Patents by Inventor Cagdas Yilmaz

Cagdas Yilmaz has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Bore cavity thermal conditioning system
    Patent number: 9188009
    Abstract: A gas turbine engine includes a rotor having at least one rotor bore cavity and a heat exchanger. The heat exchanger is fluidically connected to a conditioning air source and to the rotor bore cavity for flowing air from the conditioning air source to the rotor bore cavity. The heat exchanger is also fluidically connected to a hot fluid source and a cool fluid source for selectively heating and cooling conditioning air flowing to the rotor bore cavity.
    Type: Grant
    Filed: October 30, 2012
    Date of Patent: November 17, 2015
    Assignee: United Technologies Corporation
    Inventors: Cagdas Yilmaz, Paul E. Coderre
  • Compressor disk bleed air scallops
    Patent number: 9145772
    Abstract: A rotor disk for a gas turbine engine includes a hub; a rim with a forward portion and an aft portion; and a plurality of circumferentially spaced radial scallops in the rim to form cooling slots between two disks when the rotor disk is connected to another rotor disk.
    Type: Grant
    Filed: March 21, 2012
    Date of Patent: September 29, 2015
    Assignee: United Technologies Corporation
    Inventors: Richard C. Baxley, Christopher St. Mary, Cagdas Yilmaz, Gary S. Odell
  • Turbofan flow path trenches
    Patent number: 8834129
    Abstract: An integrally bladed disk includes a rotor disk and circumferentially spaced first and second blades. The rotor disk has a rim the periphery of which forms a flow surface. The first and second blades extend integrally outward from the rim. The rim defines a trench in the flow surface between the first and second blades aft of a leading edge of the rim. The trench extends axially forward and rearward of a leading edge of the first blade.
    Type: Grant
    Filed: February 21, 2013
    Date of Patent: September 16, 2014
    Assignee: United Technologies Corporation
    Inventors: Roland R. Barnes, Cagdas Yilmaz
  • Rotatable component mount for a gas turbine engine
    Patent number: 8668463
    Abstract: Radial shifting of a rotatable component in a gas turbine engine is prevented by radially offsetting overlying mounting apertures in said component and a base or mounting flange therefor such that fasteners received within said overlying apertures are radially interference fit within the apertures thereby eliminating the necessity of machining or otherwise forming the apertures to an exact fit with the fasteners.
    Type: Grant
    Filed: July 29, 2010
    Date of Patent: March 11, 2014
    Assignee: United Technologies Corporation
    Inventor: Cagdas Yilmaz
  • COMPRESSOR DISK BLEED AIR SCALLOPS
    Publication number: 20130195660
    Abstract: A rotor disk for a gas turbine engine includes a hub; a rim with a forward portion and an aft portion; and a plurality of circumferentially spaced radial scallops in the rim to form cooling slots between two disks when the rotor disk is connected to another rotor disk.
    Type: Application
    Filed: March 21, 2012
    Publication date: August 1, 2013
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Richard C. Baxley, Christopher St. Mary, Cagdas Yilmaz, Gary S. Odell
  • Turbofan flow path trenches
    Patent number: 8403645
    Abstract: An integrally bladed disk includes a rim and blades. The blades are circumferentially spaced and extend integrally outward from the rim to define a flow path therebetween. The periphery of the rim forms a flow surface and includes a trench that is disposed adjacent the blades.
    Type: Grant
    Filed: September 16, 2009
    Date of Patent: March 26, 2013
    Assignee: United Technologies Corporation
    Inventors: Roland R. Barnes, Cagdas Yilmaz
  • ROTATABLE COMPONENT MOUNT FOR A GAS TURBINE ENGINE
    Publication number: 20120027601
    Abstract: Radial shifting of a rotatable component in a gas turbine engine is prevented by radially offsetting overlying mounting apertures in said component and a base or mounting flange therefor such that fasteners received within said overlying apertures are radially interference fit within the apertures thereby eliminating the necessity of machining or otherwise forming the apertures to an exact fit with the fasteners.
    Type: Application
    Filed: July 29, 2010
    Publication date: February 2, 2012
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: Cagdas Yilmaz
  • VORTEX REDUCING DEVICE FOR A GAS TURBINE ENGINE
    Publication number: 20120020797
    Abstract: A gas turbine engine has a vortex reducing device therein that includes a retainer and paddles. The retainer is arcuate in shape and has a plurality of circumferentially spaced slots that extend through it. The paddles are circumferentially spaced about the retainer and extend outward thereform. Each paddle is disposed between adjacent slots.
    Type: Application
    Filed: July 22, 2010
    Publication date: January 26, 2012
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: Cagdas Yilmaz
  • TURBOFAN FLOW PATH TRENCHES
    Publication number: 20110064580
    Abstract: An integrally bladed disk includes a rim and blades. The blades are circumferentially spaced and extend integrally outward from the rim to define a flow path therebetween. The periphery of the rim forms a flow surface and includes a trench that is disposed adjacent the blades.
    Type: Application
    Filed: September 16, 2009
    Publication date: March 17, 2011
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Roland R. Barnes, Cagdas Yilmaz