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Bruce Varney

Advanced Turbine Components

Bruce specializes in design of hot section components, with a particular focus on components using advanced materials and/or cooling methods.

experience

Engineering Manager - Advanced Turbine Components  
Rolls-Royce Corporation, April 2002 to Present, Indianapolis United States
(Gas Turbines)
I am responsible for the design of all advanced turbine components made from advanced materials (e.g. CMCs) or with advanced cooling schemes.

President/CEO  
Sophic Consulting, Inc., January 2001 to April 2002, Columbus United States
(Consulting)
Consulting firm for IT and Engineering needs.

Technical Specialist  
Cummins Engine Company, May 1995 to January 2001, Columbus United States
(Diesel Engine)
Fuel Systems Structural Performance and Performance engineering roles.

Engineering Co-op  
General Electric, May 1990 to December 1991, Cincinnati, Ohio United States
(Gas Turbines)
Low Observables and CFM56 Compressors

education

Purdue Univ/W.L.  
Master Of Science, Aeronautics & Astronautics, Aug, 1989 to May, 1995
Tau Beta Pi Sigma Gamma Tau

patents

Fuel injector with isolated spring chamber   (US 6029902 A)    
Inventors: Daniel K. Hickey, Daniel K. Vetters, Bruce E. Varney, Tibor Kiss.  Issued March 26, 1998  in United States

An improved unit fuel injector is provided which effectively and precisely controls the timing of fuel injection by avoiding outside influences acting on a timing plunger. The unit fuel injector includes a timing plunger positioned between upper and lower plungers, a timing chamber positioned between the timing plunger and upper plunger and a spring chamber positioned between the timing plunger and a metering chamber for containing one or more springs for biasing the plungers. A spring chamber drain valve device is provided for directing fuel in the spring chamber to a low pressure drain while isolating the spring chamber from the low pressure drain system thereby preventing pressure variations in the drain system from entering the spring chamber and acting on the timing plunger. In addition, a scavenge circuit is provided to direct a scavenging flow of fuel and combustion gas from the injector directly to the low pressure drain without communication with the spring chamber. Consequently, pressure variations in the spring chamber are minimized thereby reducing the variations in biasing force on the timing plunger 38 to permit precise control of the timing fluid metering into the timing chamber by simply varying the timing fluid pressure.

Top stop assembly for a fuel injector   (US 5934254 A)    
Inventors: Daniel K. Vetters, Bruce E. Varney, Daniel K. Hickey.  Issued March 27, 1998  in United States

A top stop assembly for a fuel injector is provided which includes a top stop housing having a threadless injector engaging portion positioned at one end of the housing for threadlessly engaging the outer diameter portion of an injector barrel to minimize inward bore distortion. The top stop is preferably formed integrally on the top stop housing body to create a predetermined axial length of the housing which defines a predetermined outer limit of a retraction stroke of an injector plunger assembly, i.e. a top stop position. The top stop position is set by selecting a top stop housing having a predetermined axial length corresponding to the desired top stop position thereby reducing costs and avoiding loosening problems associated with multi-part top stop assemblies.

Gas turbine engine combustor liner   (US 20140260282 A1)    
Inventors: Donald E. Pinnick, Kenneth W. Froemming, Bruce E. Varney.  Filed December 20, 2013  in United States

A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated alloy structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.

Gas turbine engine combustor liner  (US 20150013340 A1)    
Inventors: Donald E. Pinnick, Kenneth W. Froemming, Bruce E. Varney, James C. Loebig, Todd Taylor, Less.  Filed December 27, 2013  in United States

A gas turbine engine variable porosity combustor liner has a laminated alloy structure. The laminated alloy structure has combustion chamber facing holes on one side and cooling plenum facing holes on a radially opposite side. The combustion chamber facing holes are in fluid communication with the cooling plenum facing holes via axially and circumferentially extending flow passages sandwiched between metal alloy sheets of the laminated alloy structure. Porous zones having respective different cooling flow amounts are formed in the laminated allow structure based on at least one of an arrangement of the combustion chamber facing holes, an arrangement of the cooling plenum facing holes, and an arrangement of the flow passages.

