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Summary 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 thick- nesses which would allow cooling passages to be added, The overall stage performance measurements and the rotor and stator exit flow field surveys were obtained. Measure- ments 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 maxi- mum 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 restag- gering 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 configurations 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 tur- bines found in the literature. Introduction The performance of radial turbines can exceed that of axial turbines in small size applications. In addition, one radial stage may replace two or possibly more axial stages because of the higher stage pressure ratios that a radial turbine can achieve. The bulkiness and weight of radial inflow turbines, however, have made them difficult to incorporate in aircraft propulsion systems. To address this issue, ajoint program was established between Pratt and Whitney Aircraft, the Army Propulsion Laboratory, and NASA Lewis Research Center to reduce the size (i.e., axial length) and weight of a radial in- flow turbine rotor. Pratt and Whitney designed two highly loaded compact radial inflow turbine rotors, both parties ana- lyzed the rotor flow fields with their respective design sys- tems, and NASA Lewis conducted aerodynamic performance tests (refs. 1to4). The design goals were to reduce the rotor axial length by 40 to 50 percent and the weight by 20 to 30 percent while main- taining or exceeding conventional state-of-the-art radial tur- bine efficiency. Carefully controlling the flow to avoid high losses in such a significantly shorter blade was aided by the use of a three-dimensional flow analysis code (ref. 1). Two compact radial turbine stages were designed using these com- putational tools and are representative of a rotorcraft main propulsion engine or a regional commuter aircraft application. The resulting turbine work factors (gJAh/U 2 ) of 1.1 to 1.2 and a pressure ratio of greater than 4.6 are indications of high aerodynamic loading. All test and rig adapting hardware was provided by Pratt and Whitney. The blading was scaled up nominally 1.5 times the engine size to make it compatible with the Lewis Small Engine Component Test Facility. The turbine testing was conducted by Lewis personnel and the data shared by the two parties.PDF Image | Aerodynamic Radial Inflow Turbine Rotors
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