Corey L Anderson

US Patent:

20200063572, Feb 27, 2020

Filed:

Aug 21, 2018

Appl. No.:

16/107160

Inventors:

- Farmington CT, US
Corey D. Anderson - East Hartford CT, US

International Classification:

F01D 5/18
F01D 9/04

Abstract:

Vanes for gas turbine engines are described. The vanes include an airfoil body extending between a first platform and a second platform, the airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side and at least one skin core cavity comprising a first skin core cavity, wherein the first skin core cavity defines a throughflow passage through the vane between the first platform and the second platform, wherein the at least one skin core cavity is defined between an external hot wall of the vane and an internal cold wall of the vane.

US Patent:

20200040760, Feb 6, 2020

Filed:

Aug 6, 2018

Appl. No.:

16/055761

Inventors:

- Farmington CT, US
Corey D. Anderson - East Hartford CT, US

Assignee:

UNITED TECHNOLOGIES CORPORATION - Farmington CT

International Classification:

F01D 17/16
F01D 9/06
F01D 11/00
F01D 9/04
F02C 7/18

Abstract:

A component for a gas turbine engine is disclosed. In various embodiments, the component includes an airfoil, including therein a first cavity and a second cavity, and an outer spindle extending from the airfoil, the outer spindle including a first channel in fluid communication with the first cavity and a second channel in fluid communication with the second cavity.

US Patent:

20200041126, Feb 6, 2020

Filed:

Aug 1, 2018

Appl. No.:

16/052242

Inventors:

- Farmington CT, US
Corey D. Anderson - East Hartford CT, US

Assignee:

UNITED TECHNOLOGIES CORPORATION - Farmington CT

International Classification:

F23R 3/04
F23R 3/00
F23R 3/42

Abstract:

A heat shield panel arrangement for use in a combustor of a gas turbine engine is disclosed. In various embodiments, the heat shield panel arrangement includes a first panel having a first rail, the first rail having a first distal tip and a first angled outer wall, the first distal tip having a first distal tip length; and a second panel having a second rail, the second rail having a second distal tip and a second angled outer wall, the second distal tip having a second distal tip length. The first distal tip length is less than the second distal tip length and the first angled outer wall is substantially parallel to the second angled outer wall with a gap formed therebetween.

US Patent:

20190383146, Dec 19, 2019

Filed:

Jun 14, 2018

Appl. No.:

16/008521

Inventors:

- Farmington CT, US
Corey D. Anderson - East Hartford CT, US

International Classification:

F01D 5/18
F01D 25/12

Abstract:

A turbine vane includes a platform, an airfoil, and a cooling arrangement. The platform has a first surface and a second surface. The first surface and the second surface each axially between a first platform end and a second platform end and each circumferentially extend between a first platform side and a second platform side. The airfoil is connected to the platform and defines a passage outlet that extends through the second surface. The cooling arrangement includes a third wall that is connected to the second surface of the platform. The third wall defines a first outlet and a second outlet.

US Patent:

20190368734, Dec 5, 2019

Filed:

May 30, 2018

Appl. No.:

15/992454

Inventors:

- Farmington CT, US
Corey D. Anderson - East Hartford CT, US

International Classification:

F23R 3/00
F23R 3/06

Abstract:

A gas turbine engine component assembly including: a first component having a first surface and a second surface opposite the first surface; and a second component having a first surface, a second surface opposite the first surface of the second component, and an impingement slot extending from the second surface of the second component to the first surface of the second component, the second surface of the first component and the first surface of the second component defining a cooling channel therebetween in fluid communication with the impingement slot, wherein the impingement slot is in fluid communication with the second surface of the first component, wherein the impingement slot includes a slot tab configured to direct airflow into the cooling channel at least partially in a lateral direction parallel to the second surface of the first component such that a cross flow is generated in the cooling channel.

US Patent:

20190330999, Oct 31, 2019

Filed:

Apr 27, 2018

Appl. No.:

15/965130

Inventors:

- Farmington CT, US
Corey D. Anderson - East Hartford CT, US

Assignee:

United Technologies Corporation - Farmington CT

International Classification:

F01D 25/12
F01D 9/02

Abstract:

A variable vane system for a gas turbine engine includes an airfoil trunnion that extends through a vane platform such that the airfoil is rotatable with respect to the vane platform about an axis, the airfoil trunnion having an inlet configuration into the airfoil and a fixed airflow inlet mask to abut the airfoil trunnion, the fixed airflow inlet mask having a mask inlet configuration that modulates an airflow through the inlet configuration.

US Patent:

20190301286, Oct 3, 2019

Filed:

Mar 28, 2018

Appl. No.:

15/938062

Inventors:

- Farmington CT, US
Corey D. Anderson - East Hartford CT, US

International Classification:

F01D 5/18
F01D 5/14
F01D 9/04

Abstract:

Airfoils for gas turbine engines are provided. The airfoil include an airfoil body, the body extending between a leading edge and a trailing edge in an axial direction and between a pressure side wall and a suction side wall in a circumferential direction, the airfoil body defining an airfoil cavity therein and a baffle located within the airfoil cavity. The airfoil includes increased thickness side walls to form an airfoil cavity to account for the baffle within the cavity and to direct cooling flow through the airfoil.

US Patent:

20190234236, Aug 1, 2019

Filed:

Jan 31, 2018

Appl. No.:

15/884500

Inventors:

- Farmington CT, US
Corey D. Anderson - East Hartford CT, US

International Classification:

F01D 25/12
F01D 9/04
F02C 3/06

Abstract:

A component for a gas turbine engine according to example of the present disclosure includes a body that has an airfoil extending between a radially inner platform and a radially outer platform, and that has an internal cavity within the airfoil. A baffle is disposed within the internal cavity. The baffle defines first and second baffle cavities that are separated by a baffle dividing wall extending between the radially inner platform and the radially outer platform. An impingement plate is spaced apart from one of the radially inner and outer platforms, includes a first opening that provides fluid communication between a first chamber and the first baffle cavity, and includes a plurality of second openings that are smaller than the first opening and provide fluid communication between the first chamber and the second baffle cavity via a second chamber.