United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Jason David Liles

Conway Chuong

Russell J Bergman

Jose R Paulino

Scott D Lewis

Scott Daniel Virkler

Jonathan Ariel Scott

James F Wiedenhoefer

Kyle C Lana

William D Blickenstaff

Charles T Ruby

Veronika Reynolds

Chuong Conway

A replaceable rotor blade tip clearance measurement device for a gas turbine engine, includes a threaded section along an axis and an integral abradable tip with an internal lattice geometry that extends from the threaded section along the axis.

Replaceable rotor blade tip clearance measurement device for a gas turbine engine

A heat exchanger plate for provides heat transfer between a first flow along a first flowpath and a second flow along a second flowpath. The heat exchanger plate comprised a body having: a first face and a second face opposite the first face; a leading edge along the second flowpath and a trailing edge along the second flowpath; a proximal edge having at least one inlet port along the first flowpath and at least one outlet port along the first flowpath; and at least one passageway along the first flowpath. Along a proximal portion, the first face and the second face converge at a first angle. Along a distal portion, the first face and the second face converge at a second angle less than the first angle.

Aircraft heat exchangers and plates

A fairing sub-assemblyfor a turbine frame comprises an inner ring, an outer ringand a plurality of strut-shells. The inner ring is formed of a plurality of inner segments. The outer ring is formed of a plurality of outer segments. The plurality of strut-shellsconnecting the inner ringand the outer ring. In another embodiment, the fairing sub-assembly comprises an inner bandjoining the plurality of inner segmentsand the plurality of strut-shellsto form outer slots, and an outer bandjoining the plurality of outer segmentsand the plurality of strut-shellsto form inner slots. A method of assembling a fairingcomprises inserting the aforementioned fairing sub-assemblyinto an aft end of a turbine frame, inserting a plurality of forward strut-shellsinto the outer and inner slots at a forward end of the turbine frame, and joining the forward strut-shellsto the fairing sub-assembly

Bench aft sub-assembly for turbine exhaust case fairing

A gas turbine engine component comprises a frame and a fairing. The frame comprises a monolithic ring-strut-ring structure. The fairing comprises a multi-segment ring-strut-ring structure that is assembled around the frame. A method of assembling the frame and fairing comprises positioning a plurality of shroud segments within a frame and joining the plurality of shroud segments to each other so that the fairing is trapped within the frame. In one embodiment, the fairing comprises a plurality of outer diameter shroud segments, a plurality of inner diameter shroud segments, a plurality of strut segments, and stiffening features connected to the plurality of strut segments to strengthen the fairing.

Multi-piece fairing for monolithic turbine exhaust case

Growing community of inventors

Port Saint Lucie, FL, United States of America

Jason David Liles