Gas turbine engine with recirculating bleed [PDF]
, 1978 Carbon monoxide and unburned hydrocarbon emissions in a gas turbine engine are reduced by bleeding hot air from the engine cycle and introducing it back into the engine upstream of the bleed location and upstream of the combustor inlet. As this hot inlet
Adamson, A. P.
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Investigation on the Flow Field Entropy Structure of Non-Synchronous Blade Vibration in an Axial Turbocompressor. [PDF]
Entropy (Basel), 2020 Zhang M, Hou A.
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Prediction of axial-flow instabilities in a turbojet engine by use of a multistage compressor simulation on the digital computer [PDF]
A method of estimating the undistorted stall line for an axial-flow compressor by using the digital computer is presented. The method involves linearization of nonlinear dynamic equations about an operating point on a speed line, and then application of ...
Blaha, R. J. +2 more
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AerospaceThe internal losses in the tip clearance region strongly influence the compressor performance and its operational range. Previous research proved that passive wall treatments with circumferential grooves in axial compressors effectively increase the ...
Ruben Bruno Diaz +4 more
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Application of Digital Twins and Metaverse in the Field of Fluid Machinery Pumps and Fans: A Review. [PDF]
Sensors (Basel), 2022 Yang B +4 more
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Effect of steady-state pressure distortion on flow characteristics entering a turbofan engine [PDF]
Flow angle, static-pressure, and total-pressure distributions were measured in the passage ahead of a turbofan engine operating with inlet pressure distortion.
Bobula, G. A., Soeder, R. H.
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Unsteady flows in axial turbomachines [PDF]
, 1957 Of the various unsteady flows that occur in axial turbomachines certain asymmetric disturbances, of wave length large in comparison with blade spacing, have become understood to a certain extent.
Marble, Frank E., Rannie, W. Duncan
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Effect of slotted casing treatment on performance of a multistage compressor [PDF]
A J85-13 engine was equipped with a compressor case that allowed changes to the case wall over the rotor tips of six of its eight stages. The engine was tested with four inlet configurations: uniform inlet flow, 180 degree circumferential distortion, hub
Moss, J. E., Jr.
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Experimental evaluation of outer case blowing or bleeding of single stage axial flow compressor. Part I - Design of rotor and bleeding and blowing configurations [PDF]
Rotor design to evaluate outer case blowing or bleeding of single stage axial flow ...
Griffin, R. G., Smith, L. H., Jr.
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Effect of casing treatment of overall performance of axial-flow transonic fan stage with pressure ratio of 1.75 and tip solidity of 1.5 [PDF]
The effect of a number of casing treatments on the overall performance of a 1.75-pressure-ratio, 423-m/sec-tip-speed fan stage was evaluated. The skewed slot configuration with short-open slots over the midportion of the rotor had a stall margin of 23.5 ...
Moore, R. D., Osborn, W. M.
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