United Technologies Corporation

Gknaerospace Sweden Ab

Pratt-whitney Canada Corp

Theodore W Kapustka

Glenn Levasseur

Joakim Berglund

Johan Ockborn

Daryl B Mountz

Bengt Pettersson

Marcus Borg

Anders Svahn

Jorge I Farah

Assaf Farah

Karl D Blume

Joseph James Sedor

Jonathan P Burt

Bruce Fielding

Dana P Stewart

Lam Nguyen

Jonathan J Jakiel

An assembly is provided for a turbine engine. This turbine engine assembly includes a tie-rod and a threaded retainer. The tie-rod includes a tie-rod threaded portion and a tie-rod unthreaded portion. The threaded retainer includes a retainer threaded portion and a retainer unthreaded portion. The retainer threaded portion is mated with the tie-rod threaded portion. The retainer unthreaded portion is radially engaged with the tie-rod unthreaded portion.

Moment accommodating fastener assembly

A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least in part of a first material. The central hub is formed at least in part of a second material.

High durability turbine exhaust case

A gas turbine engine has a spool including compressor and turbine rotors connected by a first shaft. The first shaft extends concentrically around a second shaft. The first shaft forward end has a portion with an inner diameter of close tolerance with the second shaft. The second shaft has a region of enlarged diameter located axially aft of the compressor rotor but axially forward of the forward end of the first shaft. The region of enlarged diameter has a diameter greater than the inner diameter of the forward end portion of the first shaft to cause the region of enlarged diameter of the second shaft to engage the first shaft in interference in the event that the second shaft is moved axially aft relative to the first shaft more than a pre-selected axial distance.

Gas turbine rotor containment

A static structure of a gas turbine engine includes a multiple of airfoil segments and at least one structural reinforcement ring mounted to the multiple of airfoil segments.

Turbine frame fairing for a gas turbine engine

Gas turbine engines and related systems involving offset hub struts are provided. In this regard, a representative bearing assembly for a gas turbine engine includes: a bearing operative to support a rotatable shaft; an annular hub positioned about the bearing; and an annular array of struts extending radially outwardly from the hub, at least two of the struts being positioned in different planes, the planes being oriented transversely with respect to the rotatable shaft. The method of assembling the struts by mounting first and second pluralities of struts, each plurality in a common plane, between the hub and the turbine exhaust case, with the second plurality of struts longitudinally offset from the first plurality of struts.

Gas turbine engines and related systems involving offset turbine frame struts

Growing community of inventors

Glastonbury, CT, United States of America

Theodore W Kapustka