IP Library › Granted Patent US 12663152
Granted Patent B2
US 12663152 · App. 17/839,188 · Granted Jun 23, 2026

Apparatus and method for mitigating particulate accumulation on a component of a gas turbine

Inventors: Dennis M. Moura (South Windsor, CT); Carey Clum (East Hartford, CT)
Assignee: RTX CORPORATION
F23R3/002F23M5/04F23M5/08F23R3/60F05D2240/35F05D2260/201F23R2900/00004F23R2900/00017F23R2900/03043F23R2900/03044F23R2900/03045
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Quick Facts
Patent No.
US 12663152
App. No.
17/839,188
Granted
Jun 23, 2026
Kind
B2
Abstract

A gas turbine engine component assembly is provided. The gas turbine engine component assembly comprising: a first component having a first surface and a second surface; a threaded stud including a first end and a second end opposite the first end, the threaded stud extending from the second surface of the first component; and a faired body operably secured to the threaded stud, wherein the faired body is shaped to redirect the airflow in a lateral direction parallel to the second surface of the first component such that a cross flow is generated.

Claims (21)

1 . A gas turbine engine component assembly, comprising:

a first component having a first surface and a second surface;

a threaded stud including a first end and a second end opposite the first end, the threaded stud extending from the second surface of the first component;

a faired body operably secured to the threaded stud, wherein the faired body is shaped to redirect an airflow in a lateral direction parallel to the second surface of the first component such that a cross flow is generated;

a second component having an inner surface, an outer surface opposite the inner surface of the second component, a cooling hole extending from the outer surface of the second component to the inner surface of the second component through the second component, and a receiving aperture extending from the outer surface to the inner surface through the second component,

wherein the inner surface of the second component and the second surface of the first component define a cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the first component,

wherein the threaded stud extends from the second surface of the first component through the cooling channel and through the receiving aperture of the second component;

an injection aperture fluidly connecting the airflow in an airflow path proximate the outer surface of the second component to the cooling channel and configured to convey the airflow into the cooling channel towards the faired body;

a nut located at the second end of the threaded stud, the nut having internal threads configured to mesh with external threads located on a cylindrical surface of the threaded stud at the second end of the threaded stud; and

a washer axially interposed between the nut and the outer surface of the second component, the washer having a solid portion that defines an opening for receiving the threaded stud therein and the washer having the injection aperture located between a peripheral portion of the nut and a peripheral portion of the washer such that the injection aperture is located past a diameter of the nut and the solid portion of the washer separates the injection aperture from the opening defined by the solid portion and the injection aperture is fluidly connected to the airflow in the airflow path through the cooling channel.

2 . The gas turbine engine component assembly of claim 1 , wherein the faired body is integrally formed from at least one of the first component and the threaded stud.

3 . The gas turbine engine component assembly of claim 2 , wherein the faired body is a fillet between the threaded stud and the first component.

4 . The gas turbine engine component assembly of claim 1 , wherein the injection aperture is fluidly connected to the cooