2 edition of Laser anemometer measurements in a transonic axial-flow fan rotor found in the catalog.
Laser anemometer measurements in a transonic axial-flow fan rotor
by National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, For sale by the National Technical Information Service] in [Washington, D.C.], [Springfield, Va
Written in English
|Statement||Anthony J. Stazisar ... [et al.].|
|Series||NASA technical paper -- 2879.|
|Contributions||Strazisar, Anthony J., United States. National Aeronautics and Space Administration. Scientific and Technical Information Division.|
|The Physical Object|
|Number of Pages||213|
American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Past researches have studied the stator blade guide vane angle implementation respective to the rotor blade angle. And outlet guide vane is recommended to encounter the air swirl problem occurs in the axial flow fan compared to inlet guide vane. This paper presents an investigation on the distance between rotor-stator for an outlet guide vane with fixed stator : Kannan M. Munisamy, Ramies Govindasamy, Savithry K. Thangaraju.
Modern aircraft engines must accommodate inflow distortions entering the engines as a consequence of modifying the size, shape, and placement of the engines and/or nacelle to increase propulsive efficiency and reduce aircraft weight and drag. It is important to be able to predict the interactions between the external flow and the fan early in the design by: 1. Axial Flow Turbines For Process, Subsea and Hydraulic Applications. Axial turbines can be likened and tend to look like marine propellers housed in a tube which is the flowmeters body. Instead of being driven, they rotate freely with the flow of fluid as it passes over them.
Full text of "NASA Technical Reports Server (NTRS) Bibliography of Lewis Research Center Technical Publications announced in " See other formats. The resulting prototype, a high-efficiency, axial flow pump will be placed into beta testing service at various sites across the country. There are 6 main objectives to be achieved in this project. The objectives are: 1. Develop Phase I design into Phase II design .
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A laser fringe anemometer has been used to survey the flowfield upstream, within, and downstream of NASA ro a low-aspect-ratio transonic axial-flow fan rotor. Laser anemometer surveys were made of the flowfield for operating conditions near peak efficiency and near stall.
The fan tip relative Mach number was The rotor was. Laser anemometer surveys were made of the 3-D flow field in NASA ro a low aspect ratio transonic axial-flow fan rotor.
The test rotor has a tip relative Mach number of tem to a transonic axial-flow compressor rotor. The results of several types of measurements which demon- strate the systen's capability of measuring velocity and flow angle in a rotating blade row are discussed.
However a comprehensive evaluation of the flow in this transonic compressor is beyond the scope of the present paper. Get this from a library. Laser anemometer measurements in a transonic axial-flow fan rotor. [Anthony J Strazisar; United States. National Aeronautics and Space Administration.
Scientific and Technical Information Division.;]. A laser anemometer system employing an efficient data acquisition technique has been used to make measurements upstream, within, and downstream of the compressor rotor. A fluorescent dye technique allowed measurements within endwall boundary by: Unsteady flows in a single-stage transonic axial-flow fan stator row Michael Dale Hathaway Figure Illustration showing laser anemometer measurements of the vortex street character of n Number of measurements or rotor shaft position Nrp Number of surveyed rotor passages.
Detailed laser anemometer measurements were acquired upstream, within, and downstream of a transonic, axial compressor rotor operating at85, 80, and 60 percent of design speed, which provided inlet relative Mach numbers at the blade tip of,andby: I read the Nasa report "Laser Anemometer Measurements in a Transonic Axial Flow Fan Rotor" that is about NASA rotor 67 and it has a lot of data about the 3D geometry about this blade,and I tried to produce the 3D geometry of this blade that I need it immediately but I couldn't.
A theory for base pressures in transonic and supersonic flow / (Urbana, Ill.: Mechanical Engineering Dept., Univ. of Illinois, ), by Helmut Hans Korst, M. Childs, R. Page, and University of Illinois (Urbana-Champaign campus).
Engineering Experiment Station (page images at. Dunker, R.J.; Flow Measurements in the Stator Row of a Single-Stage Transonic Axial-Flow Compressor with Controlled Diffusion Stator Blades. AGARD CPPa Google Scholar Author: Alexander Wiedermann. This paper deals with the experimental quantification of the unsteady effects of the interactions between rotor and stator rows in high speed compressors.
Due to the fact that the levels of the periodic fluctuations arising from the unsteady interaction may be low compared with the random fluctuations arising from the measurement uncertainties, it is crucial to minimize the errors inherent to Cited by: Advocacy 1.
Barta, D. and Ewert, M., "Life Support System Technology Development for Exploration Missions," 2. Carrasquillo, R. L., "ISS ECLSS Technology. Figure 1 illustrates the LSCC impeller and the locations of laser-anemometer measurements.
The upper part of Figure 2 shows results of velocity measurements taken at the percent meridional chord position, indicating the extent of the through-flow-velocity deficit characteristic of. Effect of simulated downstream flow blockage doors on the performance of an axial-flow fan rotor, (Washington, Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of andLaser anemometer measurements in an annular cascade of core turbine vanes and comparison with theory /.
Hi, If anybosdy has NASA Rotor 67 geometry in soft copy, data poins. Kidly send me at [email protected] Regards, nasa rotor 67 or 37 geometry - Page 2 -- CFD Online Discussion Forums. Today's high efficiency transonic axial flow compressors for civil aviation give a total pressure ratio in the order of –, realized by combining high rotor speeds (tip speed in the order of m/s) and high stage loading (2Δh/u 2 in the order of ).
The rotor blade aspect ratio parameter showed a general trend towards lower values Cited by: Chima RV and Strazisar AJ. Comparison of two and three dimensional flow computations with laser anemometer measurements in a transonic compressor rotor. In: ASME international gas turbine conference and exhibit, London, UK,p.
VT01A Google ScholarCited by: 3. The rotor consists of 8 blades witii tip diameter of mm and hub to tip ratio The rotor blades, which are made of polypropylene and fiberglass, have N A C A 65 series compressor blade sections with a chord / of 62 mm at the tip.
The rotor nominal speed is rpm, giving an inlet Reynolds number at the design point Re = / / v = 10^.Cited by: 1. Full text of "NASA Technical Reports Server (NTRS) Bibliography of Lewis Research Center technical publications announced in " See other formats.
Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of andrespectively, and with design pressure ratio of Comparison of two- and three-dimensional flow computations with laser anemometer measurements in a transonic compressor WINCOF-I code for prediction of fan.
"Axial Flow Fan Tip Leakage Flow Control Using Tip Platform Extensions,"(with Akturk) Transactions of the ASME, Journal of Fluids Engineering, MayVol, pp " Computational Shape Design of a Radar Antenna Used for Airport Ground Traffic Control," (with Gumusel) in Progress in Computational Fluid Dynamics, Vol, No.1,  Strazisar A J., et al., Laser anemometer measurements in a transonic axial-flow fan rotor, -NASATechnical Paper (NASA TP), آمار تعداد مشاهده مقاله: Author: اکرم جهانبخشی, افشین احمدی ندوشن.The axial flow fan also achieves high efficiency at an op timum blade setting and is only slightly lower than that ob tained with the backwardly inclined airfoil centrifugal fan.
For all other centrifugal fan blade types, peak efficiencies fall gen erally in the range of 70 to 80 percent. CONTROL OF FAN OUTPUT.