Patents by Inventor Aleksandar Kojovic
Aleksandar 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).
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Publication number: 20120227415Abstract: The positioning arrangement comprises at least one pair of complimentary rounded recesses, each recess being provided on the mating face of the corresponding component. One ball is positioned between each pair of complementary recesses.Type: ApplicationFiled: April 20, 2012Publication date: September 13, 2012Inventors: LEV ALEXANDER PROCIW, Aleksandar Kojovic
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Patent number: 7805948Abstract: An assembly for sealingly mounting a device in a hole in a pressure vessel casing, the assembly transferring a load produced by pressurized fluid to the casing and retaining the stem to the casing.Type: GrantFiled: December 15, 2005Date of Patent: October 5, 2010Assignee: Pratt & Whitney Canada Corp.Inventors: Lev Alexander Prociw, Aleksandar Kojovic, Honza Stastny
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Patent number: 7712313Abstract: In the fuel nozzle, the fuel is circulated in a helical path around the interface of a stem of the fuel nozzle and a flange for increase the cooling.Type: GrantFiled: August 22, 2007Date of Patent: May 11, 2010Assignee: Pratt & Whitney Canada Corp.Inventors: Aleksandar Kojovic, Lev Alexander Prociw
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Patent number: 7533531Abstract: A gas turbine engine internal fuel manifold assembly including an annular fuel distribution member defining at least one fuel flow passage therein, and a plurality of fuel nozzles having spray tips mounted to the fuel distribution member. the spray tips are in fuel flow communication with the fuel flow passage, and each fuel nozzle has at least one core airflow passage extending through a center thereof between the spray tip and an air inlet defined in the fuel nozzle.Type: GrantFiled: April 1, 2005Date of Patent: May 19, 2009Assignee: Pratt & Whitney Canada Corp.Inventors: Lev Alexander Prociw, Aleksandar Kojovic, Harris Shafique
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Publication number: 20090050714Abstract: In the fuel nozzle, the fuel is circulated in a helical path around the interface of a stem of the fuel nozzle and a flange for increase the cooling.Type: ApplicationFiled: August 22, 2007Publication date: February 26, 2009Inventors: ALEKSANDAR KOJOVIC, Lev Alexander Prociw
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Publication number: 20080083223Abstract: 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: ApplicationFiled: October 4, 2006Publication date: April 10, 2008Inventors: Lev Alexander PROCIW, Aleksandar KOJOVIC, Harris SHAFIQUE
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Publication number: 20080006641Abstract: The positioning arrangement comprises at least one pair of complimentary rounded recesses, each recess being provided on the mating face of the corresponding component. One ball is positioned between each pair of complementary recesses.Type: ApplicationFiled: February 22, 2005Publication date: January 10, 2008Inventors: Lev Prociw, Aleksandar Kojovic
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Publication number: 20070137218Abstract: An assembly for sealingly mounting a device in a hole in a pressure vessel casing, the assembly transferring a load produced by pressurized fluid to the casing and retaining the stem to the casing.Type: ApplicationFiled: December 15, 2005Publication date: June 21, 2007Inventors: Lev Prociw, Aleksandar Kojovic, Honza Stastny
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Publication number: 20060218925Abstract: A gas turbine engine internal fuel manifold has a plurality of airblast fuel nozzles in communication with an air source such that nozzle core air does not pass through the manifold.Type: ApplicationFiled: April 1, 2005Publication date: October 5, 2006Inventors: Lev Prociw, Aleksandar Kojovic, Harris Shafique
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Patent number: 6745571Abstract: A method of combustor cycle air flow adjustment for a gas turbine engine according to the present invention solves the problem of a higher flame temperature in the combustor, thereby affecting the emission levels when a heat-recuperated air flow cycle is used to increase the compressed air temperature. In low emission combustors this impact is severe because emission levels are significantly dependent on the primary combustion zone flame temperature. The method of the present invention includes a step of changing a geometry of an air flow passage and thereby changing distribution of a total air mass flow between an air mass flow for combustion and an air mass flow for cooling in order to ensure that flame temperature in a primary combustion zone of a combustor are maintained substantially the same whether the gas turbine engine is manufactured to operate as a simple air flow cycle engine or as a heat-recuperated air flow cycle engine.Type: GrantFiled: April 24, 2003Date of Patent: June 8, 2004Assignee: Pratt & Whitney Canada Corp.Inventors: Peter John Stuttaford, Aleksandar Kojovic
