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Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages IV : modification of aerodynamic design and prediction of performance

Year: 1955
Type: article
Abstract: An eight-stage hi&-pressure-ratio axial-flaw cmpressor, designed for use as a research canpressor, w a s modifiedto improve design-speed performance and to provide an instrument for continued study of the problems associated with desfgn and off-design performance of transonic stages combined vith highly loaded subsanic stages.This canpressor consisted of two transonic W e t stages and six subsonic stages modified to produce a maximum design-speed over-all total-pressure ratio of 10.90 at an equivalent weight flow of 30.0 pounds per square f o o t of rotor frontal area.The cmpressor tip dlameter w a s increased fram 20 to 20.86 inches at the canpressor m e t and decreased linearly to the original 20-inch diameter at the Inlet to the seventh stage.The increase in the inlet tip diameter resulted i4 a first-stage design tip speed of 1218 feet per second, a meximum relative tip &ch n-er of 1.25, and an inlet hub-tip ratio of 0.46.This report also discusses the method used for predicting the performance of the modified comgressor and campares the results of t h i s prediction with the over-all performance of the o r i n i n n f compressor.The use of transonic inlet stages in an axial-flow cmpressor presents a means by w h i c h weight flow per unit frontal area, o r average stage pressure ratio, or both, can be increased.In order to study the problems associated with stagfng transonic inlet stages with highly loaded subsonic s t a g e s , the eight-stage campressor of reference 1 was built and operated as a research unit.The results of the investigation of this compressor (ref.2 ) show that, at design speed, a maxFmum over-all pressure ratio of approximately fr
Language: English
Open Access status: green
OpenAlex ID: W313015340
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Cited by: 1
Related to: 10