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 published on a yearly basis
Papers
More filters
TL;DR: In this article, the design of an annular combustion chamber in a gas turbine engine is the backbone of a jet trainer aircraft, specifically designed for a low bypass turbofan engine in a jet aircraft.
32 citations
Patent•
19 Jun 2008
TL;DR: The thrust reverser comprises sections, such as arms and skins, which may be connected along joints to provide a thrust reversers body as discussed by the authors, and a plurality of fittings may be integrally formed on a surface of each arm.
Abstract: The thrust reverser comprises sections, such as arms and skins, which may be connected along joints to provide a thrust reverser body. A plurality of fittings may be integrally formed on a surface of each arm.
32 citations
TL;DR: Turbofan noise generation and suppression in aircraft engines are reviewed in this article. But the authors focus on the long chain of physical processes which connect unsteady flow interactions with fan blades to far field noise.
Abstract: Turbofan noise generation and suppression in aircraft engines are reviewed. The chain of physical processes which connect unsteady flow interactions with fan blades to far field noise is addressed. Mechanism identification and description, duct propagation, radiation and acoustic suppression are discussed. The experimental technique of fan inflow static tests are discussed. Rotor blade surface pressure and wake velocity measurements aid in the determination of the types and strengths of the generation mechanisms. Approaches to predicting or measuring acoustic mode content, optimizing treatment impedance to maximize attenuation, translating impedance into porous wall structure and interpreting far field directivity patterns are illustrated by comparisons of analytical and experimental results. The interdependence of source and acoustic treatment design to minimize far field noise is emphasized. Area requiring further research are discussed and the relevance of aircraft turbofan results to quieting other turbomachinery installations is addressed.
32 citations
01 Jan 2012
TL;DR: A model-based inversion flight control law is presented which provides a rate command response type in all axes and demonstrates the potential of the PrandtlPlane control characteristics.
Abstract: The conceptual and preliminary design of a 300-passenger box-wing aircraft configuration, designated the PrandtlPlane, is investigated. Currently there are still a number of technical issues which must be investigated thoroughly to demonstrate the feasibility of this configuration. This research study is focused on two aspects of the PrandtlPlane design, (1) the propulsion system and (2) the flight control system. A nonlinear aircraft model is created with an in-house developed flight mechanics toolbox, which is designed for its application in the conceptual and preliminary design phase. The resulting propulsion system design has two conventional turbofan engines at the tail of the aircraft. For a large version of the PrandtlPlane, it might be beneficial to consider large open-rotor systems underneath the rear wing. The volume of the wing system, which is smaller than that of conventional aircraft, poses constraints on the fuel system design. Flight control of the PrandtlPlane is quite different from the control of conventional aircraft. If control surfaces are placed on the front and rear wings, then a pure moment can be created by differential deflection of these controls. Furthermore, a combined deflection of the front and rear wing control surfaces allows the use of direct lift control. The aircraft exhibits good inherent handling qualities in the longitudinal axis. The Dutch roll mode is slightly unstable. Improvements are expected if the vertical tails of the aircraft are redesigned. Finally, a model-based inversion flight control law is presented which provides a rate command response type in all axes. An additional outer control loop is designed which provides direct lift control. The control law is tested on the nonlinear aircraft model and demonstrates the potential of the PrandtlPlane control characteristics.
32 citations
18 Sep 2014
TL;DR: In this paper, the effects of boundary layer ingestion on turbofan engine performance were investigated using a modified JT15D-1 turboprocessor with a wire mesh distortion screen.
Abstract: Boundary Layer Ingestion (BLI) is currently being researched as a potential method to improve efficiency and decrease emissions for the next generation of commercial aircraft. While re-energizing the boundary layer formed over the fuselage of an aircraft has many system level benefits, ingesting the low velocity boundary layer flow through a serpentine inlet into a turbofan engine adversely affects the performance of the engine. This work reports an experimental investigation of the effects of a BLI-type distortion on a turbofan engine’s performance. A modified JT15D-1 turbofan engine was used in this study. Inlet flow distortion was created by a layered wire mesh distortion screen designed to create a total pressure distortion profile at the aerodynamic interface plane (AIP) similar to NASA’s Inlet A boundary layer ingesting inlet flow profile. Results of this investigation showed a 15.5% decrease in stream thrust and a 14% increase in TSFC in the presence of BLI-type distortion. The presence of the distortion screen resulted in a 24% increase in mass-averaged entropy production along the entire fan flow path compared to the non-distorted test.Copyright © 2014 by ASME
32 citations