Jason C Smoke

US Patent:

7097411, Aug 29, 2006

Filed:

Apr 20, 2004

Appl. No.:

10/829114

Inventors:

Jason C. Smoke - Phoenix AZ, US
Cristopher Frost - Scottsdale AZ, US
Richard D. Kocher - Tempe AZ, US
Jeff D. Guymon - Gilbert AZ, US
Ly D. Nguyen - Phoenix AZ, US

Assignee:

Honeywell International, Inc. - Morristown NJ

International Classification:

F01D 1/02
F04D 29/44

US Classification:

415 1, 415204, 415206, 4152112

Abstract:

A compressor scroll housing for use in conjunction with turbo-machinery, particularly applicable in aircraft. The scroll housing can include a plurality of scroll vanes arrayed around the scroll housing. Scroll vanes, integrally formed with the scroll housing, carry stress load on the scroll housing, including the load from fluid pressure within the scroll and carcass loading from the engine. The plurality of scroll vanes adapted for guiding flow of fluid from an inlet to an outlet while supporting the scroll housing. Chord length and cross sectional area of each scroll vane can be sized to maintain an equal stress in all scroll vanes. A method of making the scroll housing for use with an impeller connected to an engine is disclosed, as well as a method of operating turbo-machinery including supporting a load on the scroll housing with scroll vanes while maintaining an equal stress on each scroll vane.

US Patent:

7540083, Jun 2, 2009

Filed:

Sep 28, 2005

Appl. No.:

11/238528

Inventors:

Mark C. Morris - Phoenix AZ, US
Jason C. Smoke - Phoenix AZ, US
William J. Weidner - Mesa AZ, US
Craig A. Wilson - Mesa AZ, US
Edward J. Mayer - Hamilton OH, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

B21K 3/04

US Classification:

2988972, 298897, 29889721, 29889722, 416 96 R, 416 97 R

Abstract:

Methods are provided for modifying an airfoil internal cooling circuit that include a flow path configured to direct air through the airfoil in a direction and the airfoil having a leading edge, a trailing edge, and a first and a second wall therebetween, each wall having an inner and an outer surface, the inner surfaces defining a cavity and having features forming at least a portion of the internal cooling circuit. The methods may include the steps of forming a pilot hole through the airfoil first and second walls at a predetermined location, forming an insert hole based on the predetermined location, the insert hole enveloping the pilot hole and configured to receive at least a portion of an insert configured to modify the internal cooling circuit flow path, placing the insert into the insert hole, and bonding the insert to the airfoil first and second walls.

US Patent:

7610946, Nov 3, 2009

Filed:

Jan 5, 2007

Appl. No.:

11/650265

Inventors:

Mark C. Morris - Phoenix AZ, US
Steve H. Halfmann - Chandler AZ, US
Jason C. Smoke - Phoenix AZ, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

B22C 9/04
B22C 9/10

US Classification:

164516, 164369

Abstract:

A core assembly including two cores is used to manufacture a blade. The first core has an outer surface shaped to complement the tip wall bottom surface. The second core has a tip surface, a side surface, and a protrusion or a depression. The tip surface is shaped to complement at least a portion of the tip wall top surface and is configured to be disposed proximate the first core. The side surface is shaped to complement at least a portion of the side wall, and the protrusion extends from the second core side surface to contact at least a portion of the ceramic mold inner surface. In embodiments employing a depression, the depression is formed in the side surface.

US Patent:

7625178, Dec 1, 2009

Filed:

Aug 30, 2006

Appl. No.:

11/513759

Inventors:

Mark C. Morris - Phoenix AZ, US
George W. Wolfmeyer - Tempe AZ, US
Luis A. Tapia - Tempe AZ, US
Vivek Agarwal - Chandler AZ, US
Kin Poon - Tempe AZ, US
Jason C. Smoke - Phoenix AZ, US
William C. Baker - Phoenix AZ, US
Henry M. Armstrong - Phoenix AZ, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

F01D 5/08

US Classification:

416 97R, 298897, 2988972, 29889721

Abstract:

An air-cooled turbine blade is provided having an airfoil shape defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root and a tip, the walls and the tip each including an interior surface that defines an interior with the root, the trailing edge including a plurality of slots formed thereon. The blade includes a suction side flow circuit formed therein comprising a forward and an aft flow circuit. The blade also includes a tip flow circuit extending along the tip interior surface to at least one of the trailing edge slots and including a first and a second opening, the first opening in flow communication with the suction side forward flow circuit outlet, and the second opening in flow communication with a cross-over hole of the suction side aft flow circuit. Methods of manufacturing the blade are also provided.

