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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Patent•
23 May 1994TL;DR: In this paper, a metal matrix composite is applied to each fan blade near its root so as to increase stiffness and thereby provide frequency and stability control to the fan blades, and a lower engine weight can be realized by using more fan blades without the need for a part span shroud.
Abstract: Metal alloy fan blades reinforced with a metal matrix composite for enhancing stiffness of the fan blades without a significant weight penalty, and which are suitable for use in high bypass turbofan engines. The metal matrix composite is bonded to each fan blade near its root so as to increase stiffness and thereby provide frequency and stability control to the fan blades. As a result, a lower engine weight can be realized by using more fan blades without the need for a part span shroud.
26 citations
Patent•
26 Mar 2013TL;DR: In this article, a gas turbine engine has a fan at an axially outer location with a booster fan positioned radially inwardly of the outer bypass duct, and a cold turbine into a radially inner core duct being directed into a compressor.
Abstract: A gas turbine engine has a fan at an axially outer location. The fan rotates about an axis of rotation. The fan delivers air into an outer bypass duct, and across a booster fan positioned radially inwardly of the outer bypass duct. The booster fan delivers air into a radially middle duct, and across a cold turbine into a radially inner core duct being directed into a compressor. From the compressor, air flows axially in a direction back toward the fan through a combustor section, and across an exhaust of the turbine section as directed into the middle duct. A gear reduction drives the fan from a fan drive turbine section. A method is also disclosed.
26 citations
Patent•
25 Jul 1997
TL;DR: A blockerless thrust reverser for an aircraft having a podded nacelle housing a turbofan engine which produces core flow and a fan exit stream was proposed in this article.
Abstract: A blockerless thrust reverser for an aircraft having a podded nacelle housing a turbofan engine which produces core flow and a fan exit stream. Reverse thrust is obtained by diverting the fan exit stream into an annular slot formed in an outer wall of the nacelle where it is turned and discharged forwardly. The fan exit stream is directed into the annular slot by injecting high pressure streams of core flow into the fan exit stream at positions which are upstream of and adjacent to the annular slot. Reverse thrust is selectively obtained by a control means which selectively opens and closes the annular slot and the core jet injectors.
26 citations
Patent•
01 Nov 1999
TL;DR: A fan case for a turbofan engine having a fan including plurality of fan blades mounted to a rotor disk and a decoupler that fails in response to a predetermined load includes a substantially annular shell as discussed by the authors.
Abstract: A fan case for a turbofan engine having a fan including plurality of fan blades mounted to a rotor disk and a decoupler that fails in response to a predetermined load includes a substantially annular shell. The shell has a forward section, an intermediate section, and an aft section. The fan case further includes an aft facing step formed at the forward end of the intermediate section to prevent blade fragments from being ejected forward. The intermediate section is axially aligned with the fan and has a large inside diameter. The intermediate section thus defines an annular space around the fan blades that is sufficiently large to allow the fan to orbit when the decoupler fails. The intermediate section and the aft section are aligned radially to allow blade fragments to be ejected aft, avoiding additional secondary blade damage.
26 citations
Patent•
24 May 1979
TL;DR: In this article, a propulsion system for an aircraft having a fuselage and a wing with two nacelles disposed on opposite sides of the fuselage, each of the naceLLes having a turbo fan therein with drive means connected to the drive means for air flow through the nacelle from a forward air inlet to air exit openings, the air flow within the nascelle divided into two air streams, one of the air-streams being directed downwardly through a variable area forward chin nozzle provided with a cascade of vanes for directing the outflow in
Abstract: A propulsion system for an aircraft having a fuselage and a wing with two nacelles disposed on opposite sides of the fuselage, each of the nacelles having a turbo fan therein with drive means connected thereto for air flow through the nacelle from a forward air inlet to air exit openings, the air flow within the nacelle divided into twi air streams, one of the air-streams being directed downwardly through a variable area forward chin nozzle provided with a cascade of vanes for directing the outflow in a desired direction with the other air stream exhausted through an aft nozzle of variable area at the aft outlet opening against a slotted flap system mounted aft of the aft nozzle against which the outflow from the aft nozzle is directed so that the two air streams provide pitch, roll and yaw control as well as balanced lift and propulsion utilizing controlled thrust modulation and vectoring for all regimes of flight from vertical takeoff and landing (VTOL) or short takeoff and landing (STOL) or a combination of these and conventional flight through a combination of nozzle area change and wing flap vectoring.
26 citations