scispace - formally typeset
Search or ask a question
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.


Papers
More filters
Journal ArticleDOI
TL;DR: In this paper, the impact of day temperature variation on the creep life-consumption of a turbofan aero-engine's hot-end components has been analyzed for a military aircraft's mission profile.

17 citations

Journal ArticleDOI
TL;DR: In this article, the authors investigated the dominant noise components of a full-scale high performance tactical aircraft using acoustic measurements of the exhaust jet from a single General Electric F414-400 turbofan engine installed in a Boeing F/A-18E Super Hornet.

17 citations

Proceedings ArticleDOI
04 Jun 2001
TL;DR: The TERTS modeling environment will be described including the numerical solutions used to comply with the real-time requirements including A TERTS model of a military afterburning turbofan will be presented including simulation results.
Abstract: Real-time simulation of gas turbine engine performance is used in a variety of aerospace applications. For simulation of propulsion system performance in flight-simulators, fidelity requirements become increasingly stringent. Significant improvements in simulation fidelity can be obtained when using thermodynamic models instead of the customary (piece-wise) linear real-time models. However, real-time thermodynamic models require sophisticated methods to efficiently solve the model equations on a real-time basis with sufficient speed.NLR has developed the ‘Turbine Engine Real-Time Simulator’ (TERTS) generic real-time engine simulation environment for full thermodynamic simulation of various gas turbine engine configurations. At NLR’s National Simulator Facility (NSF), research is performed on pilot-in-the-loop simulation of complex aircraft and helicopter configurations such as thrust-vectoring and Integrated Flight Propulsion Control (IFPC) concepts. For this application, high-fidelity real-time gas turbine models are required. TERTS has an efficient method for solving the engine model equations real-time. The system is implemented in Matlab-Simulink®, which offers advantages in terms of control system modeling flexibility. With TERTS, detailed thermodynamic real-time engine models can easily be implemented in NSF providing an excellent means to analyze a variety of engine effects on pilot-in-the-loop aircraft performance.In this paper the TERTS modeling environment will be described including the numerical solutions used to comply with the real-time requirements. A TERTS model of a military afterburning turbofan will be presented including simulation results.Copyright © 2001 by ASME

17 citations

Journal ArticleDOI
TL;DR: Viswanathan et al. as mentioned in this paper presented the aeroacoustic characteristics of two beveled nozzles, with bevel angles of 24 deg and 45 deg, operated at supercritical pressure ratios, under static conditions as well as in the presence of a Mach 0.32 flight stream.
Abstract: The nozzles of a dual-stream turbofan engine are operated invariably at supercritical pressure ratios at cruise, thereby producing shocks in the jet plume. Consequently, broadband shock-associated noise is generated in addition to turbulent mixing noise. The jet exhaust noise impinges on the fuselage and is then transmitted into the interior of the aircraft cabin. In a companion paper, the beveled nozzle has been shown to provide a community noise benefit during takeoff. (Viswanathan, K., "Elegant Concept for Reduction of Jet Noise from Turbofan Engines," Journal of Aircraft, Vol. 43, No. 3, 2006, pp. 616-626.) Here, the aeroacoustic characteristics of two beveled nozzles, with bevel angles of 24 deg (bevel24) and 45 deg (bevel45), operated at supercritical pressure ratios, are presented under static conditions as well as in the presence of a Mach 0.32 flight stream. The intended application is for the control of aft-cabin noise. The velocity of the primary jet plays a strong role in the reduction of noise at the aft polar angles, with a substantial benefit at higher jet velocities. The magnitude of reduction in overall levels for bevel45 at the aft angles ranges from ∼5 to ∼12 dB under static conditions, depending on the Mach number of the secondary stream. In the presence of a flight stream, the jet conditions, as well as the bevel angle, control the flight effects at different azimuthal angles. It is demonstrated that at typical cruise power settings, the current concept with bevel24 yields a reduction of ∼4 dB in overall levels; the reduction occurs over a wide range of lower frequencies without any increase at the higher frequencies. Given this reduction in impingement levels on the rear fuselage, this design could yield a cabin noise benefit in addition to the benefit for community noise at takeoff conditions.

17 citations


Network Information
Related Topics (5)
Turbine
106.6K papers, 1M citations
74% related
Nozzle
158.6K papers, 893K citations
73% related
Reynolds number
68.4K papers, 1.6M citations
72% related
Internal combustion engine
130.5K papers, 1M citations
72% related
Piston
176.1K papers, 825.4K citations
71% related
Performance
Metrics
No. of papers in the topic in previous years
YearPapers
2023163
2022320
2021112
2020131
2019175
2018189