United Technologies Corporation

Raytheon Technologies Corporation

Paul Thomas Rembish

Gregory E Reinhardt

Steven Clarkson

Daniel W Major

Daniel K Van Ness

Barry William Spaulding

Donald Summers

Edward F Pietraszkiewicz

Steven J Feigleson

Carl Brian Klinetob

Thomas B Hyatt

Christopher B Jelks

Scott W Gayman

Ryan Shepard Levy

Sandra S Pinero

Steven L Conner

Jesse Gannelli

Daniel L Van Ness

Daniel K Van Ness Ii

A case for a gas turbine engine includes a case body defining an axially extending core flow path, a radially extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A lubricant conduit is connected to the case body and is in thermal communication with the structure-supporting member.

Gas turbine engines with heated cases

A gas turbine engine includes a fan that includes a plurality of fan blades rotatable about an axis. An on-wing portion includes a compressor section and a combustor that is in fluid communication with the compressor section. A turbine section is in fluid communication with the combustor. A core flow path is arranged within a core nacelle. The fan is arranged upstream from the core flow path. A fan drive gear system module is coupled to the turbine section for rotating the fan about the axis. A connector assembly including first and second members respectively is secured to the on-wing portion and the fan drive gear system module. The first and second members are removably secured to one another by radially extending fasteners. The first members are connected to an on-wing portion of the gas turbine engine and the second members are connected to the fan drive gear system module. The fasteners are accessible through the bypass flow path.

Fan drive gear system module and inlet guide vane coupling mechanism

A turbofan engine structural guide vane is mounted to a forward bulkhead of a core engine case structure at an inner end and to a fan case at an outer end. A plurality of shear pins extend from the aft portion of the structural guide vane into a corresponding plurality of openings defined in the bulkhead for bearing circumferential loads.

Structural guide vane circumferential load bearing shear pin

A connection assembly for securing a fan drive gear system module within a gas turbine engine includes first and second members removably secured to one another by radially extending fasteners.

A case for a gas turbine engine includes a core body. The core body defines a longitudinally extending core flow path, a laterally extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A heating element is connected to the core body and is in thermal communication with the structure-supporting member.

Core case heating for gas turbine engines

A tool for forming a trench and a plurality of cooling holes within the trench includes a body, the body including a ridge portion extending along a first side of the tool. The ridge portion is operable to mate with a workpiece to form a trench on the workpiece. A plurality of electrodes extend from the ridge portion and are oriented to form a plurality of cooling holes within the trench on the workpiece.

Method of creating an airfoil trench and a plurality of cooling holes within the trench

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East Hampton, CT, United States of America

Paul Thomas Rembish