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Morrison, G. L.

Publications and source records attributed to Morrison, G. L..

At least 19 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1992

Measured effect of step axial location on labyrinth seal leakage

An advanced, finite volume code has been extensively used in a parametric design study of simple stepped seals, in order to ascertain a leakage-minimizing optimal design and test it, in conjunction with the baseline case of the wear-ring seal of a high pressure pump. It is found that a significant leakage effect arises from this shifting of the rotor and stator sealing surfaces; at extremely low rpm, a significant shaft speed effect occurs for the optimized design in some shaft locations.

Morrison, G. L.↗
NASA NTRS1992

Friction-factor characteristics for narrow channels with honeycomb surfaces

The experimental determination of friction-factors for the flow of air in a narrow channel lined with various honeycomb geometries has been carried out. Test results show that, generally, the friction-factor is nearly constant or slightly decreases as the Reynolds number increases, a characteristic common to turbulent flow in pipes. However, in some test geometries this trend is remarkably different. The friction factor dramatically drops and then rises as the Reynolds number increases. This phenomenon can be characterized as a 'friction-factor jump'. Further investigations of the acoustic spectrum and friction-factor measurements for a broad range of Reynolds numbers indicate that the 'friction-factor jump' phenomenon is accompanied by an onset of a normal mode resonance excited coherent flow fluctuation structure, which occurs at Reynolds number of the order of 10,000. The purpose of this paper is to explain the friction-factor-jump phenomenon and friction-factor characteristics.

Ha, T. W.↗
NASA NTRS1992

Development of the mean velocity distribution in rectangular jets

The mean flowfield of 1 x 2 and 1 x 4 aspect ratio rectangular jets has been measured using a laser Doppler anemometer system. The development of the downstream velocity distribution is analyzed with respect to centerline velocity decay, shear layer growth, axis switching, and velocity profile development. Comparisons are made with axisymmetric, planar, and other rectangular jets.

Morrison, G. L.↗
NASA NTRS1989

Three dimensional flow field measurements of a 4:1 aspect ratio subsonic jet

Flow field measurements for a subsonic rectangular cold air jet with an aspect ratio of 4:1 (12.7 x 50.8 mm) at a Mach number of 0.09 and Re of 100,000 have been carried out using a three-dimensional laser Doppler anemometer system. Mean velocity measurements show that the jet width spreads more rapidly along the minor axis than along the major axis. The outward velocities, however, are not significantly different for the two axes, indicating the presence of enhanced mixing along the minor axis. The jet slowly changes from a rectangular jet to a circular jet as the flow progresses downstream.

Morrison, G. L.↗
NASA NTRS1988

Numerical and experimental evaluation of a new low-leakage labyrinth seal

The effectiveness of a recently developed leakage model for evaluating new design features of most seals is demonstrated. A preliminary assessment of the present stator groove feature shows that it gives approximately a 20 percent leakage reduction with no shaft speed effects. Also, detailed distributions of predicted streamlines, axial velocity, relative pressure and turbulence energy enhance one's physical insight. In addition, the interesting measured effect of axial position of the rotor/stator pair on leakage rate and stator wall axial pressure distribution is examined.

Rhode, D. L.↗
NASA NTRS1988

3-D laser anemometer measurements in a labyrinth seal

The flow field inside a seven cavity labyrinth seal with a 0.00127 m clearance was measured using a 3-D laser Doppler anemometer system. Through the use of this system, the mean velocity vector and the entire Reynolds stress tensor distributions were measured for the first, third, fifth, and seventh cavities of the seal. There was one large recirculation region present in the cavity for the flow condition tested, Re = 28,000 and Ta = 7,000. The axial and radial mean velocities as well as all of the Reynolds stress term became cavity independent by the third cavity. The azimuthal mean velocity varied from cavity to cavity with its magnitude increasing as the flow progressed downstream.

Morrison, G. L.↗
NASA NTRS1988

3-D laser anemometer measurements in an annular seal

The flow field inside an annular seal with a 0.00127 m clearance was measured using a 3-D laser Doppler anemometer system. Through the use of this system, the mean velocity vector and the entire Reynolds stress tensor distributions were measured for the entire length of the seal (0.0373 m). The seal was operated at a Reynolds number of 27,000 and a Taylor number of 6,600.

Morrison, G. L.↗
NASA NTRS1988

Experimental verification of a secondary recirculation zone in a labyrinth seal

The existence of a secondary recirculation zone inside the cavities of a labyrinth seal operating at a Reynolds number of 15,000 and a Taylor number of 10,300 has been experimentally verified. A three-dimensional laser Doppler anemometer system was used to measure the complete mean velocity and Reynolds stress tensor distributions in the first, third, fifth and seventh cavities of a seven cavity labyrinth seal which had a clearance of 1.27 mm.

Morrison, G. L.↗
NASA NTRS1988

Design optimization and testing of a pump wear ring labyrinth seal

It has been demonstrated that design optimization of labyrinth seals using the present numerical model is quite beneficial. The results shown include important, but previously unknown effects on the leakage rate, especially that of step height. Further, complete details are given of a very effective seal designed using this technique for the SSME high pressure hydrogen turbopump. Measurements using turbine flow meters revealed that the optimized configuration gives 67 percent leakage reduction over the original design. These measurements also reveal important leakage effects of the axial straining of the stator, which begins during pump start-up.

