United Technologies Corporation

Raytheon Technologies Corporation

Randall J Brown

Bradley T Duelm

Kevin W White

Nathan A Shirk

Lewis M Holby

Jonathan Ariel Scott

Henry K Webster

Alan D Lees

An annular finger seal includes a base portion defining a base edge of the annular finger seal and having a center pass-through aperture. The base edge may be substantially continuous. The annular finger seal may also include a finger portion defining a finger edge of the annular finger seal and including a plurality of fingers. The finger edge may be segmented by gaps disposed between adjacent fingers of the plurality of fingers. A gas turbine engine includes a combustor section, a turbine section, and an annular finger seal. The annular finger seal includes a plurality of fingers and the annular finger seal is disposed at an adjoining interface between the combustor section and the turbine section. The annular finger seal may be mounted to the turbine section and may engage a radially inward facing surface, relative to the engine central longitudinal axis, of the combustor section.

Combustor finger seal

A finger seal for a gas turbine engine is disclosed. The finger seal includes a first leg, a second leg, a third leg, a fourth leg, a first bend segment disposed between the first leg and the second leg, a second bend segment disposed between the second leg and the third leg, and a third bend segment disposed between the third leg and the fourth leg. The third bend segment is radially outward of the first bend segment relative to an axial centerline of the gas turbine engine.

Triple bend finger seal and deflection thereof

A seal for a gas turbine engine includes a top, a bottom, a left side, a right side, a back and a front. The back is parallel to the front and the left side is parallel to the right side such that a non-square shape is formed by the intersection of the back, the left side, the front and the right side. The top includes a first vane mating surface and the bottom includes a second vane mating surface.

Universal seal

A seal for a gas turbine engine is shown. The engine may have a first vane for imparting a first twist to air passing thereby and/or a second vane for imparting a second, different twist to air passing thereby, each of the first and second vanes having a mounting area for mounting the seal thereto. The seal includes a top, a bottom, a left side, a right side a back, and a front. The back is parallel to the front and the left side is parallel to the right side such that a non-square shape is formed by the intersection of the back, the left side, the front and the right side so that the seal may mate with the mounting area of the first vane and, if the seal is inverted, may mate with the mounting area of the second vane.

Growing community of inventors

Hartford, CT, United States of America

Randall J Brown