Alan J Goetschius

7093439, Aug 22, 2006

May 16, 2002

10/147571

Monica Pacheco-Tougas - Manchester CT, US
James B. Hoke - Tolland CT, US
Alan J. Goetschius - Marlborough CT, US

United Technologies Corporation - Hartford CT

F02C 1/00
F02G 3/00

60752, 60754, 60755

The present invention relates to heat shield panels or liners to be used in combustors for gas turbine engines. The heat shield panels each comprise a hot side and a cold side and at least one isolated cooling chamber on the cold side. Each cooling chamber has a plurality of cooling film holes for allowing a coolant, such as air, to flow from the cold side to the hot side. A combustor having an arrangement of heat shield panels or liners is also described.

7363763, Apr 29, 2008

Oct 23, 2003

10/691790

Monica Pacheco-Tougas - Manchester CT, US
James B. Hoke - Tolland CT, US
Alan J. Goetschius - Marlborough CT, US

United Technologies Corporation - Hartford CT

F23R 3/42

60752, 60754, 60755

A gas turbine engine combustor has forward bulkhead extending between inboard and outboard walls and cooperating therewith to define a combustor interior volume or combustion chamber. At least one of the walls has an exterior shell and an interior shell including a number of panels. Each panel has interior and exterior surfaces and a perimeter having leading and trailing edges and first and second lateral edges. A number of cooling passageways have inlets on the panel exterior surface and outlets on the panel interior surface. A rail protrudes from the exterior surface and is recessed from the leading edge along a majority of the leading edge.

8015829, Sep 13, 2011

Feb 26, 2008

12/037128

Monica Pacheco-Tougas - Manchester CT, US
James B. Hoke - Tolland CT, US
Alan J. Goetschius - Marlborough CT, US

United Technologies Corporation - Hartford CT

F23R 3/42

60804, 60754, 60755, 60805

A gas turbine engine combustor has forward bulkhead extending between inboard and outboard walls and cooperating therewith to define a combustor interior volume or combustion chamber. At least one of the walls has an exterior shell and an interior shell including a number of panels. Each panel has interior and exterior surfaces and a perimeter having leading and trailing edges and first and second lateral edges. A number of cooling passageways have inlets on the panel exterior surface and outlets on the panel interior surface. The shell has a plurality of holes for directing air to a space between the shell and heat shield and adapted for preferentially directing said air toward leading edge portions of first stage vanes of a turbine section.

60984074, Aug 8, 2000

Jun 8, 1998

9/093371

John J. Korzendorfer - West Hartford CT
Jeffrey D. Melman - Simsbury CT
Alan J. Goetschius - Marlborough CT

United Technologies Corporation - Hartford CT

F02C 722

60737

A premixing, tangential entry fuel injector (10) for a gas turbine engine features a secondary fuel-air injection insert (40) positively secured to a centerbody shell (38) by a braze joint (98). A secondary fuel supply tube (42), positively secured to both a centerbody base (36) and to the insert (40), is curved in at least two dimensions. In an exemplary embodiment, the tube is coiled into a spiral shape covering a single 360. degree. cycle. During engine operation, the centerbody expands axially in response to elevated temperatures in the engine's interior, causing the insert (40) to be displaced away from the base (36). The curvature of the tube allows the tube to flex slightly to accommodate the displacement. Ideally the curvature of the tube is such that the tube's natural frequency is well above the maximum vibratory frequency that the tube will experience during engine operation.

61347809, Oct 24, 2000

Sep 9, 1999

9/391992

Joseph D. Coughlan - South Glastonbury CT
Alan J. Goetschius - Marlborough CT

United Technologies Corporation - Hartford CT

B23P 1500

298892

A swirler 50 for a gas turbine engine combustor 10 has an outer wall 54, groupings 52 of vanes 42 attached to the outer wall, a centerbody 60 mechanically decoupled from the outer wall via the groupings of vanes so that the swirler can accommodate differential rates of thermal growth between the outer wall and the inner centerbody and vanes. Alternatively, the centerbody may be attached to one of the groupings of vanes to keep the centerbody from vibrating.

59963522, Dec 7, 1999

Dec 22, 1997

8/995508

Joseph D. Coughlan - South Glastonbury CT
Alan J. Goetschius - Marlborough CT

United Technologies Corporation - Hartford CT

F23R 314

60748

A swirler 50 for a gas turbine engine combustor 10 has an outer wall 54, groupings 52 of vanes 42 attached to the outer wall, a centerbody 60 mechanically decoupled from the outer wall via the groupings of vanes so that the swirler can accommodate differential rates of thermal growth between the outer wall and the inner centerbody and vanes. Alternatively, the centerbody may be attached to one of the groupings of vanes to keep the centerbody from vibrating.

20180283211, Oct 4, 2018

Mar 31, 2017

15/475736

- Farmington CT, US
Alan J. Goetschius - Amston CT, US
Thomas B. Avis - Manchester CT, US

F01D 25/16
F01D 25/20

A lubrication system for a gas turbine engine is provided. The lubrication system includes a supply source of a fluid lubricant, a main supply pump, and a boost pump system. The main supply pump has an MSP fluid flow inlet port and an MSP fluid flow exit port. The main supply pump is configured to receive a source fluid lubricant flow at a first pressure, and configured to produce a supply fluid flow at a second pressure. The second pressure is greater than the first pressure. The boost pump system has a boost pump having a BP fluid flow inlet port, and a BP fluid flow exit port. The boost pump system is configured so that the boost pump selectively receives at least a portion of the supply fluid flow from the main supply pump at the BP fluid flow inlet port, and the boost pump is configured to produce a boost supply fluid flow at a third pressure at the BP fluid flow exit port, wherein the third pressure is greater than the second pressure.

20180274588, Sep 27, 2018

Mar 27, 2017

15/470252

- Farmington CT, US
Gregory M. Savela - Stuart FL, US
Robert J. Morris - Portland CT, US
Christopher J. Zuck - Stevenson Ranch CA, US
Daniel L. Gysling - South Glastonbury CT, US
Alan J. Goetschius - Amston CT, US

F16C 27/04
F16C 27/02
F02C 7/06

A squeeze film damper includes a static member and a whirling member positioned adjacent to the static member. A gap is formed between the static member and the whirling member. A pressurized oil reservoir is formed in the gap between the static member and the whirling member. A first low pressure oil reservoir is formed in a first cavity in the whirling member, wherein the first low pressure oil reservoir is positioned on a first end of the pressurized oil reservoir. A second low pressure oil reservoir is formed in a second cavity in the whirling member, wherein the second low pressure oil reservoir is positioned on a second end of the pressurized oil reservoir. A first primary seal is positioned between the first end of the pressurized oil reservoir and the first low pressure oil reservoir, and a second primary seal is positioned between the second end of the pressurized oil reservoir and the second low pressure oil reservoir.