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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TL;DR: Using entropy statistics, two allegedly dominant designs, the piston propeller DC3 and the turbofan Boeing 707, are shown to have triggered a scaling trajectory at the level of the respective firms, which points to the versatility of a dominant design which allows a firm to react to a variety of user needs.
99 citations
TL;DR: In this article, the major components of airframe noise are discussed and a comparison is made between prediction and experimental data and the prospects for airframe noisiness reduction is made.
99 citations
TL;DR: In this paper, a thermodynamic cycle analysis is performed to compare the relative performances of the conventional engine and the turbine-burner engine with different combustion options for both turbojet and turbofan conegurations.
Abstract: In a conventional turbojet and turbofan engine, fuel is burned in the main combustor before the heated highpressure gas expands through the turbine. A turbine-burner concept was proposed in a previous paper in which combustion is continued inside the turbine to increase the efe ciency and speciec thrust of the turbojet engine. This concept is extended to include not only continuous burning in the turbine but also “discrete” interstage turbine burners as an intermediate option. A thermodynamic cycle analysis is performed to compare the relative performances of the conventional engineand theturbine-burner engine with differentcombustion options for both turbojet and turbofan conegurations. Turbine-burner engines are shown to provide signie cantly higher specie c thrust with no or only small increases in thrust specie c fuel consumption compared to conventional engines. Turbine-burner engines also widen the operational range of e ight Mach number and compressor pressure ratio. The performance gain of turbine-burner engines over conventional engines increases with compressor pressure ratio, fan bypass ratio, and eight Mach number.
99 citations
TL;DR: In this article, a polynomial fixed-order controller design is extended to SISO gain-scheduling with guaranteed stability and H ∞ performance over the whole scheduling parameter range.
97 citations
Patent•
31 Jul 1987TL;DR: In this paper, an improved arrangement of a turbofan engine comprises a core engine, an upstream fan, a downstream fan and a booster compressor, and the gear assembly is positioned axially between the upstream fan and downstream fan.
Abstract: An improved arrangement of a turbofan engine comprises a core engine, an upstream fan, a downstream fan and a booster compressor. The upstream fan and downstream fan are both positioned upstream of the core engine, and are arranged to be driven in opposite directions by a gear assembly. The gear assembly is positioned axially between the upstream fan and downstream fan. The booster compressor is positioned upstream of the upstream fan and downstream fan, and comprises a first rotor carrying blades and a second rotor carrying blades. The first rotor is driven with the upstream fan and the second rotor is driven by the turbine of the core engine in opposite direction to the first rotor.
97 citations