The combustion chamber of gas turbine unit is one of the most critical components to be designed. Scanning through literature reveals that the design methodologies for combustion chamber are available in a discrete manner and there exist a need to compile this information and evolve a systematic design procedure for combustion chamber. The present paper is an attempt towards presenting such a complete design methodology of combustion chamber for small gas turbine applications. The combustion chamber for the 20 kW gas turbine engine has been designed and fabricated as per these summarized design guidelines then checked for the axial and radial temperature profiles as well as liner wall temperatures, experimentally. The liner wall temperatures achieved is in the vicinity of 300°C when centerline temperature is of the order of 1300°C. This adequately validates the design methodologies proposed in this paper.

1.
V. W. Greenhough and A. H. Lefebvre, Some Applications of Combustion Theory of Gas Turbine Development, 16th Symposium (International) on Combustion, pp. 858–869, New York, 1957.
2.
A. H. Lefebvre, Gas Turbine Combustion, 2nd ed., Taylor & Francis, 1999.
3.
A. H. Lefebvre and E. R. Norster, A Design of Tubular Combustion Chambers for optimum Mixing Performance, Technical Advances in Gas Turbine Design, pt. 3N, Proc. Inst. Mech. Eng., 1969.
4.
Novick
A. S.
,
Irwin
J. R.
and
Quinn
R. E.
,
Development of a Gas Turbine Combustor Dilution Zone Design Analysis
,
J. Airer
, vol.
17
No.
8
, pp.
712
718
,
1980
.
5.
Nealy
D. A.
and
Reider
S. B.
,
Evaluation of Laminated Porous Wall Materials for Combustor Liner Cooling
,
J. Eng. Power
, vol.
102
, pp.
268
276
,
1980
.
6.
G. Sovran and E. D. Klomp, Experimentally Determined Optimum Geometries for Rectilinear Diffuser with Rectangular, Conical or Annular Cross-section, in Fluid Mechanics of Internal Flow, pp. 270–319, Elsevier, New York, 1967.
This content is only available via PDF.
You do not currently have access to this content.