United Technologies Corporation

Raytheon Technologies Corporation

Jason Arnold

Graham Ryan Philbrick

Patrick D Couture

Thomas A Mariano

Scott Daniel Virkler

Jonathan Lemoine

Dale William Petty

John D Wiedemer

Graham R Philbrick

An example diffuser assembly includes a diffuser case, an annular ring, and a retaining tab that is mounted to the annular ring and has an end that engages an inner wall of the diffuser case. The engagement between the second end and the inner wall locks the retaining tab and limits movement of the annular ring along a central longitudinal axis of the diffuser case. Another example diffuser assembly includes a diffuser case, an annular ring, and a snap ring. The snap ring is situated in an annular groove of an inner wall of the diffuser case, and restricts movement of the annular ring along a central longitudinal axis of the diffuser case. A retaining tab is affixed to either the annular ring or the diffuser case, and has an end retaining the annular ring in the annular groove.

Retaining tab for diffuser seal ring

Disclosed is an active tip clearance control system (ATCCS) for a gas turbine engine, having an electronically controlled regulating valve directing cooling airflow to a turbine case, and an engine electronic control (EEC), controlling the electronically controlled regulating valve, wherein the EEC controls the electronically controlled regulating valve to regulate cooling airflow according to a selected target blade tip clearance schedule, and wherein the selected target blade tip clearance schedule is selected before or after an engine cycle, from of a plurality of target blade tip clearance schedules, each correlating to one of a plurality of thrust rating applications for the engine.

Thrust rating dependent active tip clearance control system

Aspects of the disclosure are directed to systems and methods for receiving operating state parameters associated with an operative state of an aircraft, determining a clearance value between a first structure of the engine and a second structure of the engine, where the clearance value is determined based on the operating state parameters and a passive clearance model that includes a specification of an uncertainty in the clearance value, determining that the clearance value deviates from a clearance target in an amount that is greater than a threshold, and engaging an active clearance control (ACC) mechanism based on the deviation.

Active clearance control for a turbine and case

Disclosed is a coupling system comprising joints configured to friction lock under compressive pressure via tapered teeth for joining rotating components, which may be rotating components of a gas turbine, or other engine. The coupling system provides the alignment orientation for the joined components, and eliminates the need for extraneous fasteners, bolts, interference fits and/or keying arrangements. The coupling system further enables material optimization by allowing for use of different materials throughout different engine sections, depending on the operating parameters.

Coupling system comprising self locking joint

A ring has a ring body with a central portion surrounding an axis and extending to first and second opposing ends separated by a split. The central portion has a first axial thickness. At least one retaining feature is formed on the ring body, the at least one retaining feature having a second axial thickness greater than the first axial thickness. An assembly and a gas turbine engine are also disclosed.

Balance ring for gas turbine engine

An interstage coverplate assembly is provided for a rotor assembly. The coverplate assembly includes an annular first coverplate, an annular second coverplate and an annular coverplate lock that extends axially between and rotatably connects the first and the second coverplates. The first coverplate includes a plurality of coverplate tabs arranged circumferentially around an axial centerline. The coverplate lock includes a plurality of lock tabs arranged circumferentially around the centerline. A first of the lock tabs circumferentially engages a first of the coverplate tabs.

Interstage coverplate assembly for arranging between adjacent rotor stages of a rotor assembly

A rotor disk assembly for a gas turbine engine includes a rotor disk with a circumferentially intermittent slot structure that extends radially outward relative to an axis of rotation. A heat shield has a multiple of radial tabs engageable with the circumferentially intermittent slot structure to provide axial retention of the cover plate to the rotor disk.

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Rocky Hill, CT, United States of America

Jason Arnold