Kenneth K Landis

US Patent:

7118325, Oct 10, 2006

Filed:

Jun 14, 2004

Appl. No.:

10/867282

Inventors:

William S. Kvasnak - Simpsonville SC, US
Kenneth K. Landis - Tequesta FL, US
Hans R. Przirembel - Monterey TN, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 5/18

US Classification:

415115, 416 97 R

Abstract:

An internally-cooled turbomachine element has an airfoil extending between inboard and outboard ends. A cooling passageway is at least partially within the airfoil and has at least a first turn. Means are in the passageway for limiting a turning a loss of the first turn. The turbomachine element may result from a reengineering of an existing element configuration lacking such means.

US Patent:

8015817, Sep 13, 2011

Filed:

Jun 10, 2009

Appl. No.:

12/481713

Inventors:

Richard Charron - West Palm Beach FL, US
Gary Snyder - Jupiter FL, US
Kenneth K. Landis - Tequesta FL, US

Assignee:

Siemens Energy, Inc. - Orlando FL

International Classification:

F02C 1/00

US Classification:

60752, 60 3937

Abstract:

A transition duct for conveying hot combustion gas from a combustor to a turbine in a gas turbine engine. The transition duct includes a panel including a middle subpanel, an inner subpanel spaced from an inner side of the middle subpanel to form an inner plenum, and an outer subpanel spaced from an outer side of the middle subpanel to form an outer plenum. The outer subpanel includes a plurality of outer diffusion holes to meter cooling air into the outer plenum. The middle subpanel includes a plurality of effusion holes to allow cooling air to flow from the outer plenum to the inner plenum. The inner subpanel includes a plurality of film holes for passing a flow of cooling air from the inner plenum through the film holes into an axial gas flow path adjacent to the inner side of the inner subpanel.

US Patent:

20070160475, Jul 12, 2007

Filed:

Jan 12, 2006

Appl. No.:

11/330598

Inventors:

Friedrich Rogers - West Palm Beach FL, US
Kenneth Landis - Tequesta FL, US

International Classification:

F01D 5/18

US Classification:

41609600R

Abstract:

A turbine airfoil having enhanced cooling capabilities. The turbine vane may be configured such that when a generally elongated airfoil of the turbine vane is attached to a turbine engine, a longitudinal axis of the generally elongated airfoil may be positioned nonparallel relative to a radial axis of the turbine engine in which the turbine vane is mounted. In this position, cooling orifices may be positioned in a region that is typically a dead zone in a conventional turbine vane where no cooling occurs. In one embodiment, a plurality of cooling orifices in an inner shroud of the turbine vane may be positioned between an outer edge of the inner shroud in closest proximity to a suction side of the airfoil near a leading edge of the airfoil and an intersection between the suction side and the inner shroud.

US Patent:

20070258814, Nov 8, 2007

Filed:

May 2, 2006

Appl. No.:

11/415597

Inventors:

Joseph Metrisin - Jupiter FL, US
Friedrich Rogers - West Palm Beach FL, US
Christopher Rawlings - Hobe Sound FL, US
Kenneth Landis - Tequesta FL, US
Jae Um - Orlando FL, US

International Classification:

F01D 5/18

US Classification:

41609700R

Abstract:

A turbine airfoil including a structural support system formed from chordal ribs within an internal cooling system in the airfoil. The chordal ribs forming the structural support system may be positioned in a cooling fluid supply channel in the hollow airfoil that is positioned proximate to a trailing edge cooling channel. The trailing edge cooling channel may include a plurality of pin fins forming a pin fin bank extending between inner surfaces of the pressure side wall and suction side wall. The chordal ribs may protrude from an inner surface of the outer wall of the hollow airfoil and extend in a general chordwise direction from a mid-chord region of the hollow airfoil to the trailing edge and into the pin fin bank. The structural support system reduces stresses proximate to the pin fins in the pin fin bank closest to the mid-chord region of the airfoil.

US Patent:

20120121381, May 17, 2012

Filed:

Nov 15, 2010

Appl. No.:

12/945943

Inventors:

Richard C. Charron - West Palm Beach FL, US
Daniel J. Pierce - Port St. Lucie FL, US
Jay A. Morrison - Cocoa FL, US
Kenneth K. Landis - Tequesta FL, US
Walter Marussich - Palm Beach Gardens FL, US

International Classification:

F03B 11/00

US Classification:

415115

Abstract:

A cooling system for a transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have a multi-panel outer wall formed from an inner panel having an inner surface that defines at least a portion of a hot gas path plenum and an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between the inner and intermediate panels. The transition duct may also include an outer panel. The inner, intermediate and outer panels may include one or more metering holes for passing cooling fluids between cooling chambers for cooling the panels. The intermediate and outer panels may be secured with an attachment system coupling the panels to the inner panel such that the intermediate and outer panels may move in-plane.

US Patent:

20130108419, May 2, 2013

Filed:

Oct 26, 2011

Appl. No.:

13/281727

Inventors:

MARCO CLAUDIO PIO BRUNELLI - Orlando FL, US
Sameer A. Khan - Orlando FL, US
Kenneth K. Landis - Tequesta FL, US
Walter H. Marussich - Palm Beach Gardens FL, US
Nicholas F. Martin - York SC, US
William W. Pankey - Palm Beach Gardens FL, US

International Classification:

F01D 25/12

US Classification:

415178

Abstract:

A ring segment for a gas turbine engine includes a panel and a cooling system. The cooling system is provided within the panel and includes a cooling fluid supply trench having an open top portion and extending radially inwardly from a central recessed portion of the panel. The cooling system further includes a plurality of cooling fluid passages extending from the cooling fluid supply trench to a leading edge and/or a trailing edge of the panel. The cooling fluid passages receive cooling fluid from the cooling fluid supply trench, wherein the cooling fluid provides convective cooling to the panel as it passes through the cooling fluid passages.

US Patent:

48591475, Aug 22, 1989

Filed:

Jan 25, 1988

Appl. No.:

7/147465

Inventors:

Kenneth B. Hall - Jupiter FL
Kenneth K. Landis - Tequesta FL

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 518

US Classification:

416 97R

Abstract:

The airfoil shaped body has a separate leading edge portion (14) spaced from the main body (12). Slots (22) thereby formed discharge cooling air parallel to surface (38) of the main body. A step change across the slot between the leading edge surface (52) and the main body surface (38) facilitates smooth introduction of cooling air.

US Patent:

48275875, May 9, 1989

Filed:

Jan 25, 1988

Appl. No.:

7/147464

Inventors:

Kenneth B. Hall - Jupiter FL
Kenneth K. Landis - Tequesta FL

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B21K 304

US Classification:

291568B

Abstract:

A turbine blade is formed from an airfoil blade 10 having V-grooves 12 in the outer surface and indentations 26 in the inner surface. A slot 30 is machined at the root of the groove intersecting the slots, and providing a smooth flow path for the cooling air discharging along the blade surface.

Author:

Kenneth M. Landis

ISBN #:

0870947494

Author:

Kenneth M. Landis

ISBN #:

0870947516