Effect of inlet swirl on the performance of annular diffusera having the same equivalent cone angle

Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering

Volumn 220, Issue 2, 2006, Pages 129-143

  Singh, S N ^a   Seshadri, V ^a   Saha, K ^a   Vempati, K K ^a   Bharani, S ^b  

^a INDIAN INSTITUTE OF TECHNOLOGY DELHI   (India)

^b UNIVERSITY OF CENTRAL FLORIDA   (United States)

Author keywords

Annular diffuser; Equivalent cone angle; Gas turbine engine; Inlet swirl; Static pressure recovery coefficient; Total pressure loss coefficient

Indexed keywords

AIRCRAFT; COMPUTATIONAL GEOMETRY; DIFFUSERS (FLUID); GAS TURBINES; SWIRLING FLOW;

ANNULAR DIFFUSER; EQUIVALENT CONE ANGLE; GAS TURBINE ENGINE; INLET SWIRL; STATIC PRESSURE RECOVERY COEFFICIENT; TOTAL PRESSURE LOSS COEFFICIENT;

INTAKE SYSTEMS;

EID: 33947576600     PISSN: 09544100     EISSN: None     Source Type: Journal    
DOI: 10.1243/09544100G05004     Document Type: Article

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