A theory of post-stall transients in multistage axial compression systems [PDF]
A theory is presented for post stall transients in multistage axial compressors. The theory leads to a set of coupled first-order ordinary differential equations capable of describing the growth and possible decay of a rotating-stall cell during a ...
Greitzer, E. M., Moore, F. K.
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Gas turbine engine fuel control [PDF]
, 1973 A variable orifice system is described that is responsive to compressor inlet pressure and temperature, compressor discharge pressure and rotational speed of a gas-turbine engine.
Gold, H. S.
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Journal of Applied Fluid Mechanics, 2020 In this paper, a numerical investigation was conducted on a subsonic compressor rotor with blade angle slot casing treatments. The purpose of the investigation is to reveal the influence of axial overlap of blade angle slot on the compressor stability ...
H. Zhang +5 more
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Broadband sound radiated from subsonic rotors [PDF]
Recent theoretical work on sound sources in subsonic turbomachinery is applied to the correlation of axial-flow fan and compressor noise measurements. Correlations are presented for directivity and sound-power spectra associated with broadband noise.
Morfey, C. L.
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Computer program for definition of transonic axial-flow compressor blade rows [PDF]
, 1974 Particular type of blade element used has two segments which have centerlines and surfaces described by constant change of angle with path distance on cone.
Crouse, J. E.
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End-wall boundary layer prediction for axial compressors [PDF]
An integral boundary layer procedure was developed for the computation of viscous and secondary flows along the annulus walls of an axial compressor. The procedure is an outgrowth and extension of the pitch-averaged methods of Mellor and Horlock.
Sockol, P. M.
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Conceptual Design of a Two Spool Compressor for the NASA Large Civil Tilt Rotor Engine [PDF]
, 2010 This paper focuses on the conceptual design of a two spool compressor for the NASA Large Civil Tilt Rotor engine, which has a design-point pressure ratio goal of 30:1 and an inlet weight flow of 30.0 lbm/sec.
Thurman, Douglas R., Veres, Joseph P.
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Axial compressor middle stage secondary flow study [PDF]
This report describes an experimental investigation of the secondary flow within and aft of an axial compressor model with thick endwall boundary layers.
Dring, R. P. +2 more
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Effect of Various Blade Modifications on Performance of a 16-Stage Axial-Flow Compressor. III - Effect on Over-All Performance Characteristics on Increasing Stator-Blade Angles in Inlet Stages [PDF]
, 1952 The stator-blade angles in the first four stages of a 16-stage axial-flow compressor were increased in order to decrease the angles of attack of these stages, and thereby to improve part-speed performance.
Hatch, James E., Medeiros, Arthur A.
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Experimental investigation of the performance of a supersonic compressor cascade [PDF]
Results are presented from an experimental investigation of a linear, supersonic, compressor cascade tested in the supersonic cascade wind tunnel facility at the DFVLR in Cologne, Federal Republic of Germany.
Schreiber, H. A. +2 more
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