David A. Knaul - Glastonbury CT, US Fadi S. Maalouf - East Hampton CT, US Nicholas Aiello - New Haven CT, US Orenthral T. Morgan - East Hartford CT, US Raji Mali - Shelton CT, US
Assignee:
Pratt & Whitney - East Hartford CT
International Classification:
F04D 29/08
US Classification:
4151701
Abstract:
A seal for a gas turbine engine and a gas turbine engine employing such a seal are disclosed. More specifically, the engine includes a knife edge seal which is better able to withstand the extremely high temperatures and mechanical loads to which gas turbine engine components are increasingly subjected. By moving the knife edge seal to the aft hub and cantilevering its angle off of vertical, thermal and mechanical loads are balanced and thus thermal mechanical fatigue life is improved while low cycle fatigue is maintained.
Scott J. Augustine - Wethersfield CT, US David A. Knaul - Glastonbury CT, US
International Classification:
F01D 5/22 F02C 7/18
US Classification:
416192, 415115
Abstract:
A mount interface between two rotating gas turbine engine components includes a rigid ring to provide radial deflection restraint. In one example, the rigid ring is comprised of a metal matrix composite material.
Acoustic Liner With Non-Uniform Volumetric Distribution
- Farmington CT, US Anthony R. Bifulco - Ellington CT, US David A. Topol - West Hartford CT, US David A. Knaul - Glastonbury CT, US Michael Raymond LaFavor - Manchester CT, US
International Classification:
F02C 7/24 F04D 29/66
Abstract:
Disclosed is an acoustic liner for a gas turbine engine, having: a face sheet; a first plurality of resonator chamber cavities, distributed non-uniformly against the face sheet, the first plurality of resonator chamber cavities defining a first aggregated volume that is configured to target noise attenuation at a first frequency, the first plurality of resonator chamber cavities include first and second resonator chamber cavities fluidly coupled to each other, which have different configurations with respect to each other; and a second plurality of resonator chamber cavities, distributed non-uniformly against the face sheet, the second plurality of resonator chamber cavities define a second aggregated volume that differs from the first aggregated volume and is configured to target noise attenuation at a second frequency, the second plurality of resonator chamber cavities include third and fourth resonator chamber cavities fluidly coupled to each other, which have different configurations with respect to each other.
A Gas Turbine Engine Integrally Bladed Rotor With Asymmetrical Trench Fillets
- Hartford CT, US David A. KNAUL - Glastonbury CT, US Michael ESPINOZA - Middletown CT, US
International Classification:
F04D 29/32 F01D 5/02 F01D 5/34
Abstract:
An integrally bladed rotor includes a rotor that has a rim that provides an inner flow surface. Circumferentially spaced apart radially extending airfoils integrally with and from the rotor and joined by an airfoil fillet. An asymmetrical trench is provided in the rim between adjacent airfoils.
Pratt & Whitney
Structures Engineering Manager
Pratt & Whitney 2006 - Dec 2015
Structures Integration Lead
Pratt & Whitney 1999 - 2006
Structures Engineer
Boeing 1997 - 1999
Structures Engineer
Education:
Carnegie Mellon University - Tepper School of Business 2002 - 2004
Master of Business Administration, Masters, Finance
Carnegie Mellon University 1995 - 1997
Master of Science, Masters, Mechanical Engineering
Clarkson University 1991 - 1995
Bachelors, Bachelor of Science, Mechanical Engineering
Skills:
Aerospace Root Cause Analysis Structural Analysis Engineering Management Ansys Mechanical Engineering Unigraphics Stress Analysis Finite Element Analysis Fortran Matlab Composites Engineering Propulsion Systems Engineering Aerodynamics Aerospace Engineering