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The Effect of Boundary Layer Changes Due to Transient Heat Transfer on the Performance of an Axial-Flow Air Compressor
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Abstract
During transient operation of a gas turbine there are significant heat transfers between the fluid stream and the blades of the compressor and turbine. At the end of a rapid deceleration from maximum speed to idling speed, heat transfer to the compressor blade boundary layers may cause sufficient disturbance to delay any immediate re-acceleration. As a first estimate in one severe case - at altitude in an aircraft engine of compression ratio 20 - the surge margin prior to the re-acceleration is reduced by about 40% due to boundary layer effects, and by a further 25% due to “bulk” heat transfer.
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Citation
Maccallum, N. and Grant, A., "The Effect of Boundary Layer Changes Due to Transient Heat Transfer on the Performance of an Axial-Flow Air Compressor," SAE Technical Paper 770284, 1977, https://doi.org/10.4271/770284.Also In
References
- Warne E. H. “Gas turbine fuel and control systems” Proc. Instn. mech. Engrs. 1968-69 121 27
- Maccallum N. R. L. “Effect of bulk heat transfers in aircraft gas turbines on compressor surge margine” Heat and Fluid Flow in Steam and Gas Turbine Plant Instn. mech. Engrs. London 1974 94 100
- Grant A. D. “The effect of heat transfer on boundary layer stability in axial flow compressors” Heat and Fluid Flow in Steam and Gas Turbine Plant Instn. mech. Engrs. London 1974 252 258
- Howell A. R. Bonham R. P. “Overall and stage characteristics of axial-flow compressors” Proc. Instn. mech. Engrs 1950 163 235 248
- Howell A. R. “The present basis of axial flow compressor design. Part I. Cascade theory and performance” Aeronaut. Res. Counc. Rep. Memo. 2095 1942
- Pollard D. Gostelow J. P. “Some experiments at low speed on compressor cascades” J. Engng. Pwr., Trans. Am. Soc. mech. Engrs. 1967 July 427 436
- Robbins W. H. Dugan J. F. Jr. “Prediction of off-design performance of multistage compressors” Ch.X. Aerodynamic design of axial-flow compressors N.A.S.A.-S.P. 36 1965
- Gray S. “Stage matching, stall, and surge in multi-stage axial flow compressors” Proc. Instn. mech. Engrs. 1969-70 184 49 56
- Howell A. R. “Fluid dynamics of axial compressors” Proc. Instn. mech. Engrs. 1946 153 441 452
- Grant A. D. “The effect of heat transfer on boundary layer stability” University of Glasgow 1973
- Luxton R. E. Young A. D. “A generalised method for the calculation of the laminar compressible boundary layer with heat transfer and non-uniform pressure distribution” Aeronaut. Res. Counc. Rep. Memo. 3233 1960
- Head M. R. Entrainment in the turbulent boundary layer” Aeronaut. Res. Counc. Rep. Memo. 3152 1960
- Green J. E. “The prediction of the turbulent boundary layer development in compressible flow” J. Fluid Mech. 1968 31 753 778
- Patel V. C. “The effects of curvature on the turbulent boundary layer” Aeronaut. Res. Counc. Rep. Memo. 3599 1969
- Rhoden H. G. “Effects of Reynolds Number on the flow of air through a cascade of compressor blades” Aeronaut. Res. Counc. Rep. Memo. 2919 1956
- Masek Z. Norbury J. F. “Low-speed performance of a compressor cascade designed for prescribed velocity distribution and tested with variable axial velocity ratio” Heat and Fluid Flow in Steam and Gas Turbine Plant Instn. mech. Engrs. London 1974 224 236
- Maccallum N. R. L. “Models for the representation of turbomachine blades during temperature transients” ASME Paper 76-GT-23