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Publication number: 20030192317Abstract: A method of combustor cycle air flow adjustment for a gas turbine engine according to the present invention solves the problem of a higher flame temperature in the combustor, thereby affecting the emission levels when a heat-recuperated air flow cycle is used to increase the compressed air temperature. In low emission combustors this impact is severe because emission levels are significantly dependent on the primary combustion zone flame temperature. The method of the present invention includes a step of changing a geometry of an air flow passage and thereby changing distribution of a total air mass flow between an air mass flow for combustion and an air mass flow for cooling in order to ensure that flame temperature in a primary combustion zone of a combustor are maintained substantially the same whether the gas turbine engine is manufactured to operate as a simple air flow cycle engine or as a heat-recuperated air flow cycle engine.Type: ApplicationFiled: April 24, 2003Publication date: October 16, 2003Inventors: Peter John Stuttaford, Aleksandar Kojovic
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Patent number: 6609362Abstract: A method of combustor cycle air flow adjustment for a gas turbine engine according to the present invention solves the problem of a higher flame temperature in the combustor, thereby affecting the emission levels when a heat-recuperated air flow cycle is used to increase the compressed air temperature. In low emission combustors this impact is severe because emission levels are significantly dependent on the primary combustion zone flame temperature. The method of the present invention includes a step of changing a geometry of an air flow passage and thereby changing distribution of a total air mass flow between an air mass flow for combustion and an air mass flow for cooling in order to ensure that flame temperature in a primary combustion zone of a combustor are maintained substantially the same whether the gas turbine engine is manufactured to operate as a simple air flow cycle engine or as a heat-recuperated air flow cycle engine.Type: GrantFiled: July 13, 2001Date of Patent: August 26, 2003Assignee: Pratt & Whitney Canada Corp.Inventors: Peter John Stuttaford, Aleksandar Kojovic
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Patent number: 6543231Abstract: A cyclone combustor of the present invention uses a novel pre-mixture injection scheme to optimize performance. The cyclone combustor includes a cylindrical combustor can and three fuel/air premixing tubes entering the combustor can radially, with a tangential offset. The tangential offset is designed to provide an optimized circulation in the combustor can for improvement of liner life span, flame stability and engine turn-down. The ignition and pilot fuel systems are placed to take advantage of the premixing tube entry locations and the tangential direction of the mixture flow momentum in the combustor can. The special combination of the parallel axes of the combustor can and the mixing tubes provides a right angle between an outlet section and the major tube section of each premixing tube. The cyclone combustor of the present invention can meet the requirements for low NOx and CO emissions.Type: GrantFiled: July 13, 2001Date of Patent: April 8, 2003Assignee: Pratt & Whitney Canada CorpInventors: Peter John Stuttaford, Aleksandar Kojovic
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Patent number: 6536201Abstract: The present invention is directed to a combustor/turbine successive dual cooling arrangement in which the combustor has a one-piece hot combustor wall and front and rear cold combustor walls, and cooling air is forced under pressure through perforations in the cold combustor walls and impinges on the annular front and rear sections of the hot combustor wall for the backside cooling of the hot combustor wall. The exhaust combustor backside cooling air is directed to gain access to the hot end of the engine, that is, the turbine section, to cool the turbine components. The combustor/turbine successive dual cooling arrangement according to the present invention enables all the air typically used to cool the hot end of the engine downstream of the combustor, to be used as combustor backside cooling as well, to significantly reduce the amount of air needed for combustor and turbine cooling.Type: GrantFiled: December 11, 2000Date of Patent: March 25, 2003Assignee: Pratt & Whitney Canada Corp.Inventors: Peter Stuttaford, Bernhard Fischer, David Edwin Cowburn, Saeid Oskooei, Michael Andrew Fryer, Aleksandar Kojovic, Jeffrey Scott Acton
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Patent number: 6530222Abstract: A swirled diffusion dump combustor of the present invention includes a cylindrical combustor can and a fuel and air mixer attached to the upstream end of the combustor can. The mixer is generally formed by an annular chamber which is defined between annular outer and inner walls, having an annularly continuous truncated conical crass-section. The upstream end of the annular chamber is closed by a manifold ring which includes an annular fuel passage and two rows of swirled air passages. Thus, the compressor air approaching the mixer from above enters the swirled air passages, and the swirled air flow in the annular chamber shears fuel from the lips of the annular fuel passage to produce a fuel/air mixture. The mixture swirl is accelerated in the annular chamber and passes a downstream annular passage which serves as the region of diffusive mixing, and also as a flame flashback restrictor. The flow then dumps into the combustor can, providing the final level of mixing, where it then burns.Type: GrantFiled: July 13, 2001Date of Patent: March 11, 2003Assignee: Pratt & Whitney Canada Corp.Inventors: Peter Stuttaford, Aleksandar Kojovic
