United Technologies Corporation

Raytheon Technologies Corporation

Herbert L Walker

Jonathan D Little

Arun Kumar Jayasingh

Bernard W Pudvah

Richard D Trask

Mark Boyer

Stephen A Hilton

John P Fournier

Manjunath Subramanya

JoAnn Barbieri

Gordon Miller Reed

David Maliniak

Daniel J Monahan

Stevan W Akerley

Anthony T Lindsey

Vernon E Estes

Henry Yazdzik, Jr

Veerachari J Mayachari

Rakesh Sharma N Dumavath

Arun Jayasingh

A variable vane stabilizer is disclosed. One or more variable vane stabilizer may be interconnected between/among two or more vanes of a gas turbine engine in order to fix the angle of attack of the vanes.

Variable vane stabilizer

A gas turbine engine includes a nosecone assembly attached to a gas turbine engine. The nosecone assembly includes a support structure and a nosecone attached to the support structure. The nosecone includes at least a first tool hole extending through the nosecone. The first tool hole is structurally reinforced.

Removable nosecone for a gas turbine engine

An assembly for a gas turbine engine includes a rotor formed by a drum and a hub. The drum has a generally conically shaped inner surface that defines a flow path along a first cavity. The hub is connected to the drum and has a conically shaped inner surface that defines a flow path along a second cavity.

Gas turbine engine rotor drain feature

A gas turbine engine includes a compressor section and a nosecone assembly. The compressor section includes an inlet guide vane assembly including an inner shroud, an outer shroud, and an inlet guide vane extending from the inner shroud to the outer shroud. The nosecone assembly is attached to the inner shroud.

Gas turbine engine with attached nosecone

Disclosed is a structural frame for a gas turbine engine comprising an integral fluid reservoir and air/fluid heat exchanger. A central hub includes a reservoir for storing a fluid and an outer rim circumscribes the hub. A heat exchanger is fluidly coupled to the reservoir and is in simultaneous communication with the fluid and an air stream.

Gas turbine engine frame with an integral fluid reservoir and air/fluid heat exchanger

A windmilling brake system for a turbine engine includes a brake drum (,) on an interior surface of an engine rotor. The drum circumscribes a brake unit (,) that includes a brake ring (,) with brake shoes (,) each connected to the ring by respective springs (,). A leg (,) extends from each shoe and toward the ring. The ring is sandwiched axially between bolting flanges (,) on forward and aft carrier portions (,) of a two piece, variable stiffness, dual load path rotor bearing support. Nonsacrificial fasteners secure the ring to one of the flanges while frangible fasteners (,) secure the flanges to each other. The frangible fasteners also extend through an eye (,) in each leg to deflect the springs and hold the brake shoes in an armed state out of contact with the drum. Upon being exposed to abnormal imbalance loads, the frangible fasteners fail in tension to disable one of the two load paths. The failure also enables the springs to concurrently force the shoes into a deployed state in which the shoes contact the drum and inhibit rotor windmilling.

Turbine engine windmilling brake

A process for joining a base for an airfoil to a disk for an integrally bladed rotor stage in a gas turbine engine includes providing a disk having a radially outer rim with a slot defined therein by a recessed surface, and further includes providing a base having a longitudinally extending root portion facing opposite a longitudinally extending support portion for supporting the airfoil. The root portion has a root surface and the support portion has an outer surface. The process further includes bringing the root surface of the root portion into contact with the recessed surface bounding the slot, applying pressure and relative movement between the base and the rim to achieve during welding, substantial contiguity between the root surface and the recessed surface over the area of the recessed surface, resulting in a substantially continuous linear friction weld between the base and the rim.

Method for linear friction welding and product made by such method

Blade attachment slots for gas turbine engines are prepared by grinding to a stepped, generally straight sided configuration, semi-finish grinding to an envelope about 0.005 inches to 0.010 inches above the blueprint configuration, and finishing by broaching. This reduces the overall cost of the manufacturing process, permits a more economical use of existing broach machines, and allows greater versatility for short model runs and 'just-in-time' production.

Growing community of inventors

Bloomfield, CT, United States of America

Herbert L Walker