Kehlhofer, R., âCalculation for part-load operation of combined gas/steam turbine plantsâ, Brown Boveri Rev., 65, 10, pp 672â679, Oct. 1978.
1094:
Ushiyama, I., âTheoretically estimating the performance of gas turbines under varying atmospheric conditionâ, ASME J. Eng. Power, Jan. 1976.
969:
1112:
Kingcombe, R.C. and
Dunning, S.W., âDesign study for a fuel efficient turbofan engineâ, ASME paper No. 80-GT-141, New Orleans, March 1980.
706:
1097:
Yannone, R.A. and
Reuther, J.F., âTen years of digital computer control of combustion turbines ASME J. Engg. Power, 80-GT-76, Jan. 1981.
1124:
Nabors, W.M. et al., âBureau of mine progress in developing the coal burning gas turbine power plantâ, ASME J. Eng. Power, April 1965.
249:. Since this is an energy transformation process, the stagnation enthalpy remains constant but the stagnation pressure decreases (p
405:{\displaystyle \,C_{0}={\sqrt {2C_{p}\,T_{01}\,\left(1-\left({\frac {p_{3}}{p_{01}}}\right)^{\frac {\gamma -1}{\gamma }}\right)}}}
996:
This configuration did not become popular with the steam and gas turbines. The only one which is employed more commonly is the
741:
These losses are also governed by the channel geometry, coefficient of skin friction and the ratio of the relative velocities w
1106:
Jackson, A.J.B., âSome future trends in aeroengine design for subsonic transport aircraftâ,-ASME J. Eng. Power, April 1976.
1073:
260:
1085:
Starkey, N.E., âLong life base load service at 1600°F turbine inlet temperatureâ, ASME J. Eng. Power, Jan. 1967.
703:
increases because this results in a large proportion of the stage enthalpy drop to occur in the nozzle ring.
689:{\displaystyle R={\frac {\text{static enthalpy drop in rotor}}{\text{stagnation enthalpy drop in stage}}}}
257:) due to losses. The energy transfer accompanied by an energy transformation process occurs in the rotor.
1115:
Mayers, M.A. et al., âCombination gas turbine and steam turbine cyclesâ, ASME paper No. 55-A-184, 1955.
68:
is a very well-known IFR turbine which generates much greater power with a relatively large impeller.
793:
This is due to the flow over the rotor blade tips which does not contribute to the energy transfer.
816:
The blade-to-gas speed ratio can be expressed in terms of the isentropic stage terminal velocity c
987:
799:
118:, respectively. The relative velocity of the flow and the peripheral speed of the rotor are w
997:
656:
The relative pressure or enthalpy drop in the nozzle and rotor blades are determined by the
729:
8:
975:
Variation of stage efficiency of an IFR turbine with blade-to-isentropic gas speed ratio
657:
100:
Velocity triangles for an inward-flow radial (IFR) turbine stage with cantilever blades
61:
712:
Variation of the degree of reaction with flow coefficient and air angle at rotor entry
1137:
1069:
734:
They depend on the geometry and the coefficient of skin friction of these components.
758:
These are mainly governed by the geometry of the diffuser and the rate of diffusion.
1091:
Traenckner, K., âPulverized-coal gasification
Ruhrgas processesâ, Trans ASME, 1953.
65:
1131:
1019:
1009:
421:
32:
28:
1015:
206:{\displaystyle \,\tan {\beta _{2}}={\frac {c_{r2}}{c_{\theta 2}-u_{2}}}}
1027:
940:{\displaystyle \,\sigma _{s}={\frac {u_{2}}{c_{0}}}=^{-{\frac {1}{2}}}}
1023:
37:
41:
1049:
754:
730:
Skin friction and separation losses in the scroll and nozzle ring
126:
respectively. The air angle at the rotor blade entry is given by
47:
24:
739:
Skin friction and separation losses in the rotor blade channels
106:
The radial and tangential components of the absolute velocity c
266:
Enthalpy-entropy diagram for flow through an IFR turbine stage
1078:'A review of cascade data on secondary losses in turbines'
1003:
829:
669:
433:
290:
135:
939:
688:
640:
404:
205:
1129:
71:
216:
31:is radial to the shaft. The difference between
1068:'Turbines, Compressors and Fans 4th Edition'
86:Ninety degree inward-flow radial turbine stage
981:
55:
811:
805:Losses in the rotor of an IFR turbine stage
753:Skin friction and separation losses in the
830:
552:
524:
331:
320:
291:
136:
968:
798:
705:
259:
46:
1004:Nikola Tesla's bladeless radial turbine
998:Ljungstrom double rotation type turbine
1130:
1044:
1042:
235:with an increase in its velocity from
1018:developed and patented his bladeless
651:
780:and hub-tip ratio at the rotor exit.
