Frank Anthony Mignano, 61Colchester, CT

7708519, May 4, 2010

Mar 26, 2007

11/691307

Frank A. Mignano - Glendale AZ, US

Honeywell International Inc. - Morristown NJ

F01D 5/14

415157, 415115, 4151701, 415202, 4152082

A vortex spoiler () for delivery of a cooling airflow () in a turbine () engine () including a plurality of inlet ports () formed circumferentially about a radial exterior sidewall (), and a plurality of outlet ports () formed circumferentially about a radial interior sidewall (). The plurality of inlet ports () are coupled to the plurality of outlet ports () via a plurality of ducts (). Each of the ducts is formed having an interior diameter at the inlet port and the outlet port formed at a preselected angle normal to the surface of the each of the radial sidewalls to form a radially curved profile such that a cooling airflow () may pass radially inwardly through each of the plurality of ducts () with minimal tangential stress and minimal static pressure loss.

8292587, Oct 23, 2012

Dec 18, 2008

12/338746

Kin Poon - Tempe AZ, US
Rajiv Rana - Phoenix AZ, US
Bob Mitlin - Scottsdale AZ, US
Ardeshir Riahi - Scottsdale AZ, US
David Chou - Phoenix AZ, US
Steve Halfmann - Chandler AZ, US
Frank Mignano - Phoenix AZ, US

Honeywell International Inc. - Morristown NJ

F01D 11/00

416193A, 415115, 415116, 416 90 R, 416 95, 416 96 R, 416 97 R, 416193 R

A turbine blade assembly includes an airfoil, a platform, and a first cover plate. A center flow path extends through the platform in communication with an internal cooling circuit of the airfoil, which extends from a first side of the platform. A second side of the platform is located opposite the platform from the first side. An edge of the platform extends between the first and second sides and, a first passage is formed between the first and second sides and includes a first inlet and a first outlet. The first passage extends from the center flow path toward the platform edge, and a first groove is formed on the second side of the platform and extends from the first outlet of the first passage toward the edge of the platform. The first cover plate is disposed over the second side of the platform covering the first groove.

2013005, Feb 28, 2013

Aug 25, 2011

13/218224

Kin Poon - Tempe AZ, US
Jeff Howe - Chandler AZ, US
Michael T. Todd Barton - Phoenix AZ, US
Frank Mignano - Phoenix AZ, US
Mahmoud Mansour - Phoenix AZ, US
Nick Nolcheff - Chandler AZ, US
Scott Taylor - Phoenix AZ, US
Steve Trzcinski - Gilbert AZ, US
Ardeshir Riahi - Scottsdale AZ, US
Jeff Guymon - Gilbert AZ, US
Alan Hemmingson - Tempe AZ, US
Alex Mirzamoghadam - Phoenix AZ, US

HONEYWELL INTERNATIONAL INC. - Morristown NJ

F04D 27/02
F01D 5/08

415 1, 415180

Gas turbine engines and methods for cooling components thereof with mid-impeller bleed (MIB) cooling air having a pressure are provided. The gas turbine engine has a compressor comprising an impeller body and an impeller shroud at least partially surrounding the impeller body. The impeller shroud has a plurality of MIB openings disposed therein. At least one edge treatment is provided thereto. The edge treatment substantially preserves pressure of the cooling air during entrance into and discharge out of the MIB opening. The plurality of MIB openings may be extended MIB openings in a thickened impeller shroud. The centerline of the MIB openings may be oriented to be substantially aligned with an averaged local absolute flow velocity vector of the cooling air at the inlet section of the MIB opening in order to extract cooling air in a direction that has a vector component in a tangential, an axial, and a radial flow direction.