Patents by Inventor Daniel Edward Demers
Daniel Edward Demers 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).
-
Patent number: 10030538Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a rotor disk, by having a vane assembly with a cooling air passage and a flow control insert located within the cooling air passage defining a conduit. A turning nozzle is mounted to the vane and has a turning passage with an inlet and an outlet, the turning nozzle is fluidly coupled to the flow control insert outlet.Type: GrantFiled: November 5, 2015Date of Patent: July 24, 2018Assignee: General Electric CompanyInventors: Wilhelm Ramon Hernandez, Daniel Edward Demers, Tyler Frederick Hooper, Victor Hugo Silva Correia, Troy Todd Dennis
-
Patent number: 9726024Abstract: An airfoil cooling circuit includes an impingement cooling circuit and a serpentine cooling circuit. An airfoil for use in a gas turbine engine having a cooling circuit which includes an impingement cooling circuit and a serpentine cooling circuit.Type: GrantFiled: December 21, 2012Date of Patent: August 8, 2017Assignee: General Electric CompanyInventors: Jared Peter Buhler, Marshall Scott Allen, Daniel Edward Demers, Robert Francis Manning
-
Publication number: 20170198602Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine within a nozzle segment comprising an outer and inner band and at least one vane extending between the outer and inner band. The outer band includes a forward and aft cavity. The apparatus comprises a forward impingement baffle located within the forward cavity comprising a forward cooling chamber and an aft impingement baffle located within the aft cavity comprising an aft cooling chamber. Cooling air introduced into the forward cooling air chamber passes through impingement holes of the forward impingement baffle into a forward impingement chamber then passes through an aperture to the aft cooling air chamber, and then passes through the impingement holes of the aft impingement baffle into an aft impingement chamber.Type: ApplicationFiled: January 11, 2016Publication date: July 13, 2017Inventors: Wilhelm Ramon Hernandez, Daniel Edward Demers, Tyler Frederick Hooper, Victor Hugo Silva Correia
-
Publication number: 20170130604Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a rotor disk, by having a vane assembly with a cooling air passage and a flow control insert located within the cooling air passage defining a conduit. A turning nozzle is mounted to the vane and has a turning passage with an inlet and an outlet, the turning nozzle is fluidly coupled to the flow control insert outlet.Type: ApplicationFiled: November 5, 2015Publication date: May 11, 2017Inventors: Wilhelm Ramon Hernandez, Daniel Edward Demers, Tyler Frederick Hooper, Victor Hugo Silva Correia, Troy Todd Dennis
-
Patent number: 9506351Abstract: A durable nozzle vane includes a leading edge where hot combustion gas impinges on the vane, a pressure side extending from the leading edge to a trailing edge and a suction side extending from the leading edge to the trailing edge, a blunt region along the suction side between the leading edge and a high curvature region, the blunt region having small curvature in the length between the leading edge and the high curvature region allowing for at least two rows of cooling apertures.Type: GrantFiled: March 28, 2013Date of Patent: November 29, 2016Assignee: General Electric CompanyInventors: Joseph Steven Bubnick, Robert Joseph Bartz, Daniel Edward Demers, Robert Alan Frederick, Todd Stephen Heffron, Sean Michael Molleson
-
Publication number: 20140348636Abstract: An airfoil cooling circuit includes an impingement cooling circuit and a serpentine cooling circuit.Type: ApplicationFiled: December 21, 2012Publication date: November 27, 2014Inventors: Jared Peter Buhler, Marshall Scott Allen, Daniel Edward Demers, Robert Francis Manning
-
Publication number: 20090293495Abstract: A turbine airfoil for a gas turbine engine includes: (a) spaced-apart pressure and suction sidewalls extending between a leading edge and a trailing edge; (b) a first cavity disposed between the pressure and suction sidewalls, the first cavity being adapted to be fed cooling air from a source within the engine, and connected to at least one film cooling hole which communicates with an exterior surface of the airfoil; (c) a second cavity disposed between the pressure and suction sidewalls, the second cavity being adapted to be fed cooling air from a source within the engine, and connected to at least one film cooling hole which communicates solely with the suction sidewall of the airfoil; and (d) a metering structure adapted to substantially restrict air flow into the second cavity.Type: ApplicationFiled: May 29, 2008Publication date: December 3, 2009Applicant: General Electric CompanyInventors: Victor Hugo Silva Correia, Daniel Edward Demers, Robert Francis Manning
-