272:
1039:
415:
13:
14:
1149:
682:stagnation enthalpy drop in stage
660:of the stage. This is defined by
424:is based on this value of work.
92:
78:
718:
918:
914:
877:
871:
1:
1062:
679:static enthalpy drop in rotor
72:Components of radial turbines
217:Enthalpy and entropy diagram
7:
10:
1154:
1007:
985:
982:Outward-flow radial stages
784:Shock or incidence losses
422:total-to-static efficiency
56:Advantages and challenges
27:in which the flow of the
1033:
812:Blade to gas speed ratio
36:same way water drives a
988:Out-flow radial turbine
277:A reference velocity (c
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406:
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52:
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208:
50:
1014:In the early 1900s,
827:
667:
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288:
133:
791:Tip clearance loss
539:
979:
937:
809:
716:
686:
658:degree of reaction
652:Degree of reaction
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525:
402:
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203:
62:axial flow turbine
53:
933:
866:
762:Secondary losses
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273:Spouting velocity
201:
1145:
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416:Stage efficiency
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66:Francis turbine
60:Compared to an
58:
17:
16:Type of turbine
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11:
5:
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1008:Main article:
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986:Main article:
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51:Radial turbine
21:radial turbine
15:
9:
6:
4:
3:
2:
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1080:
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1074:9780070707023
1071:
1067:
1066:
1051:
1045:
1043:
1038:
1031:
1029:
1025:
1021:
1020:Tesla turbine
1017:
1011:
1010:Tesla turbine
1001:
999:
994:
989:
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34:
30:
29:working fluid
26:
22:
1016:Nikola Tesla
1013:
995:
991:
974:
949:
815:
804:
722:
719:Stage losses
711:
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655:
419:
276:
265:
243:
236:
229:
222:
220:
105:
99:
85:
59:
20:
18:
1063:References
1028:cavitation
1024:corrosion
923:−
905:β
900:
888:ϕ
833:σ
621:γ
614:−
611:γ
572:−
522:ψ
494:−
469:−
440:η
390:γ
383:−
380:γ
341:−
188:−
180:θ
146:β
141:
38:watermill
1138:Turbines
1132:Category
755:diffuser
965:â 0.707
25:turbine
1072:
787:waves.
253:> p
1082:1974.
1053:(PDF)
1034:Notes
122:and u
114:and c
110:are c
33:axial
23:is a
1070:ISBN
1026:and
958:= 90
950:for
420:The
897:cot
772:, d
242:to
228:to
138:tan
1134::
1041:^
820:.
776:/d
768:/d
745:/w
701:θ2
597:01
559:01
489:01
477:03
464:01
444:ts
366:01
327:01
255:02
251:01
116:q2
112:r2
42:MW
19:A
1055:.
963:s
961:Ď
956:2
954:β
931:2
928:1
919:]
915:)
909:2
892:2
884:+
881:1
878:(
875:2
872:[
869:=
862:0
858:c
852:2
848:u
842:=
837:s
818:0
778:2
774:3
770:2
766:2
747:2
743:3
674:=
671:R
628:)
617:1
604:)
593:p
587:3
583:p
577:(
569:1
565:(
555:T
548:p
544:C
536:2
531:2
527:u
516:=
508:s
505:s
502:3
498:h
485:h
473:h
460:h
453:=
397:)
386:1
373:)
362:p
356:3
352:p
346:(
338:1
334:(
323:T
316:p
312:C
308:2
303:=
298:0
294:C
279:0
246:2
244:c
239:1
237:c
232:2
230:p
225:1
223:p
196:2
192:u
183:2
176:c
169:2
166:r
162:c
156:=
150:2
124:2
120:2
108:2
Text is available under the Creative Commons Attribution-ShareAlike License. Additional terms may apply.
_turbine_stage_with_cantilever_blades.jpg)
