GILBERT BARDSLEY WILCOX
Pilots at Pleasant Vw Dr, Somers, CT
License number
Connecticut A2055402
Issued Date
May 2015
Expiration Date
May 2017
Category
Airmen
Type
Authorized Aircraft Instructor
Address
Address
30 Pleasant View Dr, Somers, CT 06071
Professional information
Turbomachinery Blade Or Vane With A Permanent Machining Datum
US Patent:
5971710, Oct 26, 1999
Filed:
Oct 17, 1997
Appl. No.:
8/953129
Inventors:
Bruce A. Stauffer - Scotland CT
Gilbert B. Wilcox - Somers CT
Gilbert B. Wilcox - Somers CT
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
B63H 126
US Classification:
416191
Abstract:
A turbine blade (18) for a gas turbine engine includes a machining datum (60) that extends radially from a pocket (54) in the outer shroud (36) of the blade. The datum is spaced from a sidewall (64) of the pocket so that the datum is peripherally continuous irrespective of whether the blade is in a prefinished state or in a completely finished state. Because the datum's peripheral continuity survives the original manufacturing process, the datum is available for use in post-manufacturing inspection and repair operations.
Apparatus For A Fuel System
US Patent:
4898329, Feb 6, 1990
Filed:
Nov 4, 1987
Appl. No.:
7/117117
Inventors:
Franklin J. Davis - Glastonbury CT
Gilbert B. Wilcox - Somers CT
Richard R. Wright - Willimantic CT
Gilbert B. Wilcox - Somers CT
Richard R. Wright - Willimantic CT
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
B05B 124, B05B 1704
US Classification:
239 13
Abstract:
A fuel nozzle assembly 32 which extends into a flow path 18 for working medium gases is disclosed. Various construction details which decrease the amount of heat transfer to the fuel are developed. The assembly includes an external heat shield 50 and an internal heat shield 98 which provide longitudinally overlapping insulating gaps 52, 102 between the fuel and the hot working medium gases. In particular, the insulating gap 52 extends to the inlet 94 of the fuel nozzle support.
Coolable Turbine Blade
US Patent:
3994622, Nov 30, 1976
Filed:
Nov 24, 1975
Appl. No.:
5/634701
Inventors:
Paul Edwin Schultz - East Hampton CT
Gilbert Bardsley Wilcox - Somers CT
Gilbert Bardsley Wilcox - Somers CT
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 518
US Classification:
416 97R
Abstract:
A rotor blade capable of use in the high temperature environment of the turbine section of a gas turbine engine is disclosed. Various construction details which tend to equalize the metal temperature of the blade during operation also improve the cooling effectiveness of the cooling medium utilized. The system is built around convective, impingement, and film cooling techniques which are employed singly or in combination to improve the service life of the blade.
Turbomachinery Blade Or Vane With A Survivable Machining Datum
US Patent:
6179567, Jan 30, 2001
Filed:
Aug 18, 1999
Appl. No.:
9/376225
Inventors:
Bruce A. Stauffer - Scotland CT
Gilbert B. Wilcox - Somers CT
Gilbert B. Wilcox - Somers CT
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
B63H 116
US Classification:
416191
Abstract:
A turbine blade (18) for a gas turbine engine includes a machining datum and support tool interface (52). The datum and interface feature is a frustoconical depression residing in a blade outer shroud (36) and ideally aligned with an airfoil stacking line (40). The blade has a prefinished state in which the depression has a prefinished depth and a finished state in which the depression has a finished depth. The finished depth is smaller than the prefinished depth, but is nevertheless sufficient to act as a support feature during manufacturing operations. The utility of the depression, as both a datum and as a support feature, survives the original manufacturing operations so that the depression is useful for post-manufacturing inspection and repair.
Turbine Vane Flow Area Restoration Method
US Patent:
5522134, Jun 4, 1996
Filed:
Jun 30, 1994
Appl. No.:
8/270700
Inventors:
Jon G. Rowe - Middletown CT
Norman Pietruska - Durham CT
Richard J. Pawlaczyk - Hartford CT
Gilbert B. Wilcox - Somers CT
Norman Pietruska - Durham CT
Richard J. Pawlaczyk - Hartford CT
Gilbert B. Wilcox - Somers CT
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
B23P 1500
US Classification:
298891
Abstract:
A method for refurbishing or restoring a turbine vane or other airfoil to restore a desired flow area includes the steps of: providing a plate to be used to restore the flow area on the airfoil; cutting the plate into a desired shape; machining a series of tapers into the cut plate so that the cut plate has a single region with a substantially uniform thickness; overlaying a surface of the airfoil with the pre-cut, pre-shaped plate so that the substantially uniform thickness region is positioned over that part of the airfoil where the flow area is to be restored; and attaching the pre-cut, pre-shaped plate to the airfoil. The refurbishment or restoration method further includes heat treating the pre-cut, pre-shaped plate so that the plate softens and conforms to the shape of the airfoil surface.