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Klassen, H. A.

Publications and source records attributed to Klassen, H. A..

13 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1977

Experimental performance of a 13.65-centimeter-tip-diameter tandem-bladed sweptback centrifugal compressor designed for a pressure ratio of 6

A 13.65 cm tip diameter backswept centrifugal impeller having a tandem inducer and a design mass flow rate of 0.907 kg/sec was experimentally investigated to establish stage and impeller characteristics. Tests were conducted with both a cascade diffuser and a vaneless diffuser. A pressure ratio of 5.9 was obtained near surge for the smallest clearance tested. Flow range at design speed was 6.3 percent for the smallest clearance test. Impeller exit to shroud axial clearance at design speed was varied to determine the effect on stage and impeller performance.

Klassen, H. A.↗
NASA NTRS1977

Experimental performance of a 16.10-centimeter-tip-diameter sweptback centrifugal compressor designed for a 6:1 pressure ratio

A backswept impeller with design mass flow rate of 1.033 kg/sec was tested with both a vaned diffuser and a vaneless diffuser to establish stage and impeller characteristics. Design stage pressure ratio of 5.9:1 was attained at a flow slightly lower than the design value. Flow range at design speed was 6 percent of choking flow. Impeller axial tip clearance at design speed was varied to determine effect on stage and impeller performance.

Klassen, H. A.↗
NASA NTRS1975

Effect of inducer inlet and diffuser throat areas on performance of a low pressure ratio sweptback centrifugal compressor

A low-pressure-ratio centrifugal compressor was tested with nine combinations of three diffuser throat areas and three impeller inducer inlet areas which were 75, 100, and 125 percent of design values. For a given inducer inlet area, increases in diffuser area within the range investigated resulted in increased mass flow and higher peak efficiency. Changes in both diffuser and inducer areas indicated that efficiencies within one point of the maximum efficiency were obtained over a compressor specific speed range of 27 percent. The performance was analyzed of an assumed two-spool open-cycle engine using the 75 percent area inducer with a variable area diffuser.

Klassen, H. A.↗
NASA NTRS1973

Performance of a low-pressure-ratio centrifugal compressor with four diffuser designs

A low-pressure-ratio centrifugal compressor was tested with four different diffuser configurations. One diffuser had airfoil vanes. Two were pipe diffusers. One pipe diffuser had 7.5 deg cone diffusing passages. The other had trumpet-shaped passages designed for linear static-pressure rise from throat to exit. The fourth configuration had flat vanes with elliptical leading edges similar to those of pipe diffusers. The side walls were contoured to produce a linear pressure rise. Peak compressor efficiencies were 0.82 with the airfoil vane and conical pipe diffusers, 0.80 with the trumpet, and 0.74 with the flat-vane design. Surge margin and useful range were greater for the airfoil-vane diffuser than for the other three.

Klassen, H. A.↗
NASA NTRS1972

Analytical investigation of conical diffusers

A study was made to determine if existing data for straight-channel single-plane divergence diffusers together with boundary-layer methods could be practically employed to predict conical diffuser performance in the high-speed flow regime. A semiempirical correlation technique, which uses the experimental performance of a straight-channel single-plane divergence diffuser, and a momentum integral boundary-layer method were employed to predict conical diffuser performance. Neither of these methods is applicable when the boundary layer separates. The momentum integral method was used to study the relative importance of various boundary layer parameters in correlating unstalled diffuser performance. Other investigators have found that the best diffuser performance occurs when the diffuser is operating in the transitory stall regime. Since the analytical methods presented in this report are not applicable after the point of boundary-layer separation, a criterion was established from examination of experimental tests which allows the designer to ascertain approximate diffuser performance in the transitory stall regime.

Means, J. L.↗
NASA NTRS1969

Electronic visualization of gas bearing behavior

Visualization technique produces a visual simulation of gas bearing operation by electronically combining the outputs from the clearance probes used to monitor bearing component motion. Computerized recordings of the probes output are processed, displayed on an oscilloscope screen and recorded with a high-speed motion picture camera.

Evans, R. C.↗