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Design of 9.271-pressure-ratio 5-stage core compressor and overall performance for first 3 stagesOverall aerodynamic design information is given for all five stages of an axial flow core compressor (74A) having a 9.271 pressure ratio and 29.710 kg/sec flow. For the inlet stage group (first three stages), detailed blade element design information and experimental overall performance are given. At rotor 1 inlet tip speed was 430.291 m/sec, and hub to tip radius ratio was 0.488. A low number of blades per row was achieved by the use of low-aspect-ratio blading of moderate solidity. The high reaction stages have about equal energy addition. Radial energy varied to give constant total pressure at the rotor exit. The blade element profile and shock losses and the incidence and deviation angles were based on relevant experimental data. Blade shapes are mostly double circular arc. Analysis by a three-dimensional Euler code verified the experimentally measured high flow at design speed and IGV-stator setting angles. An optimization code gave an optimal IGV-stator reset schedule for higher measured efficiency at all speeds.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Steinke, Ronald J.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 5, 2013
Publication Date
May 1, 1986
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NAS 1.60:2597
Accession Number
Distribution Limits
Work of the US Gov. Public Use Permitted.
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