United Technologies Corporation

Raytheon Technologies Corporation

John D Wiedemer

Keith A Santeler

James Thompson Beals

Dilip M Shah

Jacob A Snyder

Dominic J Mongillo, Jr

Brandon W Spangler

Paul M Lutjen

Daniel A Bales

Carl R Verner

Jonathan Lemoine

Gary L Grogg

Dinesh K Gupta

Dale William Petty

Sudhangshu Bose

Christopher R Joe

Blake J Luczak

Stephen Douglas Murray

Daniel F Paulonis

John J Marcin

James N Knapp

Joshua E Persky

Anita L Tracy

Corneil S Paauwe

Glenn A Cotnoir

Jason Arnold

Paul A Smith, Jr

Scott D Hjelm

Christopher J Lehane

Michael F Benamati

Venkat Seetharaman

Kevin D Carpenter

Stephen D Murray

Keith Santeler

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

Convective cooling of gas turbine engine airfoil platforms is enhanced by grooving the interface of the platforms with corresponding platform-to-platform seals, thereby accelerating cooling airflow over the platform surfaces.

Turbine airfoil with platform cooling

A turbine outer air seal includes, in a radially inner major surface thereof, at least one circumferential groove accommodating a plurality of holes which supply air for film cooling the radially inner surface of the air seal.

Turbine outer air seal

A refractory metal core for use in a casting system has a coating for providing oxidation resistance during shell fire and protection against reaction/dissolution during casting. In a first embodiment, the coating includes at least one oxide and a silicon containing material. In a second embodiment, the coating includes an oxide selected from the group of calcia, magnesia, alumina, zirconia, chromia, yttria, silica, hafnia, and mixtures thereof. In a third embodiment, the coating includes a nitride selected from the group of silicon nitride, sialon, titanium nitride, and mixtures thereof. Other coating embodiments are described in the disclosure.

Refractory metal core coatings

A composite core for an investment casting process, the core including both a ceramic portion and a refractory metal portion, with the refractory metal portion being so disposed as to perform the function of a plurality of such refractory metal elements. In particular, a refractory metal element attached to a trailing edge of a ceramic element extends beyond the plane of a tip end of the ceramic element so as to replace the refractory metal element otherwise extending from the ceramic tip edge. The refractory metal element also extends beyond the space to be occupied by the wax casting, both in the direction of the tip end and the trailing edge such that improved placement and securing of the core is facilitated during the casting process. A further embodiment uses a single refractory metal element that extends into both the airfoil portion and an orthogonal extending platform portion thereof.

Composite core for use in precision investment casting

A casting system for forming a gas turbine engine component is provided. The casting system, in a first embodiment, comprises a shaped refractory metal sheet having a plurality of features for forming a plurality of film cooling passages, which features are formed from refractory metal material bent out of the sheet. The casting system for forming a gas turbine engine component in a second embodiment comprises a metal wall having an airfoil shape and a refractory metal core adjacent the metal wall and having a shape corresponding to the shape of the metal wall.

Refractory metal core

A shroud for a rotor assembly disposed within a case is provided. The shroud includes suspension apparatus, a control ring, and a blade outer air seal. The suspension apparatus is disposed between the control ring and the case. The control ring includes a body and a first attachment mechanism. The blade outer air seal includes a second attachment mechanism. The first and second attachment mechanisms cooperate to secure the blade outer air seal to the control ring.

Rotor blade outer tip seal apparatus

Growing community of inventors

Glastonbury, CT, United States of America

John D Wiedemer