Patents by Inventor Stanislav Kostka, JR.
Stanislav Kostka, JR. 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: 11320146Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall including a shell and a heat shield. The combustor wall defines first and second cavities between the shell and the heat shield. The heat shield defines a first outlet and an elongated second outlet. The first outlet is fluidly coupled with the first cavity. The second outlet is fluidly coupled with the second cavity. The combustor wall defines one of the cavities with a tapered geometry.Type: GrantFiled: December 4, 2019Date of Patent: May 3, 2022Assignee: Raytheon Technologies CorporationInventors: Frank J. Cunha, Stanislav Kostka, Jr.
-
Patent number: 11226098Abstract: An assembly for a turbine engine is provided. This turbine engine assembly includes a shell and a heat shield with a cooling cavity between the shell and the heat shield. The heat shield defines a plurality of cooling apertures and an indentation in a side of the heat shield opposite the cooling cavity. The cooling apertures are fluidly coupled with the cooling cavity. The indentation is configured such that cooling air, directed from a first of the cooling apertures, at least partially circulates against the side of the heat shield.Type: GrantFiled: March 23, 2020Date of Patent: January 18, 2022Assignee: Raytheon Technologies CorporationInventors: Frank J. Cunha, Stanislav Kostka, Jr.
-
Patent number: 11193672Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular body. The annular body extends through the combustor wall and at least partially defines a quench aperture along a centerline through the combustor wall. The shell defines a first cooling aperture radially outwards of the annular body relative to the centerline and is configured to direct air to impinge against a portion of the annular body between the heat shield and the shell.Type: GrantFiled: August 12, 2019Date of Patent: December 7, 2021Assignee: Raytheon Technologies CorporationInventors: Frank J. Cunha, Stanislav Kostka, Jr.
-
Patent number: 11112115Abstract: A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis and a liner panel with a second inner periphery along the axis. The second inner periphery is smaller than the first inner periphery. Another wall assembly for use in a combustor of a gas turbine engine includes an annular grommet mounted between the support shell and the liner panel. The annular grommet defines a contoured inner wall.Type: GrantFiled: June 30, 2014Date of Patent: September 7, 2021Assignee: Raytheon Technologies CorporationInventors: Stanislav Kostka, Jr., Randal G. McKinney, James B. Hoke, Timothy S. Snyder, Frank J. Cunha
-
Patent number: 10968829Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular body. The body extends laterally between an inner surface and an outer surface. The inner surface defines an igniter aperture in the combustor wall. The outer surface is vertically between the heat shield and the shell. The shell defines a first cooling aperture through which air is directed to impinge against the outer surface.Type: GrantFiled: December 4, 2014Date of Patent: April 6, 2021Assignee: Raytheon Technologies CorporationInventors: Frank J. Cunha, Stanislav Kostka, Jr.
-
Patent number: 10794595Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall with a shell and a heat shield. The combustor wall defines a quench aperture therethrough. The combustor wall also defines a cavity between the shell and the heat shield. The shell defines a first aperture through which air is directed into the cavity. The heat shield includes a rail that at least partially defines a second aperture configured to direct at least some of the air within the cavity out of the combustor wall and towards the quench aperture.Type: GrantFiled: February 3, 2015Date of Patent: October 6, 2020Assignee: Raytheon Technologies CorporationInventors: Randal G. McKinney, Frank J. Cunha, Stanislav Kostka, Jr.
-
Patent number: 10753608Abstract: A structure is provided for a turbine engine. The structure includes a shell with a first surface, and a heat shield with a textured second surface and a textured third surface. The texture of a portion of the second surface is different than the texture of a portion of the third surface. The first surface and the second surface define a first cooling cavity between the shell and the heat shield. The first surface and the third surface define a second cooling cavity between the shell and the heat shield.Type: GrantFiled: November 21, 2014Date of Patent: August 25, 2020Assignee: Raytheon Technologies CorporationInventors: Frank J. Cunha, Stanislav Kostka, Jr.
-
Publication number: 20200240638Abstract: An assembly for a turbine engine is provided. This turbine engine assembly includes a shell and a heat shield with a cooling cavity between the shell and the heat shield. The heat shield defines a plurality of cooling apertures and an indentation in a side of the heat shield opposite the cooling cavity. The cooling apertures are fluidly coupled with the cooling cavity. The indentation is configured such that cooling air, directed from a first of the cooling apertures, at least partially circulates against the side of the heat shield.Type: ApplicationFiled: March 23, 2020Publication date: July 30, 2020Inventors: Frank J. Cunha, Stanislav Kostka, JR.
-
Patent number: 10697636Abstract: An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell and a heat shield. The combustor wall defines a quench aperture through the shell and the heat shield. The heat shield defines an effusion outlet a distance from the quench aperture equal to between about twenty-five times and about seventy-five times a width of the effusion outlet.Type: GrantFiled: December 4, 2014Date of Patent: June 30, 2020Assignee: Raytheon Technologies CorporationInventors: Frank J. Cunha, Stanislav Kostka, Jr., Randal G. McKinney
-
Publication number: 20200109857Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall including a shell and a heat shield. The combustor wall defines first and second cavities between the shell and the heat shield. The heat shield defines a first outlet and an elongated second outlet. The first outlet is fluidly coupled with the first cavity. The second outlet is fluidly coupled with the second cavity. The combustor wall defines one of the cavities with a tapered geometry.Type: ApplicationFiled: December 4, 2019Publication date: April 9, 2020Inventors: Frank J. Cunha, Stanislav Kostka, JR.
