Organizational Unit: TurboPropulsion Laboratory
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The Turbopropulsion Laboratory (TPL) and Gas Dynamics Laboratory (GDL) possess a unique set of facilities which are used in teaching and research related to air-breathing propulsion, space propulsion and turbomachinery. The research activities are supported by the U.S. Navy, NASA and industry.
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Now showing 1 - 8 of 8
Publication Progress report - multistage axial compressor program on tip clearance effects(Monterey, CA; Naval Postgraduate School, 1981-08) Moyle, Ian N; TurboPropulsion Laboratory; Aeronautics and AstronauticsPublication Procedure and computer program for the approximation of data (with application to multiple sensor probes)(Monterey, CA; Naval Postgraduate School, 1980-08) Zebner, H.; TurboPropulsion Laboratory; Operations Research (OR); Aeronautics and AstronauticsA procedure to approximate data given at arbitrary intervals in two-, three- and four dimensions using polynominal expressions is described. The programming of the problem is explained in each case and a user manual is given for software implemented on the TPL Hewlett-Packard computer system. The method, which is general, was derived and has been applied to represent the calibration of flow probes which have multiple sensors.Publication Professor Garth V. Hobson: a biography(Monterey, California. Naval Postgraduate School, 2013) Hobson, Garth V.; TurboPropulsion Laboratory; Mechanical and Aerospace Engineering (MAE)Publication An Experimental and Analytical Study of Tip Clearance Effects in Axial Flow Compressors(Monterey, CA; Naval Postgraduate School, 1991-12) Moyle, Ian N.; TurboPropulsion LaboratoryAn analytical and experimental study of the performance changes and flow effects of rotor tip clearance variation in axial flow compressors is presented. The analyses demonstrate that previously unrecognized loss characteristics and flow behavior trends can be identified in a wide range of published tests of clearance effects. The performance and flow data are correlated at constant power conditions or nondimensionally in terms of the test compressor's geometry and wall flow conditions to observe the trends.Publication Experimental and computational investigation of cross-flow fan propulsion for lightweight VTOL aircraft(American Society of Mechanical Engineers (ASME), 2004-06) Hobson, Garth V.; Cheng, W.T.; Seaton, M. Scot; Gannon, Anthony; Platzer, Max F.; TurboPropulsion LaboratoryCross-flow fan propulsion has not been seriously considered for aircraft use since an Vought Systems Division (VSD) study for the U.S. Navy in 1975. A recent conceptual design study of light-weight, single seat VTOL aircraft suggest that rotary-engine powered cross-flow fans may constitute a promising alternative to the conventional lift-fan vertical thrust augmentation systems for VTOL aircraft. The cross-flow fan performance data obtained by VSD supported the hypothesis that they could be improved to the point where their thrust augmentation could be used in a VTOL aircraft. In this paper we report results of a NASA Glenn supported experimental and computational cross-flow fan investigation which is currently in progress and we provide an assessment of the potential suitability of cross-flow fans for VTOL aircraft propulsion. The tests are carried out in the Turbopropulsion Laboratory of the Naval Postgraduate School, using an existing Turbine Test Rig as a power source to drive the cross- flow fan. A 0.305 m (12-inch) diameter, 38.1 mm (1.5-inch) span cross-flow fan test article was constructed to duplicate as closely as possible the VSD fan so that baseline comparison performance data could be obtained. Performance measurements were taken over a speed range of 1,000 to 7,000 RPM and results comparable to those measured by Vought Systems Division were obtained. At 3,000 RPM a 2:1 thrust-to-power ratio was measured which dropped to one as the speed was increased to 6,000 RPM. Performance maps were experimentally determined for the baseline configuration as well as one with both cavities blanked off, for the speed range from 2,000 to 6,000 rpm. Using Flo++, a commercial PC-based computational fluid dynamics software package by Softflo, 2-D numerical simulations of the flow through the cross-flow fan were also obtained. Based on the performance measurements it was concluded that the optimum speed range for this rotor configuration was in the 3,000 to 5,000 rpm range. The lower speed producing the best thrust-to-power ratio and the upper speed range producing the highest efficiency over sizeable throttling range.Publication Stator Averaged, Rotor Blade-to-Blade near Wall Flow in a Multistage Axial Compressor with Tip Clearance Variation(American Society of Mechanical Engineers (ASME), 1991) Moyle, I.N.; Walker, G.J.; Shreeve, R.P.; TurboPropulsion LaboratoryThis paper describes the effect of tip clearance changes on the pressure at the case wall of a second stage rotor. Wall shear distributions under the rotor tip are also presented. The results show low pressure areas extending along the rotor suction side but lying away from the blade. Pressure contours indicate the tangential loading at the tip is lower than predicted by two dimensional calculations, however, the predicted loading is observed between the lowest pressure’s path in the passage and the blade pressure side. The results suggest a viscous or shearing layer, due to blade-to-wall relative motion, is generated on the blade side of the tip gap which modifies the inviscid relative flow field and produces an unloading on the blade tip.Publication Electricity Spikes and the Power of Collaboration(Defense Acquisition University, 2019-03) Gannon, Anthony; Regnier, Eva D.; Taber, Douglass; Graduate School of Business & Public Policy (GSBPP); Graduate School of Engineering and Applied Science (GSEAS); TurboPropulsion LaboratoryLike many Department of Navy Installations, Naval Support Activity Montereyfaces power bills that can change dramatically due to short spikes in electricity demand. Unlike most Navy installations, NSAM hosts an academic institution—the Naval Postgraduate School (NPS), where students and faculty can work closely with Naval Facilities Engineering Command (NAVFAC). At NPS and NSAM, the connections built over years of collaborations formed through the Energy Systems and Technology Evaluation Program (ESTEP) researchhelped save 25 percent on power bills for one of the NPS labs.Publication Report on the September 1980 AIAA Delegation Visit to China(Monterey, CA; Naval Postgraduate School, 1981-01) Shreeve, Raymond P.; TurboPropulsion Laboratory; AeronauticsA complete account is given of the experiences, observations and opinions of one member of a delegation from the American Institute of Aeronautics and Astronautics which visited aeronautics and propulsion activities in China in September 1980. Technical visits to, factories, research institutes and universities in Shanghai, Xian and Beijing are documented in detail. Observations and impressions of the country and the people are included and conclusions are drawn concerning the practicality of technical exchange at the basic research level.