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Publication number: 20030010036Abstract: A method of combustor cycle air flow adjustment for a gas turbine engine according to the present invention solves the problem of a higher flame temperature in the combustor, thereby affecting the emission levels when a heat-recuperated air flow cycle is used to increase the compressed air temperature. In low emission combustors this impact is severe because emission levels are significantly dependent on the primary combustion zone flame temperature. The method of the present invention includes a step of changing a geometry of an air flow passage and thereby changing distribution of a total air mass flow between an air mass flow for combustion and an air mass flow for cooling in order to ensure that flame temperature in a primary combustion zone of a combustor are maintained substantially the same whether the gas turbine engine is manufactured to operate as a simple air flow cycle engine or as a heat-recuperated air flow cycle engine.Type: ApplicationFiled: July 13, 2001Publication date: January 16, 2003Inventors: Peter John Stuttaford, Aleksandar Kojovic
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Publication number: 20030010031Abstract: A cyclone combustor of the present invention uses a novel pre-mixture injection scheme to optimize performance. The cyclone combustor includes a cylindrical combustor can and three fuel/air premixing tubes entering the combustor can radially, with a tangential offset. The tangential offset is designed to provide an optimized circulation in the combustor can for improvement of liner life span, flame stability and engine turn-down. The ignition and pilot fuel systems are placed to take advantage of the premixing tube entry locations and the tangential direction of the mixture flow momentum in the combustor can. The special combination of the parallel axes of the combustor can and the mixing tubes provides a right angle between an outlet section and the major tube section of each premixing tube. The cyclone combustor of the present invention can meet the requirements for low NOx and CO emissions.Type: ApplicationFiled: July 13, 2001Publication date: January 16, 2003Inventors: Peter John Stuttaford, Aleksandar Kojovic
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Publication number: 20030010032Abstract: A swirled diffusion dump combustor of the present invention includes a cylindrical combustor can and a fuel and air mixer attached to the upstream end of the combustor can. The mixer is generally formed by an annular chamber which is defined between annular outer and inner walls, having an annularly continuous truncated conical cross-section. The upstream end of the annular chamber is closed by a manifold ring which includes an annular fuel passage and two rows of swirled air passages. Thus, the compressor air approaching the mixer from above enters the swirled air passages, and the swirled air flow in the annular chamber shears fuel from the lips of the annular fuel passage to produce a fuel/air mixture. The mixture swirl is accelerated in the annular chamber and passes a downstream annular passage which serves as the region of diffusive mixing, and also as a flame flashback restrictor. The flow then dumps into the combustor can, providing the final level of mixing, where it then burns.Type: ApplicationFiled: July 13, 2001Publication date: January 16, 2003Inventors: Peter John Stuttaford, Aleksandar Kojovic
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Publication number: 20020069644Abstract: The present invention is directed to a combustor/turbine successive dual cooling arrangement in which the combustor has a one-piece hot combustor wall and front and rear cold combustor walls, and cooling air is forced under pressure through perforations in the cold combustor walls and impinges on the annular front and rear sections of the hot combustor wall for the backside cooling of the hot combustor wall. The exhaust combustor backside cooling air is directed to gain access to the hot end of the engine, that is, the turbine section, to cool the turbine components. The combustor/turbine successive dual cooling arrangement according to the present invention enables all the air typically used to cool the hot end of the engine downstream of the combustor, to be used as combustor backside cooling as well, to significantly reduce the amount of air needed for combustor and turbine cooling.Type: ApplicationFiled: December 11, 2000Publication date: June 13, 2002Inventors: Peter Stuttaford, Bernhard Fischer, David Edwin Cowburn, Saeid Oskooei, Michael Andrew Fryer, Aleksandar Kojovic, Jeffrey Scott Acton