3290 Patterson Ave southeast, Grand Rapids, MI 49512
Industry:
Aviation & Aerospace
Work:
Dassault Systèmes
Director of Fluid Mechanics
Ge Aviation Jun 2016 - Oct 2018
Consulting Engineer For High Fidelity Cfd, Advanced Design Tools
Ge Aviation May 2015 - Jun 2016
Principal Engineer For High Fidelity Cfd, Advanced Design Tools
Ge Aviation Nov 2012 - May 2015
Principal Engineer, Thermal System Design
Ge Aviation Feb 2012 - Nov 2012
Senior Staff Engineer, Thermal System Design
Education:
Stanford University 1997 - 2003
Doctorates, Doctor of Philosophy, Aerospace Engineering
Von Karman Institute For Fluid Dynamics 1998 - 1999
Masters, Aerospace Engineering
University of Cincinnati 1995 - 1997
Master of Science, Masters, Aerospace Engineering
Penn State University 1991 - 1995
Bachelors, Bachelor of Science, Aerospace Engineering
Skills:
Cfd Fluid Dynamics Heat Transfer Propulsion Systems Turbomachinery Aerodynamics Thermal System Design Product Development Technical Project Leadership Fluid Mechanics High Performance Computing Thermal Management Simulations R&D Fortran Turbulence Numerical Simulation Propulsion Gas Turbines Numerical Analysis Modeling Computational Fluid Dynamics Research and Development
- Johnston RI, US Gregory M. Laskowski - Waltham MA, US
International Classification:
G16H 50/50 G06F 30/25
Abstract:
Described are computer aided techniques to simulate a human respiratory event. The computer aided techniques access a model including a portion of a person's respiratory tract, which models the respiratory tract as a volumetric region, initiate a respiratory event into the volumetric regions, which respiratory event originates in the accessed model at a depth that is inside of the modeled respiratory tract, simulate movement of elements of the respiratory event within the volumetric region, with the elements representing particles of the respiratory event, at an inlet boundary condition representing an area of the model that is at the threshold depth inside the respiratory tract, and obtain from the simulation, a representation of a trajectory of particles of the respiratory event.
- Schenectady NY, US Gregory Michael LASKOWSKI - Rowley MA, US Robert PROCTOR - West Chester OH, US Curtis STOVER - Mason OH, US Robert Francis Manning - Newburyport MA, US Victor Hugo Silva CORREIA - Milton Mills NH, US Jared Peter BUHLER - Tewksbury MA, US Robert Carl MURRAY - Rotterdam NY, US Corey BOURASSA - Mechanicville NY, US Jonathan Russell RATZLAFF - Loveland OH, US
A turbine engine having an inducer assembly. The inducer assembly includes a centrifugal separator fluidly coupled to an inducer with an inducer inlet and an inducer outlet. The centrifugal separator includes a body, an angular velocity increaser to form a concentrated-particle stream and a reduced-particle stream, a flow splitter, and an exit conduit fluidly coupled to the body to receive the reduced-particle stream and define a separator outlet.
- Schenectady NY, US Gregory Michael LASKOWSKI - Rowley MA, US Robert PROCTOR - West Chester OH, US Curtis STOVER - Mason OH, US Robert Francis Manning - Newburyport MA, US Victor Hugo Silva CORREIA - Milton Mills NH, US Jared Peter BUHLER - Tewksbury MA, US Robert Carl MURRAY - Rotterdam NY, US Corey BOURASSA, Jr. - Mechanicville NY, US Byron Andrew PRITCHARD - Loveland OH, US Jonathan Russell RATZLAFF - Loveland OH, US
A turbine engine having a bypass fluid conduit coupled to the turbine section includes at least one particle separator located within the bypass fluid conduit to separate particles from a bypass fluid stream prior to the bypass stream reaching the turbine section for cooling. A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser, a particle outlet, an angular velocity decreaser downstream of the angular velocity increaser, and a bend provided between the angular velocity increaser and the angular velocity decreaser.
- Schenectady NY, US Gregory Michael Laskowski - Rowley MA, US Curtis Walton Stover - Mason OH, US William Collins Vining - Schenectady NY, US
International Classification:
F01D 25/14 F01D 25/12 F01D 25/28 F02C 7/12
Abstract:
A shroud assembly for a gas turbine engine includes a shroud, hanger, and a hanger support mounted adjacent to a plurality of blades. The hanger can have an interior chamber defining a cooling circuit with a particle separator located within the interior chamber. The particle separator can have an inlet for accepting a flow of cooling fluid, such that a the flow of cooling fluid separates into a major flow and a minor flow carrying particles or particulate matter along the minor flow into a particle collector comprising at least a portion of the particle separator. Particles become constrained to the minor flow and pass into the particle collector, while the major flow is separated into the remaining area of the interior chamber to remove the particles from the flow of cooling fluid passing into the interior chamber.