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Richard J Musiol, 604920 Black Ivy Ct NE, Cedar Rapids, IA 52411

Known as:
Richard Joseph Musiol Richard E Musiol Richard B Musiol Rich Jennifer Musiol Rich J Musiol Rick E Musiol Dick E Musiol
Related to:
Jacob W Musiol 30

Richard Musiol Phones & Addresses

4920 Black Ivy Ct NE, Cedar Rapids, IA 52411    319-3934308   

Fairview, PA   

Erie, PA   

1891 Dunbar Dr, Tempe, AZ 85282    480-8397592   

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Richard J Musiol

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Work

Company: Rockwell collins Oct 2006 Position: Principal mechanical engineer

Education

Degree: Bachelors, Bachelor of Science School / High School: Rensselaer Polytechnic Institute 1982 to 1986 Specialities: Mechanical Engineering

Interests

Science and Technology • Education • Environment

Industries

Aviation & Aerospace
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Richard Musiol resumes & CV records

Resumes

Richard Musiol Photo 14

Associate Director, Mechanical Engineering

Location:
2205 Northmont Pkwy, Duluth, GA 30096
Industry:
Aviation & Aerospace
Work:
Rockwell Collins
Principal Mechanical Engineer Ge Transportation Oct 2003 - Sep 2006
Principal Systems Engineer Honeywell Jan 1987 - Oct 2003
Senior Project Engineer Collins Aerospace Jan 1987 - Oct 2003
Associate Director, Mechanical Engineering
Education:
Rensselaer Polytechnic Institute 1982 - 1986
Bachelors, Bachelor of Science, Mechanical Engineering
Interests:
Science and Technology
Education
Environment

Publications & IP owners

Us Patents

Combustor Hot Streak Alignment For Gas Turbine Engine

US Patent:
2003000, Jan 2, 2003
Filed:
Jun 15, 2001
Appl. No.:
09/882518
Inventors:
Rodolphe Dudebout - Phoenix AZ, US
Mark Morris - Phoenix AZ, US
Douglas Freiberg - Phoenix AZ, US
Craig McKeever - Gilbert AZ, US
Richard Musiol - Tempe AZ, US
Ardeshir Riahi - Phoenix AZ, US
William Howe - Chandler AZ, US
Assignee:
Honeywell International, Inc. - Morristown NJ
International Classification:
F03D001/00
US Classification:
415/001000
Abstract:
A method and apparatus to reduce the average and maximum temperatures to which the nozzles in the hot-section of gas-turbine engine are subjected is described. The method relates to the circumferential alignment of fuel nozzles and downstream turbine nozzles in a gas turbine engine. This situates the hot-streak emerging from each fuel nozzle in between the like-numbered turbine nozzle airfoils. The most severe operating condition for reducing the durability of nozzle airfoils is the one generating hot operating temperature conditions. By identifying the temperature profile passing through downstream nozzle airfoils, airfoils in static stages can be selectively spaced around the circumference of the ring attached to the casing of the gas turbine engine to avoid high temperature exposure to the airfoils. This method and apparatus mitigates the worst oxidation and thermo-mechanical fatigue damage in the airfoils by allowing the hot gas regions to pass through the path in between two adjacent airfoils.

Possible Relatives

Jennifer C Musiol  Martin M Musiol  William F Musiol  Richard O Johnson  Richard E Stamps  Richard E Stanbrough  Richard H Stanchfield  Richard W Stanczyk  Richard M Standage  Richard A Standen 

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