Patents by Inventor Aleksander Kojovic

Aleksander Kojovic 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).

  • Reverse flow ceramic matrix composite combustor
    Patent number: 9423130
    Abstract: A gas turbine engine has an annular reverse-flow combustor with a combustor inner liner enclosing a combustion chamber. The inner liner having a dome portion at an upstream end of the combustor and a downstream combustor exit defined between a small exit duct portion and a large exit duct portion. At least one of the dome portion, the small exit duct portion and the large exit duct portion is made of a separately formed hemi-toroidal shell composed of a ceramic matrix composite.
    Type: Grant
    Filed: April 28, 2014
    Date of Patent: August 23, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Lev Alexander Prociw, Aleksander Kojovic, David C. Jamon, Jun Shi, Shaoluo L. Butler
  • REVERSE FLOW CERAMIC MATRIX COMPOSITE COMBUSTOR
    Publication number: 20140311152
    Abstract: A gas turbine engine has an annular reverse-flow combustor with a combustor inner liner enclosing a combustion chamber. The inner liner having a dome portion at an upstream end of the combustor and a downstream combustor exit defined between a small exit duct portion and a large exit duct portion. At least one of the dome portion, the small exit duct portion and the large exit duct portion is made of a separately formed hemi-toroidal shell composed of a ceramic matrix composite.
    Type: Application
    Filed: April 28, 2014
    Publication date: October 23, 2014
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: Lev Alexander PROCIW, Aleksander Kojovic, David C. Jamon, Jun Shi, Shaoluo L. Butler
  • Reverse flow ceramic matrix composite combustor
    Patent number: 8745989
    Abstract: A gas turbine engine has an annular reverse-flow combustor with a combustor inner liner enclosing a combustion chamber. The inner liner having a dome portion at an upstream end of the combustor and a downstream combustor exit defined between a small exit duct portion and a large exit duct portion. At least one of the dome portion, the small exit duct portion and the large exit duct portion is made of a separately formed hemi-toroidal shell composed of a ceramic matrix composite.
    Type: Grant
    Filed: April 9, 2009
    Date of Patent: June 10, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Lev Alexander Prociw, Aleksander Kojovic, David C. Jarmon, Jun Shi, Shaoluo L. Butler
  • REVERSE FLOW CERAMIC MATRIX COMPOSITE COMBUSTOR
    Publication number: 20100257864
    Abstract: A gas turbine engine has an annular reverse-flow combustor with a combustor inner liner enclosing a combustion chamber. The inner liner having a dome portion at an upstream end of the combustor and a downstream combustor exit defined between a small exit duct portion and a large exit duct portion. At least one of the dome portion, the small exit duct portion and the large exit duct portion is made of a separately formed hemi-toroidal shell composed of a ceramic matrix composite.
    Type: Application
    Filed: April 9, 2009
    Publication date: October 14, 2010
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Lev Alexander Prociw, Aleksander Kojovic, David C. Jarmon, Jun Shi, Shaoluo L. Butler
  • Method of manufacturing a metal injection moulded combustor swirler
    Patent number: 7721436
    Abstract: A combustor swirler for a gas turbine engine and method of manufacturing by metal injection molding an inner component and an outer cylindrical component. Indentations are molded in one of the inner and outer components and sealed by the engagement of the components together to form a series of fluid flow passages. The inner and outer components are molded with interlocking features for ensuring proper alignment of the components during assembly.
    Type: Grant
    Filed: December 20, 2005
    Date of Patent: May 25, 2010
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Lev Alexander Prociw, Harris Shafique, Aleksander Kojovic
  • Multi-channel fuel manifold
    Patent number: 7716933
    Abstract: A fuel manifold for a gas turbine engine having a first peripheral surface having a first channel defined therein and a second peripheral surface having a second channel defined therein, each of the first and second channels being sealingly enclosed to define a corresponding conduit.
    Type: Grant
    Filed: October 4, 2006
    Date of Patent: May 18, 2010
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Lev Alexander Prociw, Aleksander Kojovic, Harris Shafique
  • Combustor swirler and method of manufacturing same
    Publication number: 20070137208
    Abstract: A combustor swirler for a gas turbine engine and method of manufacturing by injection moulding an inner component and an outer cylindrical component. Indentations are moulded in of the inner and outer component and sealed by the engagement of the components together to form a series of fluid flow passages.
    Type: Application
    Filed: December 20, 2005
    Publication date: June 21, 2007
    Inventors: Lev Prociw, Harris Shafique, Aleksander Kojovic