Turbofan Engine for Stol Aircraft
AssigneeAvcen Limited
InventorMike Dacre
Life of this patent
Estimating the term…
Abstract
A module (10) for use with a bypass turbofan engine. The module comprises a hot flow channel through which the hot gas flow generated by the engine can flow and a bypass flow channel (14) through which the bypass air generated by the engine can flow. Part of the bypass air may be re-directed to be exhausted from the module at an angle relative to the longitudinal axis of the module so as to create vertical thrust. The hot flow channel may be separated from the bypass flow channel by a porous separator (12) that allows a degree of mixing between the hot gas flowing in the hot gas flow channel and the cold gas flowing in the cold gas flow channel.
Claims25
1-35. (canceled)
An aircraft comprising a pair of wings, a pair of airfoils and a pair of bypass turbofan engines each of said engines being mounted to one of the wings;
- wherein each engine comprises a module comprising a generally elongate housing, a central portion extending through the length of the module for exhausting the hot exhaust gas from the engine, and a peripheral portion surrounding the central portion for the bypass air from the engine;
- wherein the housing includes at least one outlet provided from the peripheral portion of the module through the housing to enable a portion of the bypass air to be separated from a remainder of the bypass air and to be directed out of the module at an angle to the axis of the module;
- wherein the engines and modules are arranged so that at least part of the portion of the bypass air is directed out of the modules flows over at least part of an upper surface of the associated airfoil when the aircraft travels at a predetermined speed.
The aircraft according to Claim 14, wherein the means for restricting fluid flow is a sleeve that includes holes that permit an amount of air to pass through the separator.
Dependencies are inferred from the claim text.