Theodore W Kapustka

US Patent:

20090142182, Jun 4, 2009

Filed:

Dec 3, 2007

Appl. No.:

11/949206

Inventors:

Theodore W. Kapustka - Glastonbury CT, US

Assignee:

UNITED TECHNOLOGIES CORP. - Hartford CT

International Classification:

F01D 25/16

US Classification:

415142

Abstract:

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.

US Patent:

20120141294, Jun 7, 2012

Filed:

Dec 2, 2011

Appl. No.:

13/309709

Inventors:

Bruce Fielding - Glen Williams, CA
Assaf Farah - Charlemagnes, CA
Karl D. Blume - Hebron CT, US
Lam Nguyen - Brossard, CA
Theodore W. Kapustka - Glastonbury CT, US

International Classification:

F01D 25/00

US Classification:

416244 R

Abstract:

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.

US Patent:

20130224010, Aug 29, 2013

Filed:

Feb 23, 2012

Appl. No.:

13/403407

Inventors:

Jorge I. Farah - Hartford CT, US
Theodore W. Kapustka - Glastonbury CT, US
Jonathan P. Burt - Sturbridge MA, US
Jonathan J. Jakiel - Vernon CT, US
Dana P. Stewart - Vernon CT, US

International Classification:

F01D 25/24
B23K 31/02
F01D 1/04

US Classification:

4152092, 228178

Abstract:

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.