Ronald A Bunker

US Patent:

20190040746, Feb 7, 2019

Filed:

Aug 7, 2017

Appl. No.:

15/670291

Inventors:

- Schenectady NY, US
Ronald Scott Bunker - Placitas NM, US

International Classification:

F01D 5/18
F01D 5/30
F01D 5/28

Abstract:

A gas turbine engine turbine blade includes internal structural support radially supporting aerodynamic fairing.Strut radially extends away from root of support. Fairing includes hollow fairing airfoil surrounding strut and extending from fairing platform to blade tip shroud at tip of the fairing airfoil. A support cap attached to radially outer end of strut outwardly restrains fairing. Seal teeth may extend outwardly from the support cap. Internal cooling air flow path may extend radially through support. Fairing may be made from material lighter in weight than the support. Fairing material may be ceramic matrix composite and support material may be metallic. Blades may be mounted in rim of disk by roots disposed in slots through rim. Annular plate mounted to, upstream of, and proximate web of disk defines in part cooling airflow path to slot.

US Patent:

20180051565, Feb 22, 2018

Filed:

Aug 16, 2016

Appl. No.:

15/238150

Inventors:

- Schenectady NY, US
Ronald Scott Bunker - Placitas NM, US

International Classification:

F01D 5/18
F01D 5/28
F01D 9/04
F01D 25/12
F04D 29/54
F04D 29/58
F04D 29/32
F02K 3/06

Abstract:

An apparatus and method for cooling an engine component, such as an airfoil, including a wall to separate a hot flow from a cooling fluid flow. The component can include at least one trench disposed in a hot surface. The trench can be fed with the cooling fluid flow to cool the engine component along the hot surface with the cooling fluid flow.

US Patent:

20180051566, Feb 22, 2018

Filed:

Aug 16, 2016

Appl. No.:

15/238211

Inventors:

- Schenectady NY, US
Ronald Scott Bunker - Placitas NM, US

International Classification:

F01D 5/18
F01D 5/28
F01D 25/12
F01D 9/04
F02K 3/06

Abstract:

An apparatus and method for cooling an engine airfoil, including a wall bounding an interior extending axially between a leading edge and a trailing edge and radially between a root and a tip. A cooling circuit it located within the interior having full-length ribs, partial-length ribs, passages, or channels can define a cooling circuit for providing a flow of cooling fluid through the airfoil. The tip can include a tip cap forming a portion of the cooling circuit.

US Patent:

20180051567, Feb 22, 2018

Filed:

Aug 16, 2016

Appl. No.:

15/238058

Inventors:

- Schenectady NY, US
Ronald Scott Bunker - Placitas NM, US

International Classification:

F01D 5/18
F01D 9/04
F01D 25/12
F02C 7/18
F01D 11/08
F01D 25/14
F23R 3/00
F23R 3/06

Abstract:

An engine component, such as an airfoil, for a turbine engine having a hole, which can be a film hole, within the outer wall of the engine component where cooling air moves from an interior cavity through the hole to an outer surface of the engine component providing a cooling film on the outer surface of the engine component.

US Patent:

20180051568, Feb 22, 2018

Filed:

Aug 16, 2016

Appl. No.:

15/238113

Inventors:

- Schenectady NY, US
Ronald Scott Bunker - Placitas NM, US

International Classification:

F01D 5/18
F01D 9/06
F23R 3/00
F23R 3/06

Abstract:

An apparatus and method for cooling an engine component, including an outer wall separating a hot fluid flow from a cooling fluid flow, using the cooling fluid flow to cool the engine component. A region in the component can include a plurality of film holes with a porous material to meter the flow of cooling fluid provided from the engine component.

US Patent:

20180051569, Feb 22, 2018

Filed:

Aug 16, 2016

Appl. No.:

15/238277

Inventors:

- Schenectady NY, US
Ronald Scott Bunker - Placitas NM, US

International Classification:

F01D 5/18
F23R 3/00
F23R 3/06
F01D 9/02
F01D 25/12

Abstract:

An apparatus and method for cooling an engine component such as a turbine engine airfoil, including a wall bounding an interior extending axially between a leading edge and a trailing edge and radially between a root and a tip. A cooling circuit it located within the interior of the airfoil can include a porous section having a porosity permitting a volume of fluid, such as air, to pass through the porous section.

US Patent:

20180051571, Feb 22, 2018

Filed:

Aug 16, 2016

Appl. No.:

15/238174

Inventors:

- Schenectady NY, US
Ronald Scott Bunker - Placitas NM, US

International Classification:

F01D 5/18
F01D 5/28
F01D 9/04
F01D 25/12
F04D 29/54
F04D 29/58
F04D 29/32

Abstract:

An apparatus and method for cooling an engine airfoil, including a wall bounding an interior extending axially between a leading edge and a trailing edge and radially between a root and a tip. A cooling circuit it located within the interior having full-length ribs and partial-length ribs to define the cooling circuit, with the partial length ribs defining a turn.

US Patent:

20180051580, Feb 22, 2018

Filed:

Aug 16, 2016

Appl. No.:

15/238233

Inventors:

- Schenectady NY, US
Ronald Scott Bunker - Placitas NM, US

International Classification:

F01D 11/04
F01D 11/00
F01D 25/12

Abstract:

An apparatus relating to a rim seal for turbine engine comprising a wing and discourager extending into a cavity to form a labyrinth fluid path. The wing and discourager can each include a radial extension. Cooling air can pass through the rim seal along the labyrinth fluid path to resist the ingestion of hot gas from a mainstream flow.