Cycle optimization of N+3 gas turbine engines
Abstract
Thermodynamic cycle analysis is performed to study and compare possible ways of achieving significant reductions in fuel burn of the N+3 commercial aviation gas turbine engines. Here N+3 represent the 3rd generation aero-engines from the current engines in use with the expected Technology Readiness Level, TRL 4–6 in the 2025 timeframe. The analysis was carried out using Numerical Propulsion System Software (NPSS). NPSS was developed by NASA Glenn Research Center in collaboration with some of the top aviation industry partners and the Department of Defense (DOD). A systematic methodology was adopted for this work. Phase one of this work was on calibrating the NPSS code with performance data of several engines available from the public domain including the CFM-56/5B, CF680-C2 & GE90 engine series along with LM6000 and LMS1000, in addition to showing repeatability of a test case, NASA N+1 advanced geared turbofan supplied by NASA. The results obtained from the NPSS showed reasonable predictions of the performance data both at ADP (Aerodynamic Design Point) and off-design conditions. Having established the reliability of the methodology, the second phase was to perform thermodynamic analysis of a three spool advanced geared turbofan gas turbine engine cycle at ADP, GTF. Next, GTF with a recuperator and intercooler were analyzed; and optimized operating conditions were established for each of these configurations. The three engines selected from the design point optimization were analyzed for off-design analysis and performed. Finally, the third phase of the project looked at other potential ways of improvement in fuel efficiency by leveraging ideas from other thermal power generating systems to assess the feasibility of application to aviation gas turbine engines.
Degree
M.S.M.E.
Advisors
Mongia, Purdue University.
Subject Area
Aerospace engineering|Mechanical engineering
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