An application of theory to axial compressor noise
Mathematical model of aircraft turbocompressor noise
Munch, C. L.↗
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Some observations of effects of porous casings on operating range of a single axial-flow compressor rotor
Test results of single axial flow with several porous outer casings
Bailey, E. E.↗
Study and development of turbofan nacelle modifications to minimize fan-compressor noise radiation. Volume 3 - Concept studies and ground tests Contractor report, 1 May 1967 - 1 Nov. 1969
Noise reduction of Boeing 707 during landing approach by modifying turbofan nacelle with polyimide fiber glass acoustic sandwich materials
Source record↗
Study and development of turbofan nacelle modifications to minimize fan-compressor noise radiation. Volume 5 - Sonic inlet development Contractor report, 1 May 1967 - 1 Nov. 1969
Static tests to determine effects of throat inlet concepts on forward-radiated fan noise of 707-320B/C airplanes
Source record↗
Study and development of turbofan nacelle modifications to minimize fan-compressor noise radiation. Volume 7 - Subjective evaluation tests Contractor report, 1 May 1967 - 1 Nov. 1969
Subjective evaluation tests of ground observers on relative noise from acoustically treated engine nacelles of Boeing 707 aircraft
Source record↗
Data compressor Patent
Description of system for recording and reading out data related to distribution of occurrence of plurality of events
Anderson, T. O.↗
Development of compressor end seals stator interstage seals, and stator pivot seals in advanced air breathing propulsion systems. Part 1: Screening studies and analysis
Design and characteristics of 28-inch diameter seals for air breathing propulsion systems - Part 1
Hawkins, R. M.↗
FORTRAN program for calculating velocities in the meridional plane of a turbomachine 1: Centrifugal compressor
The program will determine the velocities in the meridional plane of a backward-swept impeller, a radial impeller, and a vaned diffuser. The velocity gradient equation with the assumption of a hub-to-shroud mean stream surface is solved along arbitrary quasi-orthogonals in the meridional plane. These quasi-orthogonals are fixed straight lines.
Vanco, M. R.↗
Digital slope-threshold data compressor
Slope-threshold compression scheme for telemetered video data is efficient, and its principle of operation is as follows: when slope of raw data exceeds threshold decision reference, previous sample is transmitted. All-digital design is more economical than analog system. It exhibits well-defined accuracy, provides unlimited storage time, and is convenient and reliable.
Anderson, T. O.↗
Transient analysis of energy Transfer Control (ECT) and compressor bleed concepts of remote lift fan control
The transient performance of two concepts for control of vertical takeoff aircraft remote lift fans is analyzed and discussed. Both concepts employ flow transfer between pairs of lift fans located in separate parts of the aircraft in order to obtain attitude control moments for hover and low-speed flight. The results presented are from a digital computer, dynamic analysis of the YJ97/LF460 remote drive turbofan. The transient responses of the two systems are presented for step demands in lift and moment.
Sellers, J. F.↗
Steady state analysis of Energy Transfer Control (ETC) and compressor bleed concepts of remote lift fan control
Two new concepts of control for VTOL aircraft remote lift fans are analyzed and discussed. Both concepts employ flow transfer among lift fans located in separate parts of the aircraft in order to obtain attitude control moments in hover and low-speed flight. The results presented are from a digital computer analysis of the YJ97/LF460 remote drive turbofan, although qualitative conclusions should apply to any remote fan system. The basic operating principles of the two systems are described, and their steady-state moment generating capabilities are discussed. Lift-recovery strategies for component failures are also analyzed.
Sellers, J. F.↗
The variable-pitch supersonic inflow compressor and its application in a hypersonic engine
Explore the source record for details and available documents.
Boxer, E.↗
An experimental investigation of compressor stall using an on-line distortion indicator and signal conditioner
The relation of the steady-state and dynamic distortions and the stall margin of a J85-13 turbojet engine was investigated. A distortion indicator capable of computing two distortion indices was used. A special purpose signal conditioner was also used as an interface between transducer signals and distortion indicator. A good correlation of steady-state distortion and stall margin was established. The prediction of stall by using the indices as instantaneous distortion indicators was not successful. A sensitivity factor that related the loss of stall margin to the turbulence level was found.
Costakis, W. G.↗
Gas boost compressor
Device, driven by low pressure gas supply, requires fewer controls and valves than conventional devices. Device can boost compression four times initial pressure.
Terp, L. S.↗
Small axial compressor technology, volume 2
Complete computer printout data are presented and supporting tests discussed in Volume I.
Holman, F. F.↗
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.↗
Evaluation of a low aspect ratio small axial compressor stage, volume 2
For abstract, see N78-12081.
Sawyer, C. W., III↗
Experimental studies on the influence of the degree of turbulence and of a turbulence thread on the compressible subsonic flow through flat compressor cascades
The measurements revealed that at low Reynolds numbers the profile loss is considerably reduced both by the increased degree of turbulence and by a turbulence thread, while it is somewhat increased at high Reynolds numbers, and that a profile loss reduction is connected with an increase in deflection and in pressure shift. The turbulence generator is most effective on the one hand in the middle of the operating range of the cascades, and on the other at very high Mach numbers together with a large angle of incidence.
Barsun, K.↗