FREDERICK GERALD BORNS
Pilots at Stellar Pkwy, Chandler, AZ
License number
Arizona A0183685
Issued Date
Apr 2016
Expiration Date
Apr 2018
Category
Airmen
Type
Authorized Aircraft Instructor
Address
Address
6 S Stellar Pkwy, Chandler, AZ 85226
Professional information
Gas Turbine Combustor Heat Shield Impingement Cooling Baffle
US Patent:
6792757, Sep 21, 2004
Filed:
Nov 5, 2002
Appl. No.:
10/288950
Inventors:
Frederick G. Borns - Chandler AZ
Ardeshir Riahi - Phoenix AZ
Ardeshir Riahi - Phoenix AZ
Assignee:
Honeywell International Inc. - Morristown NJ
International Classification:
F02G 100
US Classification:
60772, 60 3911, 60752
Abstract:
A heat shield for a combustor dome includes U-shaped baffles on the outer diameter area of the upstream surface of the heat shield. The baffles are clocked with respect to the impingement openings in the combustor dome. The baffles increase cooling of the heat shield by segregating the cooling air flow from the impingement openings and by reducing cross-flow at the outer diameter of the heat shield. The baffles also function as heat shield stiffeners. Slots extend radially inward from the outer rim of the heat shield. Keyholes are at the inner ends of the slots. The slots and keyholes reduce the hoop stresses of the heat shield.
Gas Turbine Engine Including Airfoils Having An Improved Airfoil Film Cooling Configuration And Method Therefor
US Patent:
7223072, May 29, 2007
Filed:
Jan 27, 2004
Appl. No.:
10/766231
Inventors:
Ardeshir Riahi - Phoenix AZ, US
Robert McDonald - Chandler AZ, US
Frederick G. Borns - Chandler AZ, US
Robert McDonald - Chandler AZ, US
Frederick G. Borns - Chandler AZ, US
Assignee:
Honeywell International, Inc. - Morristown NJ
International Classification:
F01D 5/18
US Classification:
416 61, 416 97 R, 29557, 29889721
Abstract:
An airfoil for a gas turbine engine blade includes a plurality of film cooling holes extending through its outer surface. The film cooling holes are formed by defining at least a first datum structure and a second datum structure, and then forming each film cooling hole at a location on the airfoil outer surface relative to the first and second datum structures. As a result, each film cooling hole has a centerline extending therethrough that forms a compound angle with respect to a tangent to the outer surface, and the distance between the centerlines of each film cooling hole is at least a predetermined minimum distance.
Turbine Blade Attachment Stress Reduction Rings
US Patent:
6019580, Feb 1, 2000
Filed:
Feb 23, 1998
Appl. No.:
9/028146
Inventors:
Lawrence D. Barr - Tempe AZ
Frederick G. Borns - Chandler AZ
Mark C. Johnson - Phoenix AZ
Frederick G. Borns - Chandler AZ
Mark C. Johnson - Phoenix AZ
Assignee:
AlliedSignal Inc. - Morris Township NJ
International Classification:
B63H 116
US Classification:
416219R
Abstract:
A turbine or compressor disk assembly comprises a plurality of blades attached to a central hub by means of the blade root of each blade engaging a corresponding slot in the hub. According to the principles of the present invention, a turbine or compressor disk assembly includes one or more locally bulging regions extending axially away from the surface of the disk in the vicinity of the bottom contact plane of the disk attachment firtree. The locally bulging regions reduce the peak Macke stress in the disk bottom fillet and blade attachment root. In an illustrative embodiment, two locally bulging regions are incorporated into the disk and the corresponding blades, one of which extends forward from the leading edge of the disk and the other of which extends rearward from the trailing edge of the disk. The rearward locally bulging region has an exaggerated extension which allows the stress reduction ring to form an aft flow discourager as well as functioning to reduce peak stress.
Dual Alloy Turbine Blade
US Patent:
5106266, Apr 21, 1992
Filed:
Aug 30, 1990
Appl. No.:
7/577849
Inventors:
Frederick G. Borns - Chandler AZ
Barry S. Bixler - Tempe AZ
Barry S. Bixler - Tempe AZ
Assignee:
Allied-Signal Inc. - Morris Township, Morris County NJ
International Classification:
F01D 528
US Classification:
416241R
Abstract:
A single crystal turbine blade has a portion of its attachment section reinforced by a core containing a fine grained, polycrystalline alloy. The blade is prepared by casting a single crystal body with a cavity within the attachment section, and then filling the attachment section with the polycrystalline superalloy to form a composite structure. Filling is preferably accomplished by plasma spraying the cavity with the superalloy, and hot isostatically compacting the sprayed superalloy to minimize porosity. The composite structure is then heat treated to develop an optimized microstructure in the dual alloy attachment section. The resulting turbine blade has improved low cycle fatigue life of the composite attachment section.
Turbine Rotor Cooling Flow System
US Patent:
8277169, Oct 2, 2012
Filed:
Jun 16, 2005
Appl. No.:
11/155399
Inventors:
Ardeshir Riahi - Scottsdale AZ, US
Frederick G. Borns - Chandler AZ, US
Vivek Agarwal - Chandler AZ, US
Frederick G. Borns - Chandler AZ, US
Vivek Agarwal - Chandler AZ, US
Assignee:
Honeywell International Inc. - Morristown NJ
International Classification:
F01D 5/08
US Classification:
415115, 415151, 415176, 416 96 R, 416 97 R
Abstract:
Disclosed herein is an apparatus comprising a disk coverplate for a turbine rotor, the disk coverplate comprising a plurality of cooling holes, wherein the distance between the centers of any two adjacent cooling holes is greater than twice the average diameter of the two adjacent cooling holes. A method to control turbine cooling air flow is also disclosed.