Corina P Moga from 2452 Burnham Walk, Carmel, IN 46032, age 60, Phone: (317)7324016

Gas Turbine Engine And Cooled Flowpath Component Therefor
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US Patent:

20120201653, Aug 9, 2012
Filed:

Dec 24, 2011
Appl. No.:

13/337103
Inventors:

Corina Moga - Carmel IN, US
Jerry Layne - Greenwood IN, US
Jeffrey F. Rhodes - Zionsville IN, US
International Classification:

F01D 9/02
F01D 25/12
US Classification:

415115
Abstract:

One embodiment of the present invention is a unique gas turbine engine. Another embodiment of the present invention is a unique cooled gas turbine engine flowpath component. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and cooled gas turbine engine flowpath components. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Turbine Blade Squealer Tip Including Internal Squealer Tip Cooling Channel
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US Patent:

20210254476, Aug 19, 2021
Filed:

Nov 18, 2020
Appl. No.:

16/951947
Inventors:

- Indianapolis IN, US
Corina Moga - Carmel IN, US
John Alan Weaver - Indianapolis IN, US
Michael Wood - Brownsburg IN, US
International Classification:

F01D 5/18
F01D 11/12
Abstract:

A gas turbine engine component may include an airfoil extending radially from a base to a blade tip, the airfoil including a pressure sidewall and a suction sidewall each extending between a leading edge and a trailing edge opposite the leading edge, an internal cooling circuit extending from the base to the blade tip; and a squealer tip. The squealer tip may include a first and a second squealer tip rail adjacent to the first squealer tip rail, and a squealer tip cap extending between the first and second squealer tip rails. The blade tip, the first and second squealer tip rails, and the squealer tip cap may define an internal squealer tip cooling channel. The blade tip may define a supply aperture that fluidly connect the internal cooling circuit and the internal squealer tip cooling channel.

Turbine Blade Squealer Tip Including Internal Squealer Tip Cooling Channel
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US Patent:

20190338650, Nov 7, 2019
Filed:

May 7, 2018
Appl. No.:

15/972725
Inventors:

- Indianapolis IN, US
Corina Moga - Carmel IN, US
John Alan Weaver - Indianapolis IN, US
Michael Wood - Brownsburg IN, US
International Classification:

F01D 5/18
F01D 11/12
Abstract:

A gas turbine engine component may include an airfoil extending radially from a base to a blade tip, the airfoil including a pressure sidewall and a suction sidewall each extending between a leading edge and a trailing edge opposite the leading edge, an internal cooling circuit extending from the base to the blade tip; and a squealer tip. The squealer tip may include a first and a second squealer tip rail adjacent to the first squealer tip rail, and a squealer tip cap extending between the first and second squealer tip rails. The blade tip, the first and second squealer tip rails, and the squealer tip cap may define an internal squealer tip cooling channel. The blade tip may define a supply aperture that fluidly connect the internal cooling circuit and the internal squealer tip cooling channel.

Impingement Plate With Stress Relief Feature
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US Patent:

20170292407, Oct 12, 2017
Filed:

Apr 10, 2017
Appl. No.:

15/482907
Inventors:

- INDIANAPOLIS IN, US
Corina Moga - Carmel IN, US
International Classification:

F01D 25/24
F01D 9/06
Abstract:

An impingement plate adapted for use in a gas turbine engine is disclosed. The plate includes a plurality of holes for directing cooling air. The plate includes a stress relief feature to prevent fatigue cracking at the coupling of the plate to the turbine engine and at the holes.

Corina P Moga