Design and Development of Combustion Chamber for Small Gas Turbine Power Plant S. V. National Institute of Technology, Surat 395 007, India

Format:

Conference/Event

Author/Creator:

Kulshreshtha, Digvijay B., author.

Conference Name:

International Mobility Engineering Congress & Exposition 2005 - SAE India Technology for Emerging Markets (2005-10-23 : P-2005, Pennsylvania, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Pune, MH The Automotive Research Association of India 2005

Summary:

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. It is worth to mention that the liner wall temperatures achieved is in the vicinity of 350°C when centerline temperature is of the order of 1300°C. The pressure loss is in the range of 10% of the delivery pressure which suggest the aerodynamic design of the combustion chamber

Notes:

Vendor supplied data

Publisher Number:

2005-26-317

Access Restriction:

Restricted for use by site license