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Steven H Zysman, 60Scottsdale, AZ

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Scottsdale, AZ   

65 Old Daniels Ln, Amston, CT 06231    860-2281704   

85 Old Daniels Ln, Amston, CT 06231   

91 Congress Dr, Amston, CT 06231   

Boynton Beach, FL   

Middletown, CT   

Monsey, NY   

East Hartford, CT   

Hebron, CT   

Manchester, CT   

3890 Max Pl APT 207, Boynton Beach, FL 33436    561-7428390   

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Defense & Space

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Steven Zysman Photo 3

Chief, Nacelle Aerodynamics At Pratt & Whitney

Location:
Hartford, Connecticut Area
Industry:
Defense & Space
Experience:
Pratt & Whitney (Public Company; Defense & Space industry): Chief, Nacelle Aerodynamics,  (-) 

Publications & IP owners

Us Patents

Gas Turbine Engine Jet Noise Suppressor

US Patent:
6487848, Dec 3, 2002
Filed:
Nov 6, 1998
Appl. No.:
09/187592
Inventors:
Steven H. Zysman - Hebron CT
Wesley K. Lord - South Glastonbury CT
Gregory A. Kohlenberg - Vernon CT
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F02K 138
US Classification:
60262, 23926519
Abstract:
The present invention relates to a gas turbine engine jet noise suppressor which does not appreciably adversely impact engine thrust and performance. The jet noise suppressor includes a nozzle, having an arrangement thereon of tabs disposed on the downstream end of the nozzle, the tabs having a length and the angular offset with respect to the engine flow such that mixing occurs primarily at the interface of the engine flow and the ambient air. In addition, various construction details are developed for the tabs including tabs that are trapezoidal with tapered sides such that the tabs minimize adverse impact to engine performance.

Bleed Deflector For A Gas Turbine Engine

US Patent:
6565313, May 20, 2003
Filed:
Oct 4, 2001
Appl. No.:
09/971404
Inventors:
John P. Nikkanen - West Hartford CT
Edward F. Migliaro - Bristol CT
Steven H. Zysman - Hebron CT
Thomas B. Avis - Manchester CT
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01B 2500
US Classification:
415144, 4152081, 415914
Abstract:
The present invention relates to a bleed deflector for a gas turbine engine. The bleed deflector comprises an inlet portion for receiving bleed air from the engine, a perforated top plate for discharging the bleed air into a duct, and an aerodynamically shaped strut for positioning the perforated top plate above an inner wall of the duct to allow dilution air to flow beneath the top plate.

Fluid Mixer With An Integral Fluid Capture Ducts Forming Auxiliary Secondary Chutes At The Discharge End Of Said Ducts

US Patent:
7434384, Oct 14, 2008
Filed:
Oct 25, 2004
Appl. No.:
10/973103
Inventors:
Wesley K. Lord - Glastonbury CT, US
Steven H. Zysman - Hebron CT, US
Matthew J. Howlett - North Haven CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F02K 9/08
US Classification:
60262, 181220, 23926511
Abstract:
A fluid mixer for mixing two fluid streams includes a set of main lobes defining alternating primary and secondary main chutes , one or more auxiliary lobes intermediate two of the main lobes, and an auxiliary fluid capture duct. The auxiliary lobes are defined, at least in part, by the discharge end of the duct. In operation, the duct conveys secondary fluid to secondary chutes defined by the lobes thereby improving the performance of the mixer despite the presence of an obstruction that would otherwise impede thorough mixing of two fluid streams.

Slotted Bleed Deflector For A Gas Turbine Engine

US Patent:
7455498, Nov 25, 2008
Filed:
Jun 19, 2006
Appl. No.:
11/471114
Inventors:
Steven H. Zysman - Amston CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 9/00
US Classification:
415144, 4152082, 415191, 4152112
Abstract:
The invention relates to a slotted bleed deflector for a gas turbine engine. The bleed deflector comprises an inlet portion for receiving bleed air from the engine and a body for distributing the bleed air into a fan bypass duct. The body includes a leading edge section, a trailing edge section and a flow compartment section where the flow compartment distributes the bleed air above an inner wall of the bypass duct.

Lubricant Cooling Exchanger Dual Intake Duct

US Patent:
7658060, Feb 9, 2010
Filed:
Jul 19, 2006
Appl. No.:
11/488981
Inventors:
Steven H. Zysman - Amston CT, US
Craig A. Nordeen - Manchester CT, US
John E. McCall - Andover CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F02C 7/06
F02K 3/04
US Classification:
60 3908, 602261
Abstract:
A heat exchange system for use in lubricating systems for aircraft turbofan engine equipment in which a lubricant is provided under pressure to spaces bounded at least in part by surfaces moving relative to one another, the heat exchange system for providing air and lubricant heat exchanges to cool the lubricant at selectively variable rates in the engine fan airstreams. A heat exchanger core is provided in a controlled air flow duct system opening at its plural entrances to the engine fan airstreams and having its outlet end opening about at the end of the fan duct nozzle.

Modulating Flow Through Gas Turbine Engine Cooling System

US Patent:
8490382, Jul 23, 2013
Filed:
Oct 12, 2006
Appl. No.:
12/439733
Inventors:
Steven H. Zysman - Amston CT, US
Gregory A. Kohlenberg - Meriden CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F02K 3/02
F02K 5/02
US Classification:
602263, 60204, 60248, 60262
Abstract:
A gas turbine engine system includes a fan bypass passage in a cooling passage having an inlet that receives a bleed flow from the fan bypass passage and an outlet that discharges the bleed flow into the fan bypass passage. A nozzle having a variable cross-sectional area controls an airflow within the fan bypass passage. The bleed flow outlet is placed such that moving the nozzle to change the variable cross-sectional area controls an amount of the bleed flow through the cooling passage.

Combined Gearbox Breather And Drain Mast For Jet Aircraft Engine

US Patent:
2009013, May 28, 2009
Filed:
Nov 28, 2007
Appl. No.:
11/946216
Inventors:
Steven H. Zysman - Amston CT, US
International Classification:
B64D 33/00
F02C 7/06
US Classification:
60 3908, 60801
Abstract:
A combined gearbox breather and drain mast is mounted to a nacelle. The combined gearbox breather and drain mast is made of a composite material and includes a body portion made of a single component with a first passage in fluid communication with a gearbox and a second passage in fluid communication with an engine component. The first passage is separate from the second passage.

Passive Boundary Layer Bleed System For Nacelle Inlet Airflow Control

US Patent:
2009030, Dec 10, 2009
Filed:
Apr 23, 2009
Appl. No.:
12/428582
Inventors:
Steven H. Zysman - Amston CT, US
Wesley K. Lord - South Glastonbury CT, US
Robert M. Miller - Bristol CT, US
Oliver V. Atassi - Longmeadow MA, US
International Classification:
F02C 9/18
F02C 7/00
US Classification:
60772, 60785
Abstract:
A gas turbine engine system includes a nacelle having a pressure side and a suction side. A passage extends between the pressure side and the suction side that permits airflow from the pressure side to the suction side. The passage receives turbulent airflow over the nacelle to produce a laminar airflow over the nacelle aft of the passage to thereby reduce drag on the nacelle.

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