United Technologies Corporation

Raytheon Technologies Corporation

Sikorsky Aircraft Corporation

Razvan Virgil Florea

Thomas Gregory Tillman

William T Cousins

Claude G Matalanis

Mark B Stucky

Brian Ernest Wake

Eric D Gray

Luca Bertuccioli

Patrick Ormande Bowles

John D Wolter

Ray-Sing Lin

Barbara Brenda Botros

ByungYoung Min

David J Arend

A hybrid wing aircraft has an engine embedded into a body of the hybrid wing aircraft. The embedded engine has a fan that is received within a nacelle. The body of the aircraft provides a boundary layer over a circumferential portion of a fan. A system delivers additional air to correct fan stability issues raised by the boundary layer.

Embedded engines in hybrid blended wing body

In accordance with one aspect of the disclosure, an airfoil is disclosed. The airfoil may include a platform and a blade extending from the platform. The blade may have a root proximate the platform and a tip radially outward from the platform. The root may have a greater thickness than a cross-section at about a quarter-span of the blade or greater.

Airfoil with thickened root and fan and engine incorporating same

A gas turbine engine propulsion system and method of assembling such is disclosed. The gas turbine engine propulsion system comprises a gas turbine engine that includes a fan flow path. The fan flow path may extend from the fan inlet to the rear exhaust outlet of the bypass flow path. A portion of the fan flow path, proximal to the fan, is non-axisymmetric. The non-axisymmetric portion may be upstream or downstream of the fan.

Non-axisymmetric fan flow path

A rotary wing aircraft includes a fuselage having a plurality of surfaces. At least one engine is mounted in the fuselage. A rotor assembly includes a rotor shaft a plurality of rotor blades operatively connected to the rotor shaft. The rotor assembly includes a plurality of surface portions. An active air discharge opening extends through one of the plurality of surfaces of the fuselage and one of the plurality of surface portions of the rotor assembly, and an active air generation system is mounted in the fuselage. The active air generation system is configured and disposed to generate and direct a flow of air through the active air discharge opening to disrupt an airstream flowing over the one of the plurality of surfaces of the fuselage and the one of the plurality of surface portions of the rotor assembly.

Active airflow system and method of reducing drag for aircraft

A gas turbine engine has an inlet duct formed to have a shape with a first ellipse in one half and a second ellipse in a second half. The second half has an upstream most end which is smaller than the first ellipse. The inlet duct has a surface defining the second ellipse which curves away from the first ellipse, such that the second ellipse is larger at an intermediate location. The second ellipse is even larger at a downstream end of the inlet duct leading into a fan.

Gas turbine engine inlet wall design

A method for designing gas turbine engine components using a coupled parametric analysis of part geometry and flow control is disclosed. Included are the steps of parametrically defining the geometry of the duct wall shape, parametrically defining one or more flow control actuators in the duct wall, measuring a plurality of performance parameters or metrics (e.g., flow characteristics) of the duct and comparing the results of the measurement with desired or target parameters, and selecting the optimal duct geometry and flow control for at least a portion of the duct, the selection process including evaluating the plurality of performance metrics in a pareto analysis. The use of this method in the design of inter-turbine transition ducts, serpentine ducts, inlets, diffusers, and similar components provides a design which reduces pressure losses and flow profile distortions.

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Manchester, CT, United States of America

Razvan Virgil Florea