International Journal of Fluid Machinery and Systems

Korean Society for Fluid machinery (한국유체기계학회)
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Design and Analysis of a Controlled Diffusion Aerofoil Section for an Axial Compressor Stator and Effect of Incidence Angle and Mach No. on Performance of CDA

  • Received : 2009.09.13
  • Accepted : 2009.10.14
  • Published : 2010.03.01
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Abstract

This paper deals with the Design and Analysis of a Controlled Diffusion Aerofoil (CDA) Blade Section for an Axial Compressor Stator and Effect of incidence angle and Mach No. on Performance of CDA. CD blade section has been designed at Axial Flow Compressor Research Lab, Propulsion Division of National Aerospace Laboratories (NAL), Bangalore, as per geometric procedure specified in the U.S. patent (4). The CFD analysis has been performed by a 2-D Euler code (Denton's code), which gives surface Mach No. distribution on the profiles. Boundary layer computations were performed by a 2-D boundary layer code (NALSOF0801) available in the SOFFTS library of NAL. The effect of variation of Mach no. was performed using fluent. The surface Mach no. distribution on the CD profile clearly indicates lower peak Mach no. than MCA profile. Further, boundary layer parameters on CD aerofoil at respective incidences have lower values than corresponding MCA blade profile. Total pressure loss on CD aerofoil for the same incidence range is lower than MCA blade profile.

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References

  1. Whitcomb, R. T. and Clark, L. R., 1965, “An aerofoil shape for efficient flight at supercritical Mach numbers,” NASA TMX - 1109.
  2. Bauer, F., Garabedian, P., Korn, D., 1972, “Supercritical Wing Sections, Lecture notes In Economics And Mathematical Systems,” Vol. 66, Springer – Verlag, New York.
  3. Bauer, F., Garabedian, P., Korn, D., 1977, “Supercritical Wing Sections III,” Lecture notes in Economics And Mathematical Systems, Vol. 150, Springer – Verlay, NewYork.
  4. Lubenstein. J. H., Robideu B. A. Ross A. K, 1984, “Aerofoil Shape For Arrays Of Aerfoils ,” U. S. Patent 4,431,376.
  5. Q. H. Nagpurwala, S.A.Guruprasad, H. Girigoswamy, B. R. Pai, “Experimental and Analytical Studies of A Transonic Stator having Controlled Diffusion Aerofoil Sections with End Bends,” Propulsion Division, National Aerospace Laboratories, Bangalore - 560017 ,ISABE 95-7074.
  6. Q. H. Nagpurwala, B. R. Pai, S. A. Guruprasad, Characteristics of conventional and controlled diffusion stator blades in a transonic compressor stage, Propulsion Division, National Aerospace Laboratories, Bangalore – 560017 ISABE, 93-7124.
  7. Horlock, J. H., 1958, “Axial Flow Compressors,” Butteworth.
  8. M. Anbarasu, B. R. Pai, “A Method for Designing Transonic Compressor Blade Profiles,Propulsion Division,” National Aerospace Laboratories , Bangalore – 560017 PDPR9016.