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Form Approved REPORT DOCUMENTATION PAGE OMB No. 0704-0188 Publicreportinbgurdenforthiscollectioonfinformatioisnestimatetdoaverage1hourperresponsein,cludintghetimeforrewewinignstructionse,archinegxistingdatasources, gatherinagndmaintaininthgedataneededa,ndcompletinagndreviewintghecollectioonfinformationS.endcommentrsegardintghisburdenestimatoeranyotheraspecotfthis. collectioonf informatioin,cludinsguggestionfosrreducintghisburdent,o WashingtoHneadquarteSresrvicesD,irectoraftoerInformatioOnperationasndReports1,215Jefferson DavisHighwayS,uite1204A,rlingtonV,A22202-430a2n,dtotheOfficeofManagemeantdBudgePt,aperwoRrkeductioPnrojec(t0704-0188W),ashingtoDn,C20503. 1. AGENCYUSEONLY(Leaveblank) 2. REPORTDATE July 1995 4. TITLEANDSUBTITLE Aerodynamic Evaluation of Two Compact Radial-Inflow Turbine Rotors 6. AUTHOR(S) E Susan Simonyi, Richard J. Roelke, Roy G. Stabe, Brentley C. Nowlin, and Danielle DiCicco 7, PERFORMINGORGANIZATIONNAME(S)ANDADDRESS(ES) National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio 44135-3191 9. SPONSORING/MONITORINGAGENCYNAME(S)ANDADDRESS(ES) National Aeronautics and Space Administration Washington, D.C. 20546-0001 11. SUPPLEMENTARYNOTES E Susan Simonyi and Roy G. Stabe, Sverdrup Technology, Inc., Lewis Research Center Group, Brook Park, Ohio 44142 (work funded by NASA Contract NAS3-25266), presently at NYMA, Inc., Engineering Services Division, 2001 Aerospace Parkway, Brook Park, Ohio 44142; Richard J. Roelke, Brentley C. Nowlin, and Danielle DiCicco, NASA Lewis Research Center. Responsible person, Brentley C. Nowlin, organization code 2850, (216) 433-2675. 12a. DISTRIBUTION/AVAILABILITYSTATEMENT 12b. DISTRIBUTIONCODE Unclassified - Unlimited Subject Category 37 13. ABSTRACT (Maximum 200 words) The aerodynamic evaluation of two highly loaded compact radial turbine rotors was conducted at the NASA Lewis Research Center Small Engine Component Test Facility (SECTF). The experimental results were used for proof-of-concept, for modeling radial inflow turbine rotors, and for providing data for code verification. Two rotors were designed to have a shorter axial length, up to a 10-percent reduced diameter, a lighter weight, and equal or higher efficiencies compared with those of conventional radial inflow turbine rotors. Three configurations were tested: rotor I, having a 40-percent shorter axial length, with the design stator (stator I); rotor I with the design stator vanes closed down (stator II); and rotor II, slightly shorter axially and having higher loading, with stator II. The stator had 36 vanes and the rotors each had 14 solid blades. Although presently uncooled, the rotor blades were designed for thicknesses which would allow cooling passages to be added. The overall stage performance measurements and the rotor and stator exit flow field surveys were obtained. Measurements of steady state temperatures, pressures, mass flow rates, flow angles, and output power were made at various operating conditions. Data were obtained at corrected speeds of 80, 90, 100, 110, and 120 percent of design over a range of equivalent inlet-to-exit pressure ratios of 3.5, 4.0, 4.5, and 5.0, the maximum pressure ratio achieved. The test showed that the configuration of rotor I with stator I running at the design pressure ratio produced a flow rate which was 5.6 percent higher than expected. This result indicated the need to close down the stator flow area to reduce the flow. The flow area reduction was accomplished by restaggering the vanes. Rotor I was retested with the closed-down stator vanes and achieved the correct mass flow. Rotor II was tested only with the restaggered vanes. The test results of the three turbine configura- tions were nearly identical. Although the measured efficiencies of the compact designs fell 2 to 3 points below the predicted effi- ciency of 91 percent, they did meet and exceed by up to 2.5 percentage points the efficiencies of state-of-the-art turbines found in the literature. 14. SUBJECTTERMS Compact radial turbine; Experiment; Performance 15. NUMBEROF PAGES "71 16. PRICECODE A04 20. LIMITATIONOFABSTRACT 17. SECURITYCLASSIFICATION OF REPORT Unclassified 18. SECURITYCLASSIFICATION OF THISPAGE 19.SECURITYCLASSIFICATION OFABSTRACT NSN7540-01-280-5500 Standard Form 298 (Rev. 2-89) Prescribedby ANSIStd.Z39-18 298-102 Unclassified Unclassified 3. REPORTTYPEANDDATESCOVERED Technical Paper 5. FUNDINGNUMBERS WU-505-62-I0 8. PERFORMINGORGANIZATION REPORTNUMBER E-9213 10. SPONSORING/MONITORING AGENCY REPORTNUMBER NASA TP-3514PDF Image | Aerodynamic Radial Inflow Turbine Rotors
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