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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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Proceedings ArticleDOI
Ken Naitoh, Dai Shimizu1, Shouhei Nonaka1, Yusuke Kainuma1, Takehiro Emoto1 
01 Dec 2012
TL;DR: In this article, a new compression system of colliding super multijets with pulsation was proposed for the purpose of a single lightweight engine capable of operating over a wide range of Mach numbers from startup to the hypersonic regime.
Abstract: In our previous reports and patents, a single lightweight engine capable of operating over a wide range of Mach numbers from startup to the hypersonic regime was proposed for aircars, aircrafts, and spaceships. A new compression system of colliding super multijets with pulsation was proposed for this purpose. The new compression system essentially differs from those for the traditional four types of engines with piston, turbofan, ran-scram, and pulse-detonation. This is the fifth compression principle. Shocktube experiments and computational fluid dynamics with a chemical reaction model clarifies a large potential and stability of this system. This ultimate engine system can be extended with a special piston and scram jet systems to achieve an improved fuel consumption rate at various situations between the ground and the space, while maintaining a very low noise level with silent detonation. The present engine system will also solve the problem of the buzz at highersonic conditions.

17 citations

Patent
30 May 1998
TL;DR: A flow diverting mechanism for the twin duct offtakes or coannular offtake for a turbo fan engine powering aircraft with either thrust reversing or short takeoff and vertical landing or both capabilities includes a rotary drum mounted between the turbine and afterburner sections as mentioned in this paper.
Abstract: A flow diverting mechanism for the twin duct offtakes or coannular offtake for a turbo fan engine powering aircraft with either thrust reversing or short takeoff and vertical landing or both capabilities includes a rotary drum mounted between the turbine and afterburner sections and includes ports complementing the inlets in the offtakes to divert the core stream through the offtakes and passages to proportion the fan discharge air utilized for cooling purposes in the engine to cool the liner and walls of the offtakes and the engine components located downstream of the rotary drum while assuring separation of the core stream flow and fan air flow.

17 citations

Proceedings ArticleDOI
03 Jun 2013
TL;DR: In this article, an over-the-rotor liners with circumferentially grooved over-rotors between the fan blades and the acoustic liners was designed to reduce the oscillating flow in the acoustic liner.
Abstract: While liners have been utilized throughout turbofan ducts to attenuate fan noise, additional attenuation is obtainable by placing an acoustic liner over-the-rotor. Previous experiments have shown significant fan performance losses when acoustic liners are installed over-the-rotor. The fan blades induce an oscillating flow in the acoustic liners which results in a performance loss near the blade tip. An over-the-rotor liner was designed with circumferential grooves between the fan blade tips and the acoustic liner to reduce the oscillating flow in the acoustic liner. An experiment was conducted in the W-8 Single-Stage Axial Compressor Facility at NASA Glenn Research Center on a 1.5 pressure ratio fan to evaluate the impact of this over-the-rotor treatment design on fan aerodynamic performance. The addition of a circumferentially grooved over-the-rotor design between the fan blades and the acoustic liner reduced the performance loss, in terms of fan adiabatic efficiency, to less than 1 percent which is within the repeatability of this experiment.

17 citations

ReportDOI
01 Nov 1976
TL;DR: The F100 multivariable control research program is to extend the linear quadratic regulator (LQR) theory to develop a "practical" control system that can operate a state-of-the-art gas turbine engine over its entire flight envelope as mentioned in this paper.
Abstract: : The objective of the F100 multivariable Control research program is to extend the linear quadratic regulator (LQR) theory to develop a 'practical' control system that can operate a state-of-the-art gas turbine engine over its entire flight envelope. The engine selected for this program is a Pratt and Whitney Aircraft F100 afterburning turbofan. To determine the adequacy of the control synthesis effort, the resulting control logic will be incorporated into a digital computer/controller, which then will be used to control a F100 engine in an altitude test facility at NASA Lewis Research Center. The F100 engine computer simulations, the control criteria for defining the basic requirements of a F100 control system, and a brief evaluation of the resulting LQR engine control system are presented in this report.

17 citations

01 Aug 1992
TL;DR: The subsonic flight test evaluation phase of the NASA F-15 performance seeking control program was completed for single-engine operation at part- and military-power settings, and validated the performanceseeking control technology, which can significantly benefit the next generation of fighter and transport aircraft.
Abstract: The subsonic flight test evaluation phase of the NASA F-15 (powered by F 100 engines) performance seeking control program was completed for single-engine operation at part- and military-power settings. The subsonic performance seeking control algorithm optimizes the quasi-steady-state performance of the propulsion system for three modes of operation. The minimum fuel flow mode minimizes fuel consumption. The minimum thrust mode maximizes thrust at military power. Decreases in thrust-specific fuel consumption of 1 to 2 percent were measured in the minimum fuel flow mode; these fuel savings are significant, especially for supersonic cruise aircraft. Decreases of up to approximately 100 degree R in fan turbine inlet temperature were measured in the minimum temperature mode. Temperature reductions of this magnitude would more than double turbine life if inlet temperature was the only life factor. Measured thrust increases of up to approximately 15 percent in the maximum thrust mode cause substantial increases in aircraft acceleration. The system dynamics of the closed-loop algorithm operation were good. The subsonic flight phase has validated the performance seeking control technology, which can significantly benefit the next generation of fighter and transport aircraft.

17 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
2023163
2022320
2021112
2020131
2019175
2018189