Topic
Turbofan
About: Turbofan is a research topic. Over the lifetime, 4114 publications have been published within this topic receiving 39490 citations. The topic is also known as: fanjet & turbofan engine.
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01 Sep 1977
TL;DR: A real time, hybrid computer simulation of a turbofan engine is described and shown to match the steady state and transient performance of the engine over a wide range of flight conditions and power settings.
Abstract: A real time, hybrid computer simulation of a turbofan engine is described. Controls research programs involving that engine are supported by the simulation. The real time simulation is shown to match the steady state and transient performance of the engine over a wide range of flight conditions and power settings. The simulation equations, FORTRAN listing, and analog patching diagrams are included.
12 citations
28 Jul 2014
TL;DR: This research constructs an integrated NPSS hybrid electric propulsion model capable of predicting hybrid electric engine performance throughout the operational envelope and a vehicle trade study is carried out to determine the optimum engine cycle for both a cryogenic and conventionally driven motor system.
Abstract: NASA is actively funding research into advanced, unconventional aircraft and engine architectures to achieve drastic reductions in vehicle fuel burn, noise, and emissions. One such concept is being explored by Boeing, General Electric, Virginia Tech, and Georgia Tech under the Subsonic Ultra Green Aircraft Research (SUGAR) project. A major cornerstone of this research is evaluating the potential performance benefits that can be attributed to using hybrid electric propulsion. Hybrid electric propulsion in this context involves a non-Brayton power generation or storage source, such as a battery or a fuel cell, that can be used to provide additional propulsive energy to a conventional Brayton cycle powered turbofan engine. This research constructs an integrated NPSS hybrid electric propulsion model capable of predicting hybrid electric engine performance throughout the operational envelope. The system consists of a battery powered motor partially drving the low pressure shaft of a conventional turbofan engine. The applied motor power adds an additional degree of freedom, along with power setting, to the aircraft designer during mission analysis. Modeling features and issues unique to hybrid electric propulsion systems are described and a vehicle trade study is carried out to determine the optimum engine cycle for both a cryogenic and conventionally driven motor system.
12 citations
TL;DR: Current turbofan engine noise and engine noise reduction technology, specifically focusing on the engine technology of larger passenger jetliners which have entered into service within the last ten (10) years are reviewed.
Abstract: This article reviews current turbofan engine noise and engine noise reduction technology, specifically focusing on the engine technology of larger passenger jetliners which have entered into service within the last ten (10) years. Important factors in turbofan engine design from a community noise perspective and the sources of noise along with their relative importance are also presented. A review of different engine noise reduction technologies is presented, as well as an estimate of the technology’s readiness level. Finally, potential trade-offs, challenges, and future technology directions are outlined.
12 citations
TL;DR: In this paper, a finite element model (FEM)-based simulation is conducted for the application of a thermoelectric generator (TEG) between the hot core stream and the cool bypass flow at the nozzle of an aviation turbofan engine.
Abstract: Finite element model (FEM)-based simulations are conducted for the application of a thermoelectric generator (TEG) between the hot core stream and the cool bypass flow at the nozzle of an aviation turbofan engine. This work reports the resulting requirements on the TEG design with respect to applied thermoelectric (TE) element lengths and filling factors (F) of the TE modules in order to achieve a positive effect on the specific fuel consumption. Assuming a virtual optimized TE material and varying the convective heat transfer coefficients (HTC) between the nozzle surfaces and the gas flows, this work reports the achievable power output. System-level requirement on the gravimetric power density (>100 Wkg−1) can only be met for F ≤ 21%. When extrapolating TEG coverage to the full nozzle surface, the power output reaches 1.65 kW per engine. The assessment of further potential for power generation is demonstrated by a parametric study on F, convective HTC, and materials performance. This study confirms a feasible design range for TEG installation on the aircraft nozzle with a positive impact on the fuel consumption. This application translates into a reduction of operational costs, allowing for an economically efficient TEG-installation with respect to the cost-specific power output of modern thermoelectric materials.
12 citations
TL;DR: In this article, an improved input and output self-tuning hybrid modeling (IOSTHM) method is proposed for improving the GPM modeling accuracy of a dual shaft turbofan GTE.
12 citations