The test performance of highly loaded turbine stages designed for high pressure ratio

dc.contributor.author	I. H. Johnston	en_US
dc.contributor.author	D. C. Dransfield	en_US
dc.date.accessioned	2014-10-21T15:55:31Z
dc.date.available	2014-10-21T15:55:31Z
dc.date.issued	1959	en_US
dc.identifier.other	ARC/R&M-3242	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/3816
dc.description.abstract	A blade design for a highly loaded two-stage turbine is described and the test performance of the turbine is presented. Some of the factors affecting the performance and matching of turbine blade rows operating at supersonic gas velocity are discussed and investigated by means of tests on a three-dimensional nozzle cascade tunnel and on a variety of single-stage turbine builds.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Reports & Memoranda	en_US
dc.title	The test performance of highly loaded turbine stages designed for high pressure ratio	en_US