United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Pedro David Laureano

Christopher M Juh

John A Lucena

Frederick M Schwarz

Bryan P Dube

Edwin Otero

Jeffrey Michael Jacques

Emma J Place

Mohamed Hassan

Shu Liu

Andrew Correia

Bernard Joseph Reilly, Iii

William R Hackbarth, Ii

Raghib A Chowdhury

A piston seal ring including a body shaped as an annular ring having an inner diameter and an outer diameter; an end gap formed in the body; a first interface surface formed on the body between the inner diameter and the outer diameter; a second interface surface orthogonally adjacent the first interface surface; and a receiver extending from the first interface surface substantially opposite the end gap, the receiver including a cavity configured to support a lug.

Aircraft piston seal ring including anti-rotation provisions

An attachment root for a blade includes a symmetric serration profile with multiple lobes. Contact surfaces of each lobe form equal contact angles with a line normal to a symmetry plane of the serration profile. Non-contact surfaces of lobes form angles greater than three degrees relative to the line that increase in a radially inward direction.

Turbine airfoil attachment with serration profile

A shaft for a gas turbine engine includes an inner contour with a stiffening rib that defines a stiffened wall thickness related to a nominal wall thickness according to a ratio between about 1.125-2.1.

Stiffened rotor shaft for a gas turbine engine

A turbine blade includes an airfoil including a pressure side and a suction side. A platform includes a pressure side wall and a suction side wall, and has a leading edge end wall and a trailing edge end wall. A pocket is positioned under the platform on the pressure side. A hole has a first end communicating with the pocket and having a second end communicating with the pressure side wall. A gas turbine engine is also disclosed.

Turbine blade cooling hole for side wall

A turbine blade includes an airfoil, a platform and a suction pocket positioned under the platform on a suction side. The suction pocket includes a platform underside, and a fillet connecting the platform underside into a neck. The neck extends into a fir tree. A first cooling hole extends from a first end in the platform underside to a second end in a top surface of the platform. A second cooling hole extends from a first end in the platform underside, but closer to the fillet than is the first end of the first cooling hole, to a second end in the top surface. There is a third cooling hole having a first end in the fillet and extending to a second end at the top surface. A gas turbine engine is also disclosed.

Turbine blade cooling hole combination

A disclosed gas turbine engine includes a compressor section including a first compressor disposed axially forward of a second compressor, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The turbine section includes a first turbine driving the first compressor and a second turbine driving the second compressor. An inner shaft defines a driving link between the second compressor and the second turbine and an outer shaft defines a driving link between the first compressor and the first turbine. The inner shaft and the outer shaft are concentric about a common axis of rotation. A bumper is disposed on the inner shaft within an axial region common to an aft portion of the outer shaft for accommodating interaction between the inner and outer shafts during high load conditions.

Geared turbofan engine with inter-shaft deflection feature

An example coupling stack includes a first rotating member and a second rotating member. A plurality of aligned slots is defined in the first rotating member and the second rotating member. A tab lock is provided having an annular body with an axial front side, an axial back side, and a radial inner periphery. Tabs are formed on the axial back side and inserted into the plurality of aligned slots. The annular body of the tab lock also includes a plurality of openings extending into the radial inner periphery. A plurality of flanges is provided on the axial back side of the annular body adjacent to the plurality of openings.

Growing community of inventors

Jacksonville, FL, United States of America

Pedro David Laureano