چكيده به لاتين
Abstract:
To reduce designing and developing new gas turbines cost, manufacturers found a new way that industrial gas turbines derived from modification of aircraft gas turbine. Aero derivative gas turbine is more efficient in mid-range power than heavy-duty gas turbine. This gas turbines have been applied in marine, power generation and oil industries. So, leading manufacturers such as GE, Rolls-Royce and P&W start designing of this new gas turbines.
This thesis presents assumption and restriction to convert turbofan engine to aero-derivative gas turbine also performance of a three spool turbofan engine similar to Trent900 in A380 and design of derived gas turbine has been carried out. Design and off-design performance have been carried out and validated with Gas turb10 software. In new case based on aero engine, fan completely removed, natural gas used as fuel and power turbine added. Take off condition has been used as design point. It is clearly observed that intermediate pressure compressor (booster) is most sensitive to variation in combustor outlet temperature due to the sever variation occurred in LP shaft non-dimensional speed (N/√T) than happened in the non-dimensional speed of HP shaft. So booster tend to cross surge line at low rotational speeds. On the other hand the HP compressor has a flat working line, and takes a longer period of time to reach the compressor surge line.
Keywords: aero-derivative gas turbine, Trent900, gas turbine performance, Gas turb10
