Effect of Blade-surface Finish on Performance of a Single-stage Axial-flow Compressor

A set of modified NACA 5509-34 rotor and stator blades was investigated with rough-machine, hand-filed, and highly polished surface finishes over a range of weight flows at six equivalent tip speeds from 672 to 1092 feet per second to determine the effect of blade-surface finish on the performance of a single-stage axial-flow compressor. Surface-finish effects decreased with increasing compressor speed and with decreasing flow at a given speed. In general, finishing blade surfaces below the roughness that may be considered aerodynamically smooth on the basis of an admissible-roughness formula will have no effect on compressor performance

SOME RESULTS OF NASA-IOWA STATE UNIVERSITY RESEARCH ON AXIAL-FLOW PUMPS

INTRODUCTION This paper is a commentary on a small chapter in the recent history of turbomachinery research. It was written to describe the positive influence of an individual, Melvin J. Hartmann, working in a federal research center, on a particular university research program. However, in its final form, it cannot help but shed some light on the longterm effects of small-scale mission-oriented, federal agency funding of engineering research in universities. Secondarily, it will recall a series of experimental investigations of axial-flow pump configurations which produced data of possible relevance to current compressor and pump problems

NACA Research Memorandums

Report presenting an investigation in which the inlet-guide-vane setting of a 10-stage compressor was reduced in order to approximate more closely the design absolute entrance flow angles to the first rotor. In order to determine the effects of these changes, the performance of the inlet stage was obtained simultaneously with the overall compressor performance for both the original and reduced incidence angles. Results regarding the compressor performance, inlet-stage performance, and effect of guide-vane resetting on compressor performance are provided

NACA Research Memorandums

Report presenting an investigation to determine some of the basic problems and effects involved in a change of solidity accomplished by a change in the number of blades in an axial-flow-compressor rotor row and in a complete stage. Results regarding rotor performance and complete stage performance are provided

NACA Research Memorandums

A set of modified NACA 5509-34 rotor and stator blades was investigated with rough-machine, hand-filed, and highly polished surface finishes over a range of weight flows at six equivalent tip speeds from 672 to 1092 feet per second to determine the effect of blade-surface finish on the performance of a single-stage axial-flow compressor. Surface-finish effects decreased with increasing compressor speed and with decreasing flow at a given speed. In general, finishing blade surfaces below the roughness that may be considered aerodynamically smooth on the basis of an admissible-roughness formula will have no effect on compressor performance