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Recent Radial Turbine Research at Nasa Lewis 1972

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Recent Radial Turbine Research at Nasa Lewis 1972 ( recent-radial-turbine-research-at-nasa-lewis-1972 )

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14.3 S. N 14.1 13.0 9.90 z q - Total all diffusers Static, original diffuser, Diffuser Original -- Seconu ---- Third Designvalue E 7 9.70 CL 9.60(a) Pressure distributions. 1•0 .9 1.D w .9 240 TSecond and third diffusers E 60 C y 160 a> 80 Fir-. 11 Diffuser des i;ri pressures and veloc I ties S?yCI?IC UFliEll IT V Si'IC,f TIOId1 The development of high-speed turbomachinery is expensive. It is, therefore, desirable to use a given basic design for a variety of applications with different power levels. The closed-loop space power program includes a range of power level:; with the co-:r_c:_ requir .:c. a. of hi _ cffl: Static efficiency Design value Orinaldiffuser - 20Q 4 8 12 16 20 24 28 Axial distance from trailing edge of rotor blades, cm 0 2 4 6 8 10 Axial distance from trailing edge of rotor blades, in. (b) Velocity distributions. --- (a) Second diffuser. (b; Third diffuser. Static,second and third diffusers Total efficiency Fig. 12 Turbine with diffuser (5 60 .64 .68 .72 .76 .80 .84 Blade-jet speed ratio, v Fig. 13 Variation of turbine effic-=roc . wi':f^ blade-;let speed ratio a'.. eq _:- tiler`_: c . i.._ speed for the i:liree di -tiers iu . The ue:a_-ed operating range could bc. achieved without major change in the turbine a,d compressor by three methods. Operating pressure could be changed with nominally constant pressure ratios. This would change mass flow but not vol- ume flow. Metering areas could be changed by si - Stato Roto 7, Downloaded from http://asmedigitalcollection.asme.org/GT/proceedings-pdf/GT1972/79818/V001T01A041/2390888/v001t01a041-72-gt-42.pdf by guest on 23 January 2021

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