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Experimental Investigation of the Effect of Partial Admission Ratio on the Performance of Supersonic Impulse Turbine  

Jeong, Eun-Hwan (한국항공우주연구원 터보펌프팀)
Park, Pyun-Goo (한국항공우주연구원 터보펌프팀)
Kim, Jin-Han (한국항공우주연구원 터보펌프팀)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.11, no.4, 2007 , pp. 59-66 More about this Journal
Abstract
In this paper, experimental investigation results of the effect of partial admission ratio on the performance of axial turbine was presented. A supersonic impulse turbine of gas generator cycle liquid rocket engine turbopump was used for the test. for experimental purpose, a nozzle block, in which total 14 number of axi-symmetric convergent-divergent nozzles are arranged circumferentially, was designed and manufactured. Partial admission ratio was controlled by changing the number of active nozzles. High pressure air was used as working medium for the test. The experimental result revealed that the performance of the supersonic impulse turbine does not much affected by the partial admission ratio for supersonic impulse turbine.
Keywords
Partial Admission Ratio; Supersonic; Impulse Turbine;
Citations & Related Records
Times Cited By KSCI : 1  (Citation Analysis)
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1 Kurzrock, J. W, 1989, Experimental Investigation of Supersonic Turbine Performance, 89-GT-238, Gas Turbine and Aeroengine Congress and Exposition, June 4-8, 1989, Toronto, Canada, 1989
2 Moffitt, T. P.; Klag, F. W. J., 1959, Experimental Investigation of the Partial Admission Performance characteristics of a Single-Stage Mach 2 Supersonic Turbine, NASA TM X-80, 1959
3 Verneau, A., 1987, Supersonic Turbines for Organic Fluid Rankine Cycles from 3 to 1300kW, VKI Lecture Series 1987-09,1987
4 정은환, 강상훈, 신동윤, 박편구, 김진한, 2006, 터보펌프 터빈의 성능 및 노즐-로터 간극의 영향에 대한 실험적 고찰, 한국추진공학회지, 제10권, 2호, 2006, pp78-86   과학기술학회마을
5 Klassen, H. A., 1968, Cold-Air Investigation of Effects of Partial Admission on Performance of 3.75-Inch Mean-Diameter Single-Stage Axial-Flow Turbine, NASA TND-4700, 1968
6 Horlock, J. H., 1966, Axial Flow Turbines, Krieger Publishing Company, Malabar, Florida, 1966
7 B. V. Ovsyanikov, B. I. Borovsky, Theory and Calculation of Liquid Propellant Rocket Engine Pumps, Mashinostroyenie. Moscow. 1986
8 Eunhwan Jeong, Pyun Goo Park, Sang Hun Kang, Jinhan Kim, 2006, Effect of Nozzle-Rotor Clearance on Turbine Performance, FEDSM2006-98388, 2006 ASME Joint US-European Fluids Engineering Summer Meeting, July 17-20, Miami, Florida, 2006