Evaluation of range and distortion tolerance for high Mach number transonic fan stages. Task 2: Performance of a 1500-foot-per-second tip speed transonic fan stage with variable geometry inlet guide vanes and stator [PDF]
A 0.5 hub/tip radius ratio compressor stage consisting of a 1500 ft/sec tip speed rotor, a variable camber inlet guide vane and a variable stagger stator was designed and tested with undistorted inlet flow, flow with tip radial distortion, and flow with ...
Bilwakesh, K. R. +2 more
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Propulsion control experience used in the Highly Integrated Digital Electronic Control (HIDEC) program [PDF]
The highly integrated digital electronic control (HIDEC) program will integrate the propulsion and flight control systems on an F-15 airplane at NASA Ames Research Center's Dryden Flight Research Facility.
Burcham, F. W., Jr., Myers, L. P.
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Effects of tip clearance on overall performance of transonic fan stage with and without casing treatment [PDF]
The overall performance of a transonic fan stage is presented for various tip clearances, with and without casing treatment. The stage was tested with a solid casing, and with open skewed slots and closed skewed slots in the casing over the rotor blade ...
Moore, R. D., Osborn, W. M.
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A preliminary evaluation of an F100 engine parameter estimation process using flight data [PDF]
The parameter estimation algorithm developed for the F100 engine is described. The algorithm is a two-step process. The first step consists of a Kalman filter estimation of five deterioration parameters, which model the off-nominal behavior of the engine
Gilyard, Glenn B. +2 more
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Multi-fidelity modelling of a high bypass ratio turbofan engine with variable area nozzle
Propulsion and Power ResearchLow pressure ratio fans of modern civil turbofans suffer from reduced stall margin in the take-off operating line and at part-speed, requiring variable geometry devices.
Andrea Magrini, Ernesto Benini
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Aerodynamic performances of three fan stator designs operating with rotor having tip speed of 337 meters per second and pressure ratio of 1.54. Relation of analytical code calculations to experimental performance [PDF]
A hub-to-shroud and a blade-to-blade internal-flow analysis code, both inviscid and basically subsonic, were used to calculate the flow parameters within four stator-blade rows.
Esgar, G. M. +2 more
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AerospaceThe self-circulating casing treatment can effectively expand the stable working range of the compressor, with little impact on its efficiency. With a single-stage transonic axial flow compressor NASA (National Aeronautics and Space Administration) Stage ...
Haoguang Zhang +4 more
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Axial compressor blades tip leakage flow control using natural aspiration. [PDF]
Sci Rep, 2023 Nejad PG, Zenouz RT.
europepmc +1 more source
Sealing technology for aircraft gas turbine engines [PDF]
Experimental evaluation under simulated engine conditions revealed that conventional mainshaft seals have disadvantages of high gas leakage rates and wear. An advanced seal concept, the self-acting face seal, has a much lower gas leakage rate and greater
Johnson, R. L., Ludwig, L. P.
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Calculated performance of the NASA Lewis icing research tunnel [PDF]
The Icing Research Tunnel is used extensively to test many classes of aircraft under atmospheric icing conditions. Because of the need to test models at higher Reynolds numbers, a new fan rotor was designed to increase test section wind speed.
Viterna, Larry A.
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