United Technologies Corporation

Raytheon Technologies Corporation

Pratt-whitney Canada Corp

Rtx Corporation

Karl D Blume

Steven H Zysman

Jesse W Clauson

James H Anderson

William G Sheridan

Enzo DiBenedetto

Gregory E Reinhardt

John C DiTomasso

Jeffrey M Simpson

Andreas Sadil

Dale William Petty

Joseph T Caprario

Steven J Bauer

Holly Teufel

Alan D Munroe

Xiaojun Campbell

Michael C Rhodes

Robert E Gurney

William O Taylor

Graham A Kaiser

Karl Milenkovic

Tsering Dolma

John P Tirone

John H Mosley

Assaf Farah

Bruce Fielding

Theodore W Kapustka

Gregory E Chetta

Chris J Niggemeier

Lam Nguyen

Joseph N Cerino

Jason W Mazanec

Duncan C Meyers

Henry Huizinga

Kurt Link

David W Leung

Dennis L Mackey

Amy U Serwinowski

Charlie Quackenbush

Frank Shurick

Robert Rozelle

Jonathan Schmid

James Schubauer

Holly Teuful

Christopher Hall

A gas turbine engine includes a compressor section, a combustor, and a turbine section. A bleed tap taps air from the compressor section through a bleed valve. The bleed valve is selectively opened by a control to dump air from the compressor section to a dump outlet. A heat exchanger duct includes a duct air inlet to cool a fluid in a heat exchanger and a duct air outlet. The dump outlet is within the heat exchanger duct.

Engine bleed air ducting into heat exchanger

An inner diffuser case for use in a combustor of a gas turbine engine includes a multiple of struts across an annular flow path between an outer shroud and an inner shroud, at least one of the multiple of struts is an open strut.

Inner diffuser case struts for a combustor of a gas turbine engine

A disclosed fan drive gear system for a gas turbine engine includes a first fan shaft coupled to a second fan shaft, a first shaft support bearing assembly disposed about the first fan shaft and a second shaft support bearing assembly disposed about the second fan shaft. A planetary gear system is coupled to the second fan shaft. A transfer bearing is configured to receive lubricant from a lubricant input and is positioned between the first and second fan shaft support bearings. A second bearing is configured to rotate with the second fan shaft and receive lubricant from the transfer bearing and communicate lubricant to at least one lubricant passage and a conduit fluidly connecting the at least one lubricant passage to the planetary gear system.

Fan drive gear system including a two-piece fan shaft with lubricant transfer leakage recapture

A gas turbine engine has a spool including compressor and turbine rotors connected by a first shaft. The first shaft extends concentrically around a second shaft. The first shaft forward end has a portion with an inner diameter of close tolerance with the second shaft. The second shaft has a region of enlarged diameter located axially aft of the compressor rotor but axially forward of the forward end of the first shaft. The region of enlarged diameter has a diameter greater than the inner diameter of the forward end portion of the first shaft to cause the region of enlarged diameter of the second shaft to engage the first shaft in interference in the event that the second shaft is moved axially aft relative to the first shaft more than a pre-selected axial distance.

Gas turbine rotor containment

A turbofan engine comprises an engine case. A gaspath extends through the engine case. A fan has a circumferential array of fan blades. A fan case encircles the fan blades radially outboard of the engine case. A plurality of fan case vanes extend aftward and outward from the engine case to the fan case. A forward frame comprises a plurality of vanes radially across the gaspath. A torque box couples the fan case vanes to the forward frame. A transmission couples a shaft to a fan shaft to drive the fan. A fan bearing assembly couples a stationary forward hub structure to the fan shaft.

Fan rotor support

A method for designing an engine case static structure of a gas turbine engine includes creating signals representing an engine case static structure knowledge base of information. The knowledge base has a plurality of design rule signals with respect to a corresponding plurality of parameter signals of associated elements of an engine case static structure, wherein the knowledge base comprises at least one data value signal for each of the plurality of design rule signals. A desired data value signal is entered for a selected one of the plurality of parameter signals of an associated element of the engine case static structure and compared to the corresponding data value signal in the knowledge base for the corresponding one of the plurality of design rule signals. Signals representative of a geometric representation of the selected parameter signal may be created.

Method and system for designing frames and cases

A method and apparatus which facilitate separation of a gas turbofan powerplant into modules for shipping, maintenance and repair is disclosed. Various construction details are developed which provide means for mounting a fan cowling to an engine core in a manner which permits transference of operational loads from the fan cowling to the engine core and separation of the fan cowling from the engine core. In one embodiment, a fan cowling (46) is attached to an engine core (18) by a plurality of radially extending through struts (64). The through struts include a bolted joint (72) which permits separation of a powerplant (12) into a first module and a second module. For this embodiment, a method for varying between an assembled and disassembled condition is comprised of manipulating the joints between an engaged and disengaged position and axially moving the separate modules along a longitudinal centerline (14).

Method of disassembling a gas turbine engine power plant

Separable fan strut for a gas turbofan powerplant

Growing community of inventors

Hebron, CT, United States of America

Karl D Blume