Research turbine and compressor equipment progress report, aug. 1964
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Research turbine and compressor equipment progress report, sep. 1964
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Research turbine and compressor equipment progress report, nov. 1964
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Research turbine and compressor equipment progress report, may 1964
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Research turbine and compressor equipment progress report, dec. 1964
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Development of compressor end seals, stator interstage seals, and interior pivot seals in advanced air breathing propulsion systems Semiannual report, 30 Jun. - 31 Dec. 1968
Design and performance of seal test equipment
Hawkins, R. M.↗
Theoretical studies of compressor noise
Theoretical study of discrete frequency noise generated by turbocompressors and blades
Lowson, M. V.↗
Multistage compressor simulation applied to the prediction of axial flow instabilities
Multistage turbocompressor simulation applied to performance prediction of axial flow instabilities
Seldner, K.↗
Gas turbine combustor insensitive to compressor outlet distortion
Short-length annular combustor for turbojet engines eliminates change of exit temperature profile. Individual scoops of full annular height control air distribution so that shifts in the radial velocity profile of air entering the combustor will not affect combustion process or alter exit temperature profile.
Humenik, F.↗
Exact solution for radiation of sound from a semi-infinite circular duct with application to fan and compressor noise
Mathematical model for investigating radiation of noise generated by rotating blades in circular duct
Lansing, D. L.↗
An application of theory to axial compressor noise
Mathematical model of aircraft turbocompressor noise
Munch, C. L.↗
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.↗
Split stator vane row for fans and compressors
Operating noise of fans is reduced by adding part span vanes to vane row of stator, reducing the number of full span vanes and maintaining a vane-to-blade ratio of about 2 to 1.
Volk, L. J.↗
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
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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
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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
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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.↗