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International Journal of Scientific and Engineering Research
ISSN Online 2229-5518
ISSN Print: 2229-5518 3    
Website: http://www.ijser.org
scirp IJSER >> Volume 3,Issue 3,March 2012
Decoding the NGTE/Calvert Axial Flow Compressor Computer Progra
Full Text(PDF, )  PP.545-547  
Author(s)
Tonye K. Jack and Robin L. Elder
KEYWORDS
Axial Compressor, Axial Performance, Compressor, Compressor Performance, Compressor Tip Clearance,, Multistage Compressor, Off-Design Performance, Stage Stacking, Diffusion factors, loss coefficient, blade aspect ratio .
ABSTRACT
Several models are used for the design and performance evaluation of axial compressors - thickness, clearance, efficiency and others. However, two principal models for the overall performance evaluation are used - in North America, the US National Aeronautics and Space Administration (NASA) or Steinke Model, and in Europe, the UK National Gas Turbine Establishment Model (NGTE) or Howell/Calvert Model. In all, there are essential relationships and connects in some of these models. An earlier investigator had applied the NASA model to a major UK gas turbine manufacturer's equipment with useful results. The aim of this research effort was to evaluate some of the major models, decode the NGTE Calvert computer program since some of these relationships are experimentally developed and not available in the open literature, find the connecting relationships, through new models developmen
References
[1] W.J. Calvert, “User‟s Guide to the Howell Multistage Compressor Performance Prediction Program”, NGTE Memo 77023, 1977

[2] T.K. Jack and R.L. Elder, “A Modified Stage Stacking Method for Axial Flow Compressors Calculation, International journal of Science and Engineering Research, 2012, (Pending Publication)

[3] C.C. Koch, and L.H. Smith, “Loss Sources and their magnitudes in Axial Flow Compressors,” ASME J. of Engr. For Power, vol. 2, no. 4, pp. 193-218, July 1976.

[4] A.D.S. Carter and H.P. Hughes, “A Theoretical Investigation into the Effect of Profile Shape on the Performance of Aerofoils in Cascade, R & M 2384, 1946

[5] R.K. Oldham, “Some Stage Design Data for Double Circular Arc Compressor Blading” NGTE Notes NT 589, 1965

[6] M.P. Boyce, “Design of Compressor Blades Suitable for Transonic Axial Flow Compressors”, ASME 67-GT-47, 1967

[7] M.V. Casey, “A Mean Line Prediction Method for Estimating, the Performance of Axial Compressors”, Proceedings of the Imech., C264/87, 1987

[8] A.R. Howell, and R.P. Bonham “Overall and Stage Characteristics of Axial Flow Compressors”, Proceedings of Imech., 1950

[9] A.R. Howell and W.J. Calvert, “A New Stage Stacking Technique for Axial Flow Compressors”,ASME J. of Engr. For Power, 1978

[10] D.C. Miller and D.L. Wasdell, “Off-Design Prediction of Compressor Blade Losses” Proceedings of the Imech., C279/87, 1987

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