US Patent:

8047771, Nov 1, 2011

Filed:

Nov 17, 2008

Appl. No.:

12/272206

Inventors:

Bradley Reed Tucker - Chandler AZ, US
Mark C. Morris - Phoenix AZ, US
Jason Smoke - Phoenix AZ, US
Daniel Ryan - Phoenix AZ, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

F04D 29/44

US Classification:

415137, 4152094

Abstract:

Turbine nozzles and methods of manufacturing the turbine nozzles are provided. In an embodiment, by way of example only, a turbine nozzle includes a first ring, a vane, and a first joint. The first ring comprises a single unitary component and having a first opening and including a first metal alloy. The vane includes a first end disposed in the first opening and includes a second metal alloy. The first joint is formed in the first opening between the first ring and the vane and includes a first braze layer and an oxide layer. The first braze layer is disposed adjacent to the oxide layer, and the first braze layer and the oxide layer are disposed between the first ring and the vane.

US Patent:

8147197, Apr 3, 2012

Filed:

Mar 10, 2009

Appl. No.:

12/401037

Inventors:

Mark C. Morris - Phoenix AZ, US
Jason Smoke - Phoenix AZ, US
Jeff Howe - Chandler AZ, US
Bob Mitlin - Scottsdale AZ, US

Assignee:

Honeywell International, Inc. - Morristown NJ

International Classification:

F01D 5/18

US Classification:

416 97R, 416223 R, 416233, 416500

Abstract:

A turbine blade assembly is provided. The turbine blade assembly comprises a turbine blade comprising a cavity, and a blade platform supporting the turbine blade, the cavity extending into the blade platform. The blade platform comprises an upper surface adjacent the turbine blade and a lower surface comprising a first rib, the cavity extending into the first rib, the first rib coupled to the lower surface, tapering as it extends away from the turbine blade, and comprising a first port extending from the cavity to the upper surface.

US Patent:

8262342, Sep 11, 2012

Filed:

Jul 10, 2008

Appl. No.:

12/171000

Inventors:

Mark C. Morris - Phoenix AZ, US
Jeff Howe - Chandler AZ, US
Greg Heitland - Mesa AZ, US
Jason Smoke - Phoenix AZ, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

F01D 5/14

US Classification:

415115, 415191

Abstract:

A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path configured to receive mainstream hot gas flow. The assembly further includes a stator assembly including a stator vane that extends into the mainstream hot gas flow path and a turbine rotor assembly downstream of the stator assembly that includes a turbine disk and a turbine blade extending from the turbine disk into the mainstream hot gas flow path. The stator assembly and turbine assembly define a turbine disk cavity, and the turbine disk cavity includes a recirculation cavity configured to recirculate gas ingested from the mainstream hot gas flow path back into the mainstream hot gas flow path.

US Patent:

8381533, Feb 26, 2013

Filed:

Apr 30, 2009

Appl. No.:

12/433634

Inventors:

Jason Smoke - Phoenix AZ, US
Bob Mitlin - Scottsdale AZ, US
Alexander MirzaMoghadam - Phoenix AZ, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

F02C 7/18
F01D 5/00

US Classification:

60806, 415115

Abstract:

An apparatus for cooling turbine blades in a turbine engine including a direct transfer axial tangential onboard injector (TOBI) for a turbine rotor and a self-supporting seal plate disposed on a rotating disk for the turbine engine. The TOBI includes a plurality of openings emanating a flow of cooling air. The self-supporting seal plate comprises a plurality of shaped cooling holes in fluid communication with the flow of cooling air emanating from the TOBI. The rotating disk includes a plurality of turbine blade slots formed therein. The plurality of cooling holes are in fluid communication with the plurality of turbine blade slots for directing the flow of cooling air to provide cooling to the plurality of turbine blades. The plurality of openings, the plurality of cooling holes and the plurality of turbine blade slots are in axial alignment and optimized to minimize radial and hoop stresses.