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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Experimental data and performance of honeycomb rotor shroud configuration to improve stall margin of 0.5 hub tip ratio single stage compressor
Flow distribution data for solid and honeycomb rotor shrouds to improve stall margin of 0.5 hub tip ratio single stage compressor
Cost analysis of turbofan nacelle modifications to minimize fan-compressor noise radiation
Flight acoustical and performance evaluations of DC 8 nacelle modifications to reduce fan-compressor noise in airport communities
Development of acoustic lining for turbofan nacelle modification to minimize fan compressor noise radiation
Thermal pump-compressor for converting solar energy
Flightworthy nacelle development to minimize fan compressor noise radiation - Vol. 4
Performance of axial flow compressor for Brayton cycle electrical power generating system with argon
Aerodynamic broadband noise mechanism applicable to axial compressors
Characteristics of fans and compressors for aircraft turbine engines
Efficiency estimates of turbine and compressor components of Brayton rotating unit during hot closed loop operation
Performance tests of compressor seals and stator pivot seals used with air breathing propulsion systems - Part 2
Performance tests and efficiency measurement of hub-slit-suction stator in single stage compressor
Output format coding for telemetry data compressor channel and frame identification
Several geometrically different porous casings were tested with an axial-flow compressor rotor to determine their effects upon the rotor stall-limit line and overall performance. The tests were conducted using both uniform and nonuniform inlet-flow conditions. The rotor performance with the various casing treatments is compared with that obtained with a solid casing. The ability of the various casing treatments to displace the rotor stall-limit line to lower weight flows was observed. Significant stall-margin increases were obtained with several of the porous casings. Peak efficiencies with two of the porous casings were as high as or slightly higher than that obtained with solid casing.
A 9.4-centimeter (3.7-in.) diameter six-stage axial-flow compressor was tested in argon over a range of inlet pressures corresponding to a Reynolds number range of 30,600 to 160,000. The effect of Reynolds number on efficiency, pressure ratio, work input, maximum flow, and surge is shown. The Reynolds number effects are discussed in terms of changes in boundary-layer thickness, losses, and the resulting changes in throughflow velocity. Significant deviation was noted from the 0.2 power relation often used to express the variation of loss with Reynolds number.
Experiments are described which demonstrated the feasibility of rapidly compressing inert gases in a ballistic piston compressor to simultaneously high temperatures and densities previously unobtainable in the laboratory. With argon, temperatures of the order of 6000 K and accompanying densities of the order of 100 Amagats have been obtained; and with nitrogen, temperatures and densities of 3000 K and 400 Amagats have been approached. Details of the design, assembly, instrumentation, and operating procedures are presented, and the results of mechanical and thermal performance tests up to 5000 atmospheres pressure are described. Emphasis is placed on experiments which demonstrated the usefulness of this apparatus for spectral line broadening studies.
A single-stage compressor with a rotor tip speed of 1600 ft/sec and a 0.5 hub tip ratio was used to investigate the effects of several stator endwall treatment methods on stage range and performance. These endwall treatment methods consisted of stator corner-blow, annular wall suction upstream of stator leading edge, and combined corner-blow and annular wall suction. The overall stage performance with corner blow was essentially the same as the baseline performance. The performance for the annular wall suction and the combined corner-blow and wall suction showed a reduction in peak efficiency of 2.5 percentage points compared to the baseline data.