Patent
Gas turbine engine fan variable area nozzle with swivalable insert system
TLDR
In this paper, a variable area nozzle (FVAN) is used to selectively vector the fan bypass flow by adjusting each of the multiple aerodynamical Iy shaped inserts relative to other inserts, providing an asymmetrical fan nozzle exit area.Abstract:
A turbofan engine (10) includes a fan variable area nozzle (FVAN) (50) which effectively changes the physical area and geometry within a fan bypass flow path (40) to manipulate the pressure ratio of the bypass flow. The FVAN generally includes a multitude of aerodynamical Iy shaped inserts (52) circumf erentially located about the core nacelle (12). The FVAN at a fully stowed position (takeoff /landing) takes up a minimum of area within the fan bypass flow path to effectively maximize the fan nozzle exit area (44) while in the fully deployed position (cruise) takes up a maximum of area within the bypass flow path to effectively minimize the fan nozzle exit area. By separately adjusting each of the multiple of inserts relative the other inserts the FVAN provides an asymmetrical fan nozzle exit area to selectively vector the fan bypass flow.read more
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Patent
Gas turbine engine with geared architecture
TL;DR: In this article, a gas turbine engine according to an exemplary aspect of the present disclosure includes a core nacelle defined about an engine centerline axis, a fan nacel mounted at least partially around the core nacelles to define a bypass flow path for a fan bypass airflow, a variable area nozzle axially movable relative to the fan nacella to vary a fan nozzle exit area and adjust a pressure ratio of the bypass airflow during engine operation, and a gear system driven by a core engine within the core Nacelle to drive a fan within the
Patent
Gas turbine engine with low fan pressure ratio
TL;DR: A turbofan engine includes a variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation as discussed by the authors.
Patent
Gas turbine engine with fan variable area nozzle having a rotational valve system
TL;DR: A turbofan engine includes a variable area nozzle having a multiple of vents through a fan nacelle and rotatable elements rotatable within the vents by an actuator system as discussed by the authors.
Patent
An aircraft propulsion system and a method of controlling the same
TL;DR: In this article, the vane assembly is configured to direct the airflow away from the rotor blades so as to reduce the relative velocity of the redirected airflow over the rotor blade blades, which results in a reduced tendency of the airflow through the propeller assembly to become choked.
Patent
Systems and methods for injecting fluids at one or more stages of a multi-stage component
Javier Ramirez Muñoz,Alfonso Cárdenas Pérez,Pedro Montiel Lopez,Cesar Octavio Vazquez Carmona +3 more
TL;DR: In this article, a system for injecting one or more fluids at one or multiple stages of a multi-stage component of a gas turbine engine is described. But the system does not specify the number of fluids to be injected at each stage.
References
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Patent
Differential geared engine
TL;DR: In this paper, a gas turbine engine consisting of a fan, a compressor and a turbine is provided with differential gearing to transmit all of the fan and compressor power requirements from the turbine, which maintains an adjustable speed relationship between the compressor with respect to the turbine depending upon the torque requirements thereof and the gear ratios within the differential gearing.
Patent
Deicing of a geared gas turbine engine
TL;DR: A geared turbofan gas turbine engine has a fan rotor carrying a plurality of fan blades driven by a gas generator via a gear assembly as discussed by the authors, and an annular chamber formed coaxially supplies air warmed in the fan casing by the heat exchanger to the exterior surface of the fan.
Engine And Installation Configurations For A Silent Aircraft
Cesare A. Hall,Daniel Crichton +1 more
TL;DR: In this article, the authors identify some key features of a propulsion system that can achieve the Silent Aircraft noise target and explore the relat ionships between the factors that affect fuel consumption.
Patent
Movable acoustic splitter for nozzle area control and thrust reversal
TL;DR: An aircraft engine nozzle foil is a plurality of segmented foil members which are movable from a cruise or stowed position along a wall of the nozzle duct at the exit plane to a first position well forward of the exiting plane within the duct to split the flow of acoustic attenuation and to increase the nozzle passageway exit plane area for low speed flight as mentioned in this paper.
Patent
Variable geometry exhaust nozzle for a turbine engine
TL;DR: In this paper, a variable exhaust nozzle for a turbine engine nacelle includes a pair of semi-cowls (58, 60) disposed about a longitudinally extending central axis (14) and a pair corresponding shells (36, 38) each of which is spaced radially inwardly from the corresponding semi-Cowl and is pivotable about a pivot axis (42, 44) between an extended position and a retracted position.