United Technologies Corporation

Raytheon Technologies Corporation

Jaimie Schweitzer

Brandon W Spangler

Thomas E Clark

Timothy M Davis

Jose R Paulino

Richard K Hayford

Scott Daniel Virkler

Edwin Otero

Zhong Ouyang

Daniel A Snyder

Kyle C Lana

Jonathan Perry Sandoval

Kevin D Smith

Jeremy Drake

Brian C McLaughlin

Terence P Tyler

Hector M Pinero

Peter J Milligan

Jaimie Taraskevich

Dairus Deylan McDowell

Di Wu

Jr Terence P Tyler

An example turbine includes a turbine disk and a turbine blade. The turbine disk includes a plurality of lugs and a plurality of slots. Each of the plurality of lugs is located between two of the plurality of slots. Each of the plurality of lugs includes a tab that extends radially outwardly from an end of the lug. The tab has a first section having an upper surface and a second section having an upper surface. The upper surface of the first section is inclined greater than the upper surface of the second section, and the upper surface of the first section of the tab defines a contour. The turbine blade includes a root received in one of the plurality of slots and a platform, and the platform has a lower surface defining a contour. When the turbine blade is received in one of the plurality of slots, the lower surface of the platform is located above a portion of the upper surface of the first section of the tab, and the contour of the upper surface of the first section of the tab matches the contour of the lower surface of the platform.

Turbine blade damper seal

A gas turbine engine includes a stator vane. A blade outer air seal may be adjacent to the stator vane. A seal assembly may be disposed between the blade outer air seal and the stator vane. The seal assembly may include a first seal disposed between a first airflow path and a second airflow path. A second seal may be disposed between the first airflow path and the second airflow path. The second seal may be disposed in a series arrangement with the first seal.

Engine air sealing by seals in series

Aspects of the disclosure are directed to a seal comprising: a first leg that emanates from a center point of the seal and is configured to contact a first component, a second leg that emanates from the center point and is configured to contact a second component that is operative at a temperature that is within a range of 648 degrees Celsius to 1093 degrees Celsius, and a third leg that emanates from the center point.

Creep resistant axial ring seal

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Newton, NH, United States of America

Jaimie Schweitzer