Raytheon Technologies Corporation

United Technologies Corporation

Rtx Corporation

General Electric Company

Raytheon Technoiogies Corporation

Dustin Wayne Davis

Ryan C Breneman

Joseph V Mantese

John Joseph Marcin

David Ulrich Furrer

James Tilsley Auxier

Andrew Joseph Boyne

Thomas Anthony Rebbecchi

Tracy A Propheter-Hinckley

Benjamin Bellows

Trevor Rudy

Brandon W Spangler

Mark F Zelesky

Stephen Karl Kramer

James B Hoke

Steven Bruce Gautschi

Dennis M Moura

Lance L Smith

Joel H Wagner

Atul Kohli

Ricardo Trindade

John R Paulus

Jonathan Lemoine

Kevin Zacchera

Jeffrey Jay Lienau

Won-Wook Kim

Steven J Bullied

John Saunders Stevenson

Zhongtao Dai

John E Holowczak

Adam Rasheed

Aaron John Avagliano

Dave J Hyland

Richard Sterling Tuthill

John J Marcin

Scott A Liljenberg

Justin Thomas Brumberg

David J Hyland

Shailesh Singh Bhaisora

Cliff Yi Guo

Ravindra Devi

Ingrid H Kerscht

Samir Baban Tambe

Benjamin D Bellows

Andrew Boyne

Tracy A Propheter-Hinkley

Richard S Tuthill

A gas turbine engine combustor section extends axially from a pre-diffuser at a forward end to an aft end relative to an engine axis. The gas turbine engine combustor section includes a combustor liner defining a combustion chamber and a combustor dome situated at a forward end of the combustor liner and affixed thereto. The gas turbine engine combustor section further includes an electrostatic particulate matter collector. The electrostatic particulate matter collector includes a first charged flow guide having an axially forward-most extent aligned with the pre-diffuser and widens radially with respect to the engine axis from the forward-most extent to the combustor dome. The electrostatic particulate matter collector further includes a fuel nozzle extending through the first charged flow guide into the combustor dome. The electrostatic particulate matter collector also includes a power supply electrically coupled to positively charge the first charged flow guide.

Electrostatic flow guide dirt collector

An assembly is provided for a turbine engine with a flowpath. This assembly includes a fuel source and an engine component. The engine component forms a peripheral boundary of the flowpath. The engine component includes a component internal passage. The engine component is configured to receive fuel from the fuel source. The engine component is configured to crack at least some of the fuel within the component internal passage thereby cooling the engine component and providing at least partially cracked fuel. The assembly is configured to direct the at least partially cracked fuel into the flowpath for combustion.

Fuel-cooled engine component(s)

A core element of an investment core for use in a casting process used to produce an airfoil includes an investment core body, an extension connected to and protruding from the investment core body, and a connection portion connected to the investment core body and to the extension. The investment core body includes a ceramic material. A shape of the extension includes a tube with a centerline axis passing through a center of the extension. A shape of a cross-section of the extension taken along a plane perpendicular to the extension centerline axis includes an ellipse. The extension is connected to the investment core body by the connection portion.

Cast-in film cooling hole structures

A mid-turbine frame for a gas turbine engine includes an inner frame case defining a sealed torque box cavity. Multiple spokes protrude radially outward from the inner frame case, and at least one service line is connected to the inner frame case.

Mid turbine frame including a sealed torque box

A core element of an investment core for use in a casting process used to produce an airfoil includes an investment core body, an extension connected to and protruding from the investment core body, and a connection portion connected to the investment core body and to the extension. The investment core body comprises a ceramic material. A shape of the extension comprises a tube with a centerline axis passing through a center of the extension. A shape of a cross-section of the extension taken along a plane perpendicular to the extension centerline axis comprises an ellipse. The extension is connected to the investment core body by the connection portion.

A process for directional solidification of a cast part comprises energizing a primary inductive coil coupled to a chamber having a mold containing a material; energizing a primary inductive coil within the chamber to heat the mold via radiation from a susceptor, wherein the resultant electromagnetic field partially leaks through the susceptor coupled to the chamber between the primary inductive coil and the mold; determining a magnetic flux profile of the electromagnetic field; sensing a magnetic flux leakage past the susceptor within the chamber; generating a control field from a secondary compensation coil coupled to the chamber, wherein the control field controls the magnetic flux experienced by the cast part; and casting the material within the mold under the controlled degree of flux leakage.

Method for magnetic flux compensation in a directional solidification furnace utilizing a stationary secondary coil

A process for directional solidification of a cast part comprises energizing a primary inductive coil coupled to a chamber having a mold containing a material; generating an electromagnetic field with the primary inductive coil within the chamber, wherein said electromagnetic field is partially attenuated by a susceptor coupled to said chamber between said primary inductive coil and said mold; determining a magnetic flux profile of the electromagnetic field after it passes through the susceptor; sensing a component of the magnetic flux in the interior of the susceptor proximate the mold; positioning a mobile secondary compensation coil within the chamber; generating a control field from a secondary compensation coil, wherein said control field controls said magnetic flux; and casting the material within the mold.

Method for magnetic flux compensation in a directional solidification furnace utilizing an actuated secondary coil

An induction furnace assembly comprising a chamber having a mold; a primary inductive coil coupled to the chamber; a layered susceptor comprising at least two layers of magnetic field attenuating material surrounding the chamber between the primary inductive coil and the mold to nullify the electromagnetic field in the hot zone of the furnace chamber.

Multi-layer susceptor design for magnetic flux shielding in directional solidification furnaces

A method of removing a core of a cast component includes providing a casting that includes a silica based ceramic core in a temperature controlled closed volume; cycling temperature between a first temperature and a second temperature within the temperature controlled closed volume that repeatedly subjects the silica based ceramic core to a beta-to-alpha cristobalite transition that induces microfractures in the silica based ceramic core; and after the cycling temperature, chemically dissolving the silica based ceramic core from the casting.

Casting core removal through thermal cycling

A combustor for a gas turbine engine includes a combustor shell having a shell opening therethrough, a combustor panel having a stud attached thereto, the stud extending through the shell opening. The stud includes a standoff to define an intermediate passage between the combustor shell and the combustor panel. A retainer is attached to the stud. A washer surrounds the stud and is positioned between the retainer and the combustor shell. The washer at least partially defines a cooling flow passage configured to direct a cooling airflow through the shell opening to impinge the cooling flow on at least one of the stud or the standoff.

Washer for combustor assembly

A combustor panel may include an attachment feature. Because conventional attachment features of conventional combustor panels may be insufficiently cooled, the present disclosure provides various combustor configurations for reducing hotspots in the vicinity of attachment features and/or for providing cooling airflow to and in the vicinity of attachment features.

Cooling configurations for combustor attachment features

Growing community of inventors

Marlborough, CT, United States of America

Dustin Wayne Davis