Rhode, D. L.↗
NASA NTRS1987

Design improvement of a pump wear ring labyrinth seal

The investigation was successful in obtaining two improved designs for the impeller wear ring seal of the liquid hydrogen turbopump of interest. A finite difference computer code was extensively used in a parametric computational study in determining a cavity configuration with high flow resistance due to turbulence dissipation. These two designs, along with that currently used, were fabricated and tested. The improved designs were denoted Type O and Type S. The measurements showed that Type O and Type S given 67 and 30 percent reduction in leakage over the current design, respectively. It was found that the number of cavities, the step height and the presence of a small stator groove are quite important design features. Also, the tooth thickness is of some significance. Finally, the tooth height and an additional large cavity cut out from the stator (upstream of the step) are of negligible importance.

Rhode, David L.↗
NASA NTRS1987

Effect of shaft rotation on the incompressible flow in a labyrinth seal

The incompressible flow in a labyrinth seal at low leakage rates was computationally and experimentally investigated over a wide range of seal rotation rates. QUICK differencing was employed in the finite difference code to reduce the effects of false diffusion. The use of measured inlet boundary conditions for the axial and swirl velocity components and for the turbulent kinetic energy resulted in good agreement between velocity predictions and hot-film measurements. It was found that when the rotation rate is increased beyond a certain point, a second recirculation zone forms inside the seal cavity, altering the flow field in the cavity and resulting in a substantial increase in the pressure drop across it.

Demko, J. A.↗
NASA NTRS1985

Predicting Leakage in Labyrinth Seals

Analytical and empirical methods evaluated. 264-page report presents comprehensive information on leakage in labyrinth seals. Summarizes previous analyses of leakage, reviews leakage tests conducted by authors and evaluates various analytical and experimental methods of determining leakage and discusses leakage prediction techniques.

Morrison, G. L.↗
NASA NTRS1985

Incompressible flow in stepped labyrinth seals

A steped labyrinth seal was experimentally investigated to determine the effects of pressure ratio, shaft speed, number of teeth, and tooth/step location upon the leakage through the seal for incompressible flow. The dependence of the flow coefficient upon the number of throttles and pressure ratio are similar to those for straight-through labyrinth seals. It can be noted that the axial location of the throttle with respect to the step had a special effect upon the flow coefficient. That is, the dependency of the flow coefficient upon rotation rate and the number of throttles changes with axial location. It was found that the minimum flow coefficient was obtained when the seal teeth were centered on the step surface. Axial pressure distribution measurements show that when the teeth are centered on the step, the pressure drop from cavity to cavity is almost uniform. It is speculated that the obtaining of this uniform pressure gradient is the cause for the enhanced performance of the stepped labyrinth seal when operated in that configuration.

Morrison, G. L.↗
NASA NTRS1984

Phase averaged acoustic measurements for a Mach number 0.6 jet

Acoustic phase (ensemble) averaged measurements were performed in a cold, axisymmetric, Mach number 0.6 jet of air. These measurements show that the noise directly radiated by the coherent structure in the jet flow field was responsible for the directivity of the acoustic field. Comparison of phase averaged acoustic spectra with phase averaged radial velocity fluctuations within the jet illustrate the direct link between the two and show that different regions of the jet are responsible for producing the noise measured at various locations in the acoustic field.

Morrison, G. L.↗
NASA NTRS1984

Frequency dependence of coherent structures in a Mach number 0.6 jet

The existence of a large scale structure in a Mach number 0.6, axisymmetric jet of cold air has been proven by previous work. In order to further characterize the coherent structure, phase averaged measurements of the axial mass velocity, radial velocity, and one component of the Reynolds stress tensor were made. These measured values were compared to the total fluctuation levels for each quantity and the result expressed as a percent of the total fluctuation level contained in the organized structure at Strouhal numbers of 0.16, 0.32, 0.474, 0.95, and 1.26. All of the phase averaged measurements required that the jet be artificially excited. The fluctuation profiles showed that the axial mass velocity fluctuations maximized when excited at a Strouhal number of 0.474. The radial velocity fluctuations possessed a lower amplitude for both the full wave and phase averaged fluctuations than the axial mass velocity fluctuation. The Reynolds stress decayed faster than the other two quantities past the end of the potential core for both the full wave and phase averaged components. The coherence contours showed that the radial velocity fluctuations possessed higher levels of coherence than the axial mass velocity fluctuation and the Reynolds stress.

Morrison, G. L.↗
NASA NTRS1984

Phase average measurements of the coherent structure in a Mach number 0.6 jet

Phase averaged measurements of the axial mass velocity, radial velocity, and the product of the two have been made in an artificially excited cold air jet. The radial velocity fluctuations had a lower amplitude for both the full wave and phase averaged fluctuations compared to the axial mass velocity fluctuations. The Reynolds stress tended to decay faster in amplitude than the axial mass velocity and radial velocity fluctuations for both the full wave and phase averaged components. The radial velocity fluctuations possessed higher levels of coherence than the axial mass velocity fluctuation and the Reynolds stress. When the jet was excited at the frequency of St = 0.474, a high amplitude component at that frequency dominated the entire phase averaged flowfield from X/D = 1 to 10. This fundamental frequency was accompanied by several relatively high amplitude harmonics. These harmonics were more pronounced in the radial velocity fluctuations than for the axial fluctuations or the Reynolds stress.

Emami, S.↗