Patent number: 6991430Abstract: A turbine blade squealer tip has a continuous squealer tip wall extending radially outwardly from and continuously around a tip cap. A recessed tip wall portion of the tip wall is recessed inboard from a pressure side of an airfoil outer wall of an airfoil of the blade forming a tip shelf therebetween. A plurality of film cooling shelf holes are disposed through the tip shelf to an internal cooling circuit of the blade and are spaced away from a junction between the recessed tip wall portion and the tip shelf. The exemplary embodiment of the airfoil includes shelf hole centerlines of the holes passing through pierce points in the shelf. At least a majority of the shelf hole centerlines are angled in outboard directions away from and outboard of the squealer tip wall. A majority of centerlines are angled away from vertical lines passing through the pierce points at first component angles in a range between 2 degrees and 16 degrees.Type: GrantFiled: April 7, 2003Date of Patent: January 31, 2006Assignee: General Electric CompanyInventors: Philip Francis Stec, Daniel Edward Demers, Richard Ludwig Schmidt
-
Patent number: 6890153Abstract: A turbine airfoil includes pressure and suction sidewalls joined together at opposite leading and trailing edges, and at a forward bridge spaced behind the leading edge to define a flow channel. The bridge includes a row of impingement holes. The flow channel includes a row of fins behind the leading edge, a row of first turbulators behind the pressure sidewall, and row of second turbulators behind the suction sidewall. The fins and turbulators have different configurations for increasing internal surface area and heat transfer for back side cooling the leading edge by the cooling air.Type: GrantFiled: April 29, 2003Date of Patent: May 10, 2005Assignee: General Electric CompanyInventors: Daniel Edward Demers, Mohammad Esmaail Taslim
-
Publication number: 20040219016Abstract: A turbine airfoil includes pressure and suction sidewalls joined together at opposite leading and trailing edges, and at a forward bridge spaced behind the leading edge to define a flow channel. The bridge includes a row of impingement holes. The flow channel includes a row of fins behind the leading edge, a row of first turbulators behind the pressure sidewall, and row of second turbulators behind the suction sidewall. The fins and turbulators have different configurations for increasing internal surface area and heat transfer for back side cooling the leading edge by the cooling air.Type: ApplicationFiled: April 29, 2003Publication date: November 4, 2004Inventors: Daniel Edward Demers, Mohammad Esmaail Taslim
-
Publication number: 20040197190Abstract: A turbine blade squealer tip has a continuous squealer tip wall extending radially outwardly from and continuously around a tip cap. A recessed tip wall portion of the tip wall is recessed inboard from a pressure side of an airfoil outer wall of an airfoil of the blade forming a tip shelf therebetween. A plurality of film cooling shelf holes are disposed through the tip shelf to an internal cooling circuit of the blade and are spaced away from a junction between the recessed tip wall portion and the tip shelf. The exemplary embodiment of the airfoil includes shelf hole centerlines of the holes passing through pierce points in the shelf. At least a majority of the shelf hole centerlines are angled in outboard directions away from and outboard of the squealer tip wall. A majority of centerlines are angled away from vertical lines passing through the pierce points at first component angles in a range between 2 degrees and 16 degrees.Type: ApplicationFiled: April 7, 2003Publication date: October 7, 2004Inventors: Philip Francis Stec, Daniel Edward Demers, Richard Ludwig Schmidt
-
Patent number: 6416284Abstract: A turbine blade includes a platform and an airfoil extending radially from the platform. An internal cooling circuit is formed in the airfoil for circulating a coolant therethrough to cool the airfoil. At least one supply passage is provided to direct some of the coolant that has passed at least partially through the internal cooling circuit onto the platform for cooling the platform.Type: GrantFiled: November 3, 2000Date of Patent: July 9, 2002Assignee: General Electric CompanyInventors: Daniel Edward Demers, Robert Francis Manning, Paul Joseph Acquaviva
-
Patent number: 6402471Abstract: A turbine blade includes a platform having an internal cavity formed therein and an airfoil extending radially from the platform. An internal cooling circuit is formed in the airfoil for circulating a coolant therethrough, and at least one supply passage extends between the internal cooling circuit and the internal platform cavity for diverting coolant to the internal platform cavity. The coolant is expelled from holes located in the forward and aft edges of the platform for purging the forward and aft disk wheel spaces and impingement cooling adjacent nozzle bands.Type: GrantFiled: November 3, 2000Date of Patent: June 11, 2002Assignee: General Electric CompanyInventors: Daniel Edward Demers, Robert Francis Manning, Paul Joseph Acquaviva