| dc.contributor.author | Seidel, Barry S. (Barry Stanley) | en_US |
| dc.contributor.other | Massachusetts Institute of Technology. Gas Turbine Laboratory | en_US |
| dc.date.accessioned | 2016-10-06T21:21:51Z | |
| dc.date.available | 2016-10-06T21:21:51Z | |
| dc.date.issued | 1959 | en_US |
| dc.identifier.uri | http://hdl.handle.net/1721.1/104671 | |
| dc.description | May 1959 | en_US |
| dc.description | Includes bibliographical references (leaves 53-55) | en_US |
| dc.description.abstract | A modified actuator disc analysis is made which, through an improved prediction of the blade forces, attempts to give closer correspondence with experiment than the previous theory. The fluid is assumed inviscid and incompressible. Perturbations to the two-dimensional flow through an isolated blade row are considered. The steady flow equations of motion and continuity are linearized. According to experiments conducted on an isolated compressor rotor, the present theory offers an improvement, compared to previous theory, in the prediction of distortion attenuation, effects of flow rate, and effects of varying chord/spacing ratio. | en_US |
| dc.description.sponsorship | Under the Sponsorship of: General Electric Company, Westinghouse Electric Corporation and Allison Division of General Motors Corporation | en_US |
| dc.format.extent | 55, [46] leaves | en_US |
| dc.publisher | Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, 1959 | en_US |
| dc.relation.ispartofseries | GTL report #51 | en_US |
| dc.subject.lcc | TJ267.A1 M37 no.51 | en_US |
| dc.subject.lcsh | Turbomachines -- Fluid dynamics | en_US |
| dc.subject.lcsh | Rotors | en_US |
| dc.title | Asymmetric inlet flow in axial turbomachines | en_US |
| dc.type | Technical Report | en_US |
| dc.identifier.oclc | 09162313 | en_US |