Gas turbine engine and diffuser   (US 20120167572 A1)    
Inventors: Edward Claude Rice, Jack Dwane Petty, Bruce Edward Varney, Mindi Danette Wigal.  Issued May 31, 2007  in United States

One embodiment of the present invention is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and components thereof. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Combustor liner support and seal assembly   (US 13/042,393)    
Inventors: Bruce Edward Varney, Vickie Rae Smiley, Todd S. Taylor, Jack Dwane Petty, SR..  Issued May 31, 2007  in United States

A method is disclosed herein for reducing binding between a combustor liner of a gas turbine engine and a free-standing ring disposed about the combustor liner. The method comprises the step of disposing a rolling assembly to roll between the combustor liner and the free-standing ring during relative radial displacement.

Turbine Shroud  (20160177786)    
Inventors: Aaron D. Sippel, Bruce E. Varney, Ted J. Freeman, Jeffrey A. Walston, Jun Shi.  Filed December 17, 2015  in United States

A turbine shroud for a gas turbine engine includes an annular metallic carrier and a ceramic-containing blade track. A connection is formed between the annular metallic carrier and the ceramic-containing blade track by insert pins extending through metallic carrier into the ceramic-containing blade track.

VANE ASSEMBLY FOR A GAS TURBINE ENGINE  (20160123164)    
Inventors: Ted J. Freeman, Bruce E. Varney, David J. Thomas, Jeffrey A. Walston.  Filed September 29, 2015  in United States

A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends from the inner platform to the outer platform. A reinforcement spar made from a metallic material extends from the inner platform to the outer platform through a hollow core of the ceramic-containing airfoil.

VANE ASSEMBLY FOR A GAS TURBINE ENGINE  (20160123163)    
Inventors: Ted J. Freeman, Bruce E. Varney, David J. Thomas, Jeffrey A. Walston.  Filed September 29, 2015  in United States

A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends from the inner platform to the outer platform. A clamp mechanism couples the inner platform and the outer platform to the ceramic-containing airfoil.

Pinned injector assembly  (6027046)    
Inventors: Daniel K. Vetters, Daniel K. Hickey, Bruce E. Varney.  Issued March 27, 1998  in United States

A unit fuel injector is provided which includes a threadless injector body attaching device for attaching an upper body section of the fuel injector to a lower body section while avoiding imparting a transverse load to the upper body section thereby minimizing bore distortion, plunger wear and the likelihood of injector failure. The threadless injector body attaching device includes a groove formed in the lower end of the upper body section and one or more apertures extending through the lower body section for positioning adjacent the groove. Also, one or more pins are provided for insertion into a respective aperture and connection to the lower body section. The groove and opposing aperture or apertures are sized to create a slip fit to avoid a contact force between the pin or pins and the upper body section.

Pinned injector assembly  (6286768)    
Inventors: Daniel K. Vetters, Daniel K. Hickey, Bruce E. Varney.  Issued March 27, 1998  in United States

A unit fuel injector is provided which includes a threadless injector body attaching device for attaching an upper body section of the fuel injector to a lower body section while avoiding imparting a transverse load to the upper body section thereby minimizing bore distortion, plunger wear and the likelihood of injector failure. The threadless injector body attaching device includes a groove formed in the lower end of the upper body section and one or more apertures extending through the lower body section for positioning adjacent the groove. Also, one or more pins are provided for insertion into a respective aperture and connection to the lower body section. The groove and opposing aperture or apertures are sized to create a slip fit to avoid a contact force between the pin or pins and the upper body section.

FUEL NOZZLE WITH SWIRLER VANES  (20100162714)    
Inventors: Edward Claude Rice, Timothy Carl Roesler, Mindi Danette Wigal, Bruce Varney.  Filed   in United States

A fuel nozzle for a gas turbine engine is provided having swirlers and a mounting device configured to mount the fuel nozzle to the inside of a combustor. In one embodiment the combustor has an interior surface formed to receive the mounting device of the fuel nozzle from within the combustor. The swirlers can be integrally formed in the fuel nozzle or can be separately attached, thus allowing the fuel nozzle to be mounted within the combustor having the relative placement of the swirlers already determined prior to installation. The fuel nozzle tip can be positioned a predetermined distance from the outlet of a swirler to reduce NOx emissions.