Nasa Technical Note

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Effects Of Diffusion Factor Aspect Ratio And Solidity On Overall Performance Of 14 Compressor Middle Stages

Author: Werner R. Britsch
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File Size: 55,15 MB
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Nasa Technical Note

Author: United States. National Aeronautics and Space Administration
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File Size: 10,90 MB
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Mission Oriented R D And The Advancement Of Technology

Author: Martin D. Robbins
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File Size: 20,47 MB
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Overall And Blade Element Performance Of A 1 20 Pressure Ratio Fan Stage At Design Blade Setting Angle

Author: George W. Lewis (Jr.)
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File Size: 43,95 MB
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Overall And Blade Element Performance Of A 1 20 Pressure Ratio Fan Stage With Rotor Blades Reset 5

Author: George W. Lewis (Jr.)
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A 51-cm-diam model of a fan stage for a short haul aircraft was tested in a single stage-compressor research facility. The rotor blades were set 5 deg toward the axial direction (opened) from design setting angle. Surveys of the air flow conditions ahead of the rotor, between the rotor and stator, and behind the stator were made over the stable operating range of the stage. At the design speed of 213.3 m/sec and a weight flow of 31.5 kg/sec, the stage pressure ratio and efficiency were 1.195 and 0.88, respectively. The design speed rotor peak efficiency of 0.91 occurred at the same flow rate.

A Collection Of Technical Papers

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Performance Of Low Pressure Ratio Low Tip Speed Fan Stage With Blade Tip Solidity Of 0 65

Author: George Kovich
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File Size: 48,99 MB
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The overall and blade-element performance of a low pressure ratio, low tip speed fan stage is presented over the stable operating range at rotative speeds from 90 to 120 percent of design speed. Stage peak efficiency of 0.927 was obtained at a weight flow of 32.4 kg sec (190.31 kg sec sq m of annulus area) and a pressure ratio of 1.134. The stall margin at design speed and peak efficiency was 15.3 percent.

Performance Of A 1 15 Pressure Ratio Axial Flow Fan Stage With A Blade Tip Solidity Of 0 5

Author: Walter Martin Osborn
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File Size: 50,40 MB
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Sae Quarterly Transactions

Author: Society of Automotive Engineers
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File Size: 60,31 MB
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Centrifugal Compressors

Author: SAE Powerplant Activity Committee
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File Size: 53,32 MB
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Performance Prediction And Preliminary Design Of Wave Rotors Enhancing Gas Turbine Cycles

Author: Pezhman Akbari
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File Size: 59,54 MB
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Paper

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Two Stage Fan 2 Data And Performance With Redesigned Second Stage Rotor Uniform And Distorted Inlet Flows

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File Size: 29,78 MB
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Design And Performance Of A High Pressure Ratio Highly Loaded Axial Flow Transonic Compressor Space

Author: George W. Lewis (Jr.)
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File Size: 65,44 MB
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Rotor Tip Clearance Effects On Overall And Blade Element Performance Of Axial Flow Transonic Fan Stage

Author: Royce D. Moore
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File Size: 13,63 MB
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Sae Technical Paper Series

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File Size: 62,39 MB
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Online version: Technical papers portion of the SAE Digital Library references thousands of SAE Technical Papers covering the latest advances and research in all areas of mobility engineering including ground vehicle, aerospace, off-highway, and manufacturing technology. Sample coverage includes fuels and lubricants, emissions, electronics, brakes, restraint systems, noise, engines, materials, lighting, and more. Your SAE service includes detailed summaries, complete documents in PDF, plus document storage and maintenance

Analysis Of An Advanced Technology Subsonic Turbofan Incorporating Revolutionary Materials

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Reports And Memoranda

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Beginning with no. 650 each hundredth number contains a list of the Reports and memoranda published since the last list.

Technical Report

Author: Aeronautical Research Council (Great Britain)
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Includes its Reports, which are also issued separately.