Edward John Hovan, Age 8461 Bolton Center Rd, Manchester, CT 06040
Edward Hovan Phones & Addresses
61 Bolton Center Rd, Manchester, CT 06040 (860) 647-1961
10 Fairfield St, Manchester, CT 06040
Bolton, CT
170 Lane 7, Sturbridge, MA 01566
Glen Rock, NJ
61 Bolton Center Rd, Manchester, CT 06040
Mentions for Edward John Hovan
Publications & IP owners
Us Patents
Air Cooled Turbine Vane
US Patent:
4025226, May 24, 1977
Filed:
Oct 3, 1975
Appl. No.:
5/619558
Inventors:
Edward John Hovan - Manchester CT
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 518
US Classification:
415115
Abstract:
A stator vane capable of use in the high temperature environment of a gas turbine engine is disclosed. Various construction details implement vane cooling concepts which are designed to prolong the service life of the vane. An effective leading edge cooling system is built around the uniform flow of film cooling air over the exterior surface of the leading edge from a cavity within the airfoil section of the vane.
Exhaust Case For A Turbine Machine
US Patent:
4023350, May 17, 1977
Filed:
Nov 10, 1975
Appl. No.:
5/630565
Inventors:
Edward John Hovan - Manchester CT
Walter Ernest Bruetsch - East Hartford CT
Walter Ernest Bruetsch - East Hartford CT
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F02C 700
F01D 2530
F01D 2530
US Classification:
60 395
Abstract:
Apparatus for reducing the pressure loss imposed upon the working medium gases flowing through an exhaust case of a turbine machine is disclosed. Various construction details which reduce the cross flow of secondary air from the pressure side of one case strut to the opposing side of the adjacent strut are developed. The loss reduction system is built around vortex generators which energize the flow boundary layer at the inner wall of the flow path for the working medium gases.
Turbine Cooling For Gas Turbine Engine
US Patent:
4820116, Apr 11, 1989
Filed:
Sep 18, 1987
Appl. No.:
7/099180
Inventors:
Edward J. Hovan - Manchester CT
Guilford E. Stephens - Manchester CT
Samuel C. Peele - Glastonbury CT
Guilford E. Stephens - Manchester CT
Samuel C. Peele - Glastonbury CT
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 518
US Classification:
415115
Abstract:
A gas turbine engine cooling system has cooling air cooling in order, the first stage disk (50) and blades (22), the second stage vanes (24), and the second stage air seal (82). Air passes to the second stage vane from the rotor through a reaction nozzle (62) effecting a reaction stage adding energy to the rotor and cooling the air.
Nacelle And Mounting Arrangement For An Aircraft Engine
US Patent:
5524847, Jun 11, 1996
Filed:
Sep 7, 1993
Appl. No.:
8/117464
Inventors:
Robert F. Brodell - Marlborough CT
Edward J. Hovan - Manchester CT
Steven T. Selfors - Somerville MA
Constantino V. Loffredo - Newington CT
Paul W. Duesler - Manchester CT
Edward J. Hovan - Manchester CT
Steven T. Selfors - Somerville MA
Constantino V. Loffredo - Newington CT
Paul W. Duesler - Manchester CT
Assignee:
United Technologies Corporation - East Hartford CT
International Classification:
F02C 720
B64D 2718
B64D 2726
B64D 2718
B64D 2726
US Classification:
244 54
Abstract:
A nacelle and mounting arrangement for a high bypass ratio ducted fan aircraft engine mounted external to the aircraft main structure is disclosed. The nacelle and mounting arrangement isolate the engine from the adverse effects of certain aerodynamic forces acting on the nacelle by transferring substantially all of those forces directly from the nacelle to the aircraft and transferring substantially none of those forces to the engine. Various arrangements of the nacelle components which facilitate engine removal while avoiding the placement of nacelle component interfaces in highly stressed regions of the nacelle are also disclosed.
Method Of Operation For A Gas Turbine Engine
US Patent:
4574584, Mar 11, 1986
Filed:
May 28, 1985
Appl. No.:
6/738630
Inventors:
Edward J. Hovan - Manchester CT
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F02C 712
US Classification:
60 3902
Abstract:
A cooling system 46 for a turbofan gas turbine engine 10 is disclosed. Various construction details which increase the effectiveness of a heat exchanger 70, 76, 112 are disclosed. In one embodiment, a rotor shaft 98 is used to pressurize buffer air for a bearing compartment 40.
Bearing Compartment For A Gas Turbine Engine
US Patent:
4561246, Dec 31, 1985
Filed:
Dec 23, 1983
Appl. No.:
6/564996
Inventors:
Edward J. Hovan - Manchester CT
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F02C 706
F02C 728
F02C 728
US Classification:
602261
Abstract:
A cooling system 46 for a turbofan gas turbine engine 10 is disclosed. Various construction details which increase the effectiveness of a heat exchanger 70, 76, 112 are disclosed. In one embodiment, a rotor shaft 98 is used to pressurize buffer air for a bearing compartment 40.
Air Cooler For Providing Buffer Air To A Bearing Compartment
US Patent:
4542623, Sep 24, 1985
Filed:
Dec 23, 1983
Appl. No.:
6/564995
Inventors:
Edward J. Hovan - Manchester CT
Joseph P. Zimonis - Palm Beach Gardens FL
Joseph P. Zimonis - Palm Beach Gardens FL
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F02C 706
F02C 728
F02C 728
US Classification:
602261
Abstract:
A cooling system 46 for a turbofan gas turbine 10 is disclosed. Various construction details which increase the effectiveness of a heat exchanger 48 located in the secondary flow path 24 are developed. In one embodiment, the cooled air is used for protecting a bearing compartment.
Nozzle For A Coolable Rotor Blade
US Patent:
4453888, Jun 12, 1984
Filed:
Apr 1, 1981
Appl. No.:
6/249767
Inventors:
Edward J. Hovan - Manchester CT
Richard R. Neumayer - Manchester CT
Richard R. Neumayer - Manchester CT
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 518
F01D 2518
F01D 2518
US Classification:
416 97R
Abstract:
A coolable rotor stage assembly 14 of the turbine 10 of an axial flow gas turbine engine is disclosed. A cavity 18 for purge air is adjacent the rotor disk 22. A nozzle 34 for metering the flow of cooling air through the rotor blade, for forming a jet of high velocity air and for directing the cooling air from the root of the rotor blade inhibits recirculation, retards formation of the radial pumping boundary layer, decreases the thickness t of the radial pumping boundary layer and does work on the rotor blade.
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