Patents by Inventor Donald Brett DeSander
Donald Brett DeSander 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: 11828199Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall; a unitary outer wall; and a plurality of nozzle airfoils having an inner end radially opposite an outer end. The unitary outer wall defines a plurality of outer pockets each configured for receipt of the outer end of one of the nozzle airfoils, and the inner wall includes defines a plurality of inner pockets each configured for receipt of the inner end of one of the plurality of nozzle airfoils. A portion of each inner pocket is defined by a forward inner wall segment and an aft inner wall segment. In another embodiment, a flow path assembly comprises an inner wall defining a plurality of bayonet slots that each receive a bayonet included with each of a plurality of nozzle airfoils that are integral with a unitary outer wall.Type: GrantFiled: March 29, 2022Date of Patent: November 28, 2023Assignee: General Electric CompanyInventors: Jason David Shapiro, Donald Brett Desander, Edward Charles Vickers
-
Patent number: 11566529Abstract: A turbomachinery component with a surface that includes a bounded wear coat, the component includes: a body; a contact surface defined by the body; a recess extending into the body and communicating with the contact surface; and a wear coat positioned in the recess.Type: GrantFiled: August 22, 2017Date of Patent: January 31, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Shawn Patrick Duffen, Donald Brett DeSander, Victor Hugo Silva Correia
-
Publication number: 20220213798Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall; a unitary outer wall; and a plurality of nozzle airfoils having an inner end radially opposite an outer end. The unitary outer wall defines a plurality of outer pockets each configured for receipt of the outer end of one of the nozzle airfoils, and the inner wall includes defines a plurality of inner pockets each configured for receipt of the inner end of one of the plurality of nozzle airfoils. A portion of each inner pocket is defined by a forward inner wall segment and an aft inner wall segment. In another embodiment, a flow path assembly comprises an inner wall defining a plurality of bayonet slots that each receive a bayonet included with each of a plurality of nozzle airfoils that are integral with a unitary outer wall.Type: ApplicationFiled: March 29, 2022Publication date: July 7, 2022Inventors: Jason David Shapiro, Donald Brett Desander, Edward Charles Vickers
-
Patent number: 11286799Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall; a unitary outer wall; and a plurality of nozzle airfoils having an inner end radially opposite an outer end. The unitary outer wall defines a plurality of outer pockets each configured for receipt of the outer end of one of the nozzle airfoils, and the inner wall includes defines a plurality of inner pockets each configured for receipt of the inner end of one of the plurality of nozzle airfoils. A portion of each inner pocket is defined by a forward inner wall segment and an aft inner wall segment. In another embodiment, a flow path assembly comprises an inner wall defining a plurality of bayonet slots that each receive a bayonet included with each of a plurality of nozzle airfoils that are integral with a unitary outer wall.Type: GrantFiled: April 8, 2019Date of Patent: March 29, 2022Assignee: General Electric CompanyInventors: Jason David Shapiro, Donald Brett Desander, Edward Charles Vickers
-
Publication number: 20200025002Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall; a unitary outer wall; and a plurality of nozzle airfoils having an inner end radially opposite an outer end. The unitary outer wall defines a plurality of outer pockets each configured for receipt of the outer end of one of the nozzle airfoils, and the inner wall includes defines a plurality of inner pockets each configured for receipt of the inner end of one of the plurality of nozzle airfoils. A portion of each inner pocket is defined by a forward inner wall segment and an aft inner wall segment. In another embodiment, a flow path assembly comprises an inner wall defining a plurality of bayonet slots that each receive a bayonet included with each of a plurality of nozzle airfoils that are integral with a unitary outer wall.Type: ApplicationFiled: April 8, 2019Publication date: January 23, 2020Inventors: Jason David Shapiro, Donald Brett Desander, Edward Charles Vickers
-
Patent number: 10253641Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall; a unitary outer wall; and a plurality of nozzle airfoils having an inner end radially opposite an outer end. The unitary outer wall defines a plurality of outer pockets each configured for receipt of the outer end of one of the nozzle airfoils, and the inner wall includes defines a plurality of inner pockets each configured for receipt of the inner end of one of the plurality of nozzle airfoils. A portion of each inner pocket is defined by a forward inner wall segment and an aft inner wall segment. In another embodiment, a flow path assembly comprises an inner wall defining a plurality of bayonet slots that each receive a bayonet included with each of a plurality of nozzle airfoils that are integral with a unitary outer wall.Type: GrantFiled: February 23, 2017Date of Patent: April 9, 2019Assignee: General Electric CompanyInventors: Jason David Shapiro, Donald Brett Desander, Edward Charles Vickers
-
Publication number: 20190063232Abstract: A turbomachinery component with a surface that includes a bounded wear coat, the component includes: a body; a contact surface defined by the body; a recess extending into the body and communicating with the contact surface; and a wear coat positioned in the recess.Type: ApplicationFiled: August 22, 2017Publication date: February 28, 2019Inventors: Shawn Patrick Duffen, Donald Brett DeSander, Victor Hugo Silva Correia
-
Publication number: 20180238185Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall; a unitary outer wall; and a plurality of nozzle airfoils having an inner end radially opposite an outer end. The unitary outer wall defines a plurality of outer pockets each configured for receipt of the outer end of one of the nozzle airfoils, and the inner wall includes defines a plurality of inner pockets each configured for receipt of the inner end of one of the plurality of nozzle airfoils. A portion of each inner pocket is defined by a forward inner wall segment and an aft inner wall segment. In another embodiment, a flow path assembly comprises an inner wall defining a plurality of bayonet slots that each receive a bayonet included with each of a plurality of nozzle airfoils that are integral with a unitary outer wall.Type: ApplicationFiled: February 23, 2017Publication date: August 23, 2018Inventors: Jason David Shapiro, Donald Brett Desander, Edward Charles Vickers
-
Patent number: 8322986Abstract: A method of fabricating a rotor blade is provided. The method includes forming at least one passageway within the rotor blade, wherein the passageway extends substantially radially from a root of the rotor blade to a tip of the rotor blade, and coupling a shroud to the tip of the rotor blade. The shroud includes at least one substantially radially-outward extending wall that at least partially defines an outer plenum that is radially outward from at least the shroud, wherein the outer plenum is in flow communication with the passageway.Type: GrantFiled: July 29, 2008Date of Patent: December 4, 2012Assignee: General Electric CompanyInventors: Donald Brett DeSander, James Earl Kopriva, Robert Francis Manning, Robert Edward Athans, Mark Douglas Gledhill
-
Publication number: 20100200189Abstract: A method for making a turbine airfoil includes providing a mold core and an outer shell which cooperatively define a cavity in the shape of a hollow airfoil having an outer wall, a root, and a tip. A tip portion of the core extends completely through the portion of the cavity defining the tip of the airfoil. The core is restrained to prevent movement between the core and outer shell. Molten metal is introduced into the cavity and solidified to form an airfoil having at least one outer wall which defines an open tip and a hollow interior. A metallic tip cap is formed on the outer wall which substantially closes off the open tip. The tip cap may be formed by packing the airfoil with metallic powder; and laser sintering the exposed powder so as to form a tip cap which is metallurgically bonded to the outer wall.Type: ApplicationFiled: February 12, 2009Publication date: August 12, 2010Applicant: General Electric CompanyInventors: Huan Qi, Magdi Azer, Prabhjot Singh, Todd Jay Rockstroh, Sudhir K. Tewari, Joseph Giancarlo Sabato, Donald Brett Desander, Mark Douglas Gledhill
-
Publication number: 20100024216Abstract: A method of fabricating a rotor blade is provided. The method includes forming at least one passageway within the rotor blade, wherein the passageway extends substantially radially from a root of the rotor blade to a tip of the rotor blade, and coupling a shroud to the tip of the rotor blade. The shroud includes at least one substantially radially-outward extending wall that at least partially defines an outer plenum that is radially outward from at least the shroud, wherein the outer plenum is in flow communication with the passageway.Type: ApplicationFiled: July 29, 2008Publication date: February 4, 2010Inventors: Donald Brett DeSander, James Earl Kopriva, Robert Francis Manning, Robert Edward Athans, Mark Douglas Gledhill
-
Publication number: 20090165988Abstract: A method for making a turbine airfoil includes: (a) providing a mold having: (i) a core; (ii) an outer shell surrounding the core such that the core and the outer shell cooperatively define a cavity in the shape of an airfoil having at least one outer wall; and (iii) a core support extending from the core to the outer shell through a portion of the cavity that defines the at least one sidewall; (b) introducing molten metal alloy into the cavity and surrounding the core support; (c) solidifying the alloy to form an airfoil casting having at least one outer wall which has at least one core support opening passing therethrough; (d) removing the mold so as to expose the airfoil; and (e) sealing the at least one core support opening in the airfoil with a metal alloy metallurgically bonded to the at least one outer wall.Type: ApplicationFiled: December 31, 2007Publication date: July 2, 2009Applicant: GENERAL ELECTRIC COMPANYInventors: Todd Jay Rockstroh, Sudhir K. Tewari, Joseph Giancarlo Sabato, Donald Brett Desander, David Henry Abbott, Mark Douglas Gledhill