Patent
Turbofan engine including fans with reduced speed
Takahiko Itoh,Hideo Takeda +1 more
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TLDR
In this paper, an impeller is directly driven by an output shaft of a core engine and the airflow produced by the impeller rotates an air turbine and a fan disposed integrally with the air turbine.Abstract:
An impeller is directly driven by an output shaft of a core engine. The airflow produced by the impeller rotates an air turbine and a fan disposed integrally with the air turbine. The impeller and the air turbine form a fluid coupling which serves also as a speed reducing mechanism. The rotational speed of the fan can be reduced to be lower than that of the output shaft while retaining efficiency of the core engine. The outer diameter of the fan can be increased, raising a bypass ratio.read more
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Gas turbine engine compressor arrangement
TL;DR: In this paper, a gas turbine engine includes a fan section, a gear arrangement configured to drive the fan, a compressor section and a turbine section, and an overall pressure ratio, which is provided by a combination of a pressure ratio across low pressure compressor sections and a high pressure compressor section, is greater than about 35.
Patent
Flexible support structure for a geared architecture gas turbine engine
Michael E. McCune,Jason Husband +1 more
TL;DR: In this paper, a gas turbine engine includes a fan shaft and a support which supports the fan shaft, the support defines at least one of the support transversals and the support lateral stiffness.
Patent
Gas Turbines with Multiple Gas Flow Paths
TL;DR: In this article, a representative gas turbine includes a spool, a compressor, and a turbine mechanically coupled to the spool; the compressor having a first set of blades and a second set of engines, the second engine being located downstream of the first engine, and the first and second engines being driven by the same spool.
Patent
Gas turbine engine systems involving tip fans
Gary D. Roberge,Gabriel L. Suciu +1 more
TL;DR: In this paper, a representative gas turbine engine system with tip fans is described, which includes a multi-stage fan having a first rotatable set of blades and a second counter-rotatable sets of blades, and an epicyclic differential gear assembly operative to receive a torque input and differentially apply the torque input to the first set of blade and counter-blades.
Patent
Gas turbine engine with low stage count low pressure turbine
TL;DR: In this article, a gas turbine engine according to an exemplary aspect of the present disclosure includes a gear train defined along an engine centeriine axis, and a spool along said engine center iine axis which drives the gear train, the spool includes a low stage count low pressure turbine.
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Fan engine with counter rotating geared core booster
James N Krebs,Peter G Kappus +1 more
TL;DR: In this paper, the authors describe a turbofan engine with high and low pressure compressors, where the low pressure compressor rotates in a direction counter to the direction of rotation of the fan.
Patent
Convertible aircraft engine
TL;DR: In this paper, a convertible aircraft engine with turboshaft and/or turbofan modes of operation is provided in a configuration that combines certain components to permit variation in bypass flow to match engine airflows with the mode of engine operation.
Patent
Turbofan engine having counterrotating compressor and turbine elements and unique fan disposition
TL;DR: In this paper, a turbofan engine is provided with a compressor and a turbine, all of the bladed stages of the turbine and substantially all of rotor stages being rotor stages, and a bladed fan occupying an annular duct substantially surrounding the compressor is driven by the intermediate of the three spools.
Patent
Gas turbine engine
TL;DR: In this paper, the first and second turbine rotors 40, 42 rotating in opposite directions without an intermediate blading are described for obtaining an output speed relative to the right of the pitch which is greater than the absolute input speed to the left of pitch for at least one of the rotors.
Patent
Convertible composite engine
TL;DR: A convertible composite engine capable of either shaft horsepower or thrust generation and split-powered operation in which partial thrust and partial shaft horsepower is generated is described in this article, where the engine is concentric about a single centerline and includes two coaxial free turbines, one driving a bypass fan and the other a shaft horsepower take-off, such as is commonly used to drive a helicopter rotor drive shaft.