Low tip speed fan noise demonstration program
Noise level data for low tip speed turbofan engine
Benzakein, M. J.↗
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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.↗
Potential flow solutions for inlets of VTOL lift fans and engines
Potential flow solution for VTOL inlets in static and crossflow operation
Stockman, N. O.↗
The effect of inlet temperature distortion on the performance of a turbo-fan engine compressor system
Inlet temperature distortion effect on performance of turbofan engine compressor systems
Antl, R. J.↗
Condensers and boilers for steam-powered cars - A parametric analysis of their size, weight, and required fan power
Size, weight, and performance of conventional condensers and boilers for steam-powered cars
Strack, W. C.↗
The effect of inlet temperature distortion on the performance of a turbo-fan engine compressor system
Turbofan engine compressor system performance dependence on circumferential extent, magnitude and rate of change of inlet temperature in altitude test facility
Antl, R. J.↗
Performance of noise suppressors for a full- scale fan for turbofan engines
Performance of noise suppressors for turbofan engines
Rice, E. 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
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↗
Large-scale wind tunnel investigation of a ducted fan - Deflected-slipstream model with an auxiliary wing
Wind tunnel investigation of longitudinal aerodynamic characteristics of semispan wing deflected-slipstream configuration with double slotted flap and auxiliary wing
Falarski, M. D.↗
Evaluation of range and distortion tolerance for high Mach number transonic fan stages, volume 2 Final report
Computer output tables for performance tests of single stage, transonic compressor for advanced aircraft
Bilwakesh, K. R.↗
Evaluation of range and distortion tolerance for high Mach number transonic fan stages, volume 1 Final report
Performance tests of single stage, transonic compressor for advanced aircraft
Bilwakesh, K. R.↗
Results of Prop-Fan/STOL wing acoustics tests
Noise characteristics of model STOL wing with externally blown flaps in vicinity of aircraft propulsor
Ganger, T. G.↗
Performance of a modular combustor designed for a VTOL tip-turbine lift fan
Combustion efficiency and performance of swirl can modules under conditions simulating operation of 10,000 pound thrust lift engine for vertical takeoff
Marchionna, N. R.↗
Performance of noise suppressors for a full- scale fan for turbofan engines
Turbofan engine noise reduction, using acoustic liners in inlet and exhaust ducts
Rice, E. J.↗
Design of aircraft turbine fan drive gear transmission system
The following basic types of gear reduction concepts were studied as being feasible power train systems for a low-bypass-ratio, single-spool, geared turbofan engine for general aircraft use: (1) single-stage external-internal reduction, (2) gears (offset shafting), (3) multiple compound idler gear system (concentric shafting), and (4) star gear planetary system with internal ring gear final output member (concentric shafting-counterrotation). In addition, studies were made of taking the accessories drive power off both the high-speed and low-speed shafting, using either face gears or spiral bevel gears. Both antifriction and sleeve-type bearings were considered for the external-internal and star-planet reduction concepts.
Dent, E.↗
Highly loaded multi-stage fan drive turbine: Plain blade configuration design
The constant-inside-diameter flowpath was scaled for testing in an existing turbine test facility. Blading detailed design is discussed, and design data are summarized. Predicted performance maps are presented. Steady-state stresses and vibratory behavior are discussed and the results of the mechanical design analysis are presented.
Evans, D. C.↗
Highly loaded multi-stage fan drive turbine: Leaned stator configuration design
The results of the high lift blade configuration design study are reported. The three-stage constant-inside-diameter turbine utilizes a ten degree tangentially leaned stator in stage three. All other bladerows use plain blades. Analysis of the leaned stator is discussed, and detailed design data are summarized. Steady-state stresses are discussed, and the results of the mechanical design analysis are presented.
Evans, D. C.↗