-
Patent number: 10598379Abstract: An assembly for a turbine engine is provided. This turbine engine assembly includes a shell and a heat shield with a cooling cavity between the shell and the heat shield. The heat shield defines a plurality of cooling apertures and an indentation in a side of the heat shield opposite the cooling cavity. The cooling apertures are fluidly coupled with the cooling cavity. The indentation is configured such that cooling air, directed from a first of the cooling apertures, at least partially circulates against the side of the heat shield.Type: GrantFiled: November 25, 2014Date of Patent: March 24, 2020Assignee: United Technologies CorporationInventors: Frank J. Cunha, Stanislav Kostka, Jr.
-
Patent number: 10533745Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall including a shell and a heat shield. The combustor wall defines first and second cavities between the shell and the heat shield. The heat shield defines a first outlet and an elongated second outlet. The first outlet is fluidly coupled with the first cavity. The second outlet is fluidly coupled with the second cavity. The combustor wall defines one of the cavities with a tapered geometry.Type: GrantFiled: February 3, 2015Date of Patent: January 14, 2020Assignee: United Technologies CorporationInventors: Frank J. Cunha, Stanislav Kostka, Jr.
-
Patent number: 10502422Abstract: An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell, a heat shield and an annular body engaged with the shell and the heat shield. The annular body extends through the combustor wall. The annular body at least partially defines a quench aperture along a centerline through the combustor wall. The annular body also at least partially defines a cooling aperture in fluid communication with the quench aperture. At least a portion of the cooling aperture extends radially outward from the quench aperture relative to the centerline.Type: GrantFiled: December 4, 2014Date of Patent: December 10, 2019Assignee: United Technologies CorporationInventors: Frank J. Cunha, Stanislav Kostka, Jr.
-
Patent number: 10480787Abstract: A cooled wall for lining a combustor of a gas turbine engine includes an annular outer wall defining a radial passage extending therethrough, an inner wall spaced radially from the outer wall to define an axial channel in fluid communication with the radial passage, and a connecting wall joining the inner wall to the outer wall. A method of making the cooled wall includes providing a three-dimensional computer model of the cooled wall, depositing a uniform thickness layer of material on a substrate, using a laser or electron beam to melt or sinter the material to form a cross section, repeating the depositing and cross section steps to form the cooled wall, and heat treating the cooled wall.Type: GrantFiled: March 26, 2015Date of Patent: November 19, 2019Assignee: United Technologies CorporationInventors: Hoyt Y. Chang, Christos Adamopoulos, Stanislav Kostka, Jr.
-
Patent number: 10443848Abstract: A grommet assembly and method of design to enhance the flow coefficient, thereof, includes a shell having a first side and an opposite second side, and a chamfered grommet projecting through the shell along a centerline and including an annular first end surface spaced outward from the first side and a conical face spanning axially and radially inward from the annular first end surface and axially beyond the second side. The assembly may further include a panel spaced from the shell and defining a cooling cavity therebetween with the conical surface defining at least in-part a hole in fluid communication through the shell and panel and isolated from the cooling cavity. A plurality of cooling channels in the grommet are in fluid communication with the cooling cavity and communicate through the panel. The combination of the conical face and the cooling channels improve the discharge coefficient of the grommet while enhancing grommet cooling.Type: GrantFiled: April 2, 2015Date of Patent: October 15, 2019Assignee: United Technologies CorporationInventors: Frank J. Cunha, Stanislav Kostka, Jr., Andreas Sadil
-
Patent number: 10386068Abstract: An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell, a heat shield and an annular body. The annular body extends through the combustor wall. The annular body at least partially defines a quench aperture along a centerline through the combustor wall. The annular body defines a first cooling aperture fluidly coupled between a cooling cavity and the quench aperture. The cooling cavity is between the shell and the heat shield.Type: GrantFiled: December 3, 2014Date of Patent: August 20, 2019Assignee: United Technologies CorporationInventors: Stanislav Kostka, Jr., Frank J. Cunha
-
Patent number: 10386066Abstract: A multi-walled structure is provided for a turbine engine. This structure includes a shell with a textured first surface, and a heat shield with a second surface. The heat shield is attached to the shell. The first and the second surfaces vertically define a cooling cavity between the shell and the heat shield. The cooling cavity fluidly couples a plurality of cooling apertures defined in the shell with a plurality of cooling apertures defined in the heat shield.Type: GrantFiled: November 21, 2014Date of Patent: August 20, 2019Assignee: United Technologies CorpoationInventors: Frank J. Cunha, Stanislav Kostka, Jr.
-
Patent number: 10378768Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular body. The annular body extends through the combustor wall and at least partially defines a quench aperture along a centerline through the combustor wall. The shell defines a first cooling aperture radially outwards of the annular body relative to the centerline and is configured to direct air to impinge against a portion of the annular body between the heat shield and the shell.Type: GrantFiled: December 4, 2014Date of Patent: August 13, 2019Assignee: United Technologies CorporationInventors: Frank J. Cunha, Stanislav Kostka, Jr.
-
Patent number: 10352566Abstract: A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a hemi-spherical protuberance.Type: GrantFiled: April 14, 2014Date of Patent: July 16, 2019Assignee: United Technologies CorporationInventors: Christopher Drake, Stanislav Kostka, Jr., Frank J. Cunha
-
Patent number: 10317078Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a body, a shell and a heat shield panel. The panel is attached to the shell with a tapered cooling cavity between the shell and the panel. The panel defines a cooling aperture configured to direct air out of the cooling cavity to impinge against the body.Type: GrantFiled: November 21, 2014Date of Patent: June 11, 2019Assignee: United Technologies CorporationInventors: Frank J. Cunha, Stanislav Kostka, Jr.