Abstract
A parametric study of a novel turbofan engine with an auxiliary high-pressure bypass (AHPB) is presented. The underlying motivation for the study was to introduce and explore a configuration of a turbofan engine which could facilitate clean secondary burning of fuel at a higher temperature than conventionally realized. The study was also motivated by the developments in engineering materials for high-temperature applications and the potential utility of these developments. The parametric study is presented in two phases. Phase I presents a schematic of the turbofan engine with AHPB and the mathematics of the performance parameters at various stations. The proposed engine is hypothesized to consist of three streams—core stream, low-pressure bypass (LPB) stream, and the AHPB or, simply, the high-pressure bypass (HPB) stream. Phase II delves into the performance simulation and the analysis of the results in an ideal set-up. The simulation and results are presented for performance analysis when (i) maximizing engine thrust while varying the LPB and AHPB ratios, and (ii) varying the AHPB ratio while maintaining the LPB ratio constant. The results demonstrate the variations in performance of the engine and a basis for examining its potential utility for practical applications.
Highlights
Background and IntroductionA turbofan engine of an airplane has a single inlet that splits into a core stream and a bypass stream.In a separate-exhaust turbofan engine, the two streams exit through separate exhaust nozzles [1]
An auxiliary high-pressure bypass (AHPB) stream comparable to the size of an low-pressure bypass (LPB) stream may be driven by an electrical actuator and power source, thereby reducing the burden on the turbine to drive the compressor and fan of a turbofan engine
To comprehensively evaluate the turbofan engine with AHPB, simulations were performed, and results were analyzed for the following scenarios: (i) maximizing engine thrust while varying LPB
Summary
A turbofan engine of an airplane has a single inlet that splits into a core stream and a bypass stream. In Reference [4], the authors state, “an engine with an extra combustor installed between the turbine stages will be referred to as a two-combustor engine: the additional combustor will be designated as an inter-stage turbine burner” They used constant-pressure burning and concluded that the increase in specific thrust might be noteworthy, Int. J. Considering that the flow at the exit of AHPB burner goes through the exhaust nozzle without passing through the turbine blades, the AHPB nozzle design would significantly benefit from advances in the development of ceramic materials for high-temperature applications [6]. An AHPB stream comparable to the size of an LPB stream may be driven by an electrical actuator and power source, thereby reducing the burden on the turbine to drive the compressor and fan of a turbofan engine
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