Raymond J. Bruchez
Engineering in West Palm Beach, FL

5697213, Dec 16, 1997

Dec 18, 1996

8/769173

Keith S. Brewer - North Palm Beach FL
Raymond J. Bruchez - North Palm Beach FL

F02K 182

60261

A liner for a gas turbine engine is provided which includes an outer wall, an inner wall, a plurality of standoffs, a plurality of attachment assemblies, and a plurality of tapered ribs. The inner wall sections each have a first edge and a second edge. The standoffs are attached to the inner wall sections, and separate the inner and outer walls. The attachment assemblies fix at least one standoff, per inner wall section, to the outer wall section. Each tapered rib has a pair of surfaces tapering from a greater end to a lesser end. The tapered ribs are attached to the outer wall, with the lesser end is in contact with the outer wall and the tapered surfaces disposed between, and in contact with, adjacent inner wall sections.

5704208, Jan 6, 1998

Dec 5, 1995

8/567644

Keith S. Brewer - North Palm Beach FL
Raymond J. Bruchez - North Palm Beach FL

F02K 182

60261

A serviceable liner is provided comprising an outer wall, an inner wall, a plurality of standoffs disposed between the walls, and a plurality of attachment assemblies for attaching the walls to one another. The outer wall includes a plurality of first apertures. The inner wall includes a plurality of sections, each section having at least one second aperture. Each attachment assembly includes a fastener and an insert. An insert is received within each first aperture and a fastener is received within each insert.

4799623, Jan 24, 1989

Nov 4, 1987

7/116930

Raymond J. Bruchez - Lake Park FL
Gunther Eichhorn - Palm Beach Gardens FL
Elliott C. Kiblinger - North Palm Beach FL

United Technologies Corporation - Hartford CT

F02K 108

23926541

A variable area convergent divergent nozzle has floating divergent flaps which shift from a low mode to a high mode depending on internal and external pressure. The lost motion connection which permits this is biased to retain the appropriate mode for long term cruise conditions, to reduce ovalization of the nozzle, and to stabilize and/or dampen vibrations.

H5282, Oct 4, 1988

Jun 4, 1986

6/870552

Raymond J. Bruchez - Lake Park FL
Gary A. Schirtzinger - Juno FL
Gunter Eichhorn - North Palm Beach FL

The United States of America as represented by the Secretary of the Air
Force - Washington DC

F02G 300

60752

A heat shield assembly 10 for attachment to an afterburner liner 18. The heat shield assembly 10 comprises a clamp 14 and an optional support bracket 16 which hold a carbon-carbon panel 12 adjacent to the liner 18. The carbon-carbon panel shields a damaged area 20 of the liner in order to extend the liner's service life.

4203285, May 20, 1980

Feb 6, 1978

5/875664

Kurt J. Hanloser - North Palm Beach FL
Raymond J. Bruchez - Lake Park FL
James T. Gill - North Palm Beach FL

The United States of America as represented by the Secretary of the Air
Force - Washington DC

F02K 310

60261

A partial swirl augmentor for a turbofan engine having an annular duct for directing hot gases into the augmentor combustion chamber. Located within the combustion chamber is a piloted vee-gutter flameholder system which has a circumferential pilot located at the outer edge of the swirlng hot turbine exhaust gas stream. As a result thereof, the partial swirl augmentor can attain state-of-the art engine after burning thrust levels with an increased altitude blow-out limit.

5201887, Apr 13, 1993

Nov 26, 1991

7/798433

Raymond J. Bruchez - North Palm Beach FL
James Hurchalla - Stuart FL
Steven B. Johnson - Stuart FL

United Technologies Corporation - Hartford CT

F02K 310

60261

Damping of the leading edge of a cantilevered mounted liner for the augmentor of a gas turbine engine is obtained by incorporating a generally annular shaped member having a U-shaped cross section and encapsulating the leading edge of the liner in the U-shaped portion of the annular member. A split ring may be included in the U-shaped portion to augment the damping function.

5082182, Jan 21, 1992

Aug 23, 1990

7/571797

Raymond J. Bruchez - North Palm Beach FL
George E. Mount - Tequesta FL
James T. Dixon - Jupiter FL
Russell H. Hagerman - Melville NY
Wayne K. Movick - Jupiter FL
Aldo Arena - Smithtown NY
Jim D. Stewart - Sebastian FL

United Technologies Corporation - Hartford CT
Grumman Aerospace Corporation - Bethpage NY

B64C 1502

23926535

An axisymmetric thrust vectoring exhaust nozzle includes a plurality of divergent flaps (30) each supported at the upstream end by a universal joint (32) and at the downstream end by a load link (34) connected to a unison ring (36) positioned by actuators (45).

5367873, Nov 29, 1994

Jan 26, 1993

8/009357

W. Kevin Barcza - Stuart FL
Raymond J. Bruchez - North Palm Beach FL

United Technologies Corporation - West Palm Beach FL

F02K 310

60261

An improved flameholder for a thrust augmentation combustor includes a toroidal pilot gutter and inner and outer radial gutters, all having U-shaped cross-section and formed from a single piece of metal. The one-piece formation enables design improvements and variations which were not possible in the multiple piece construction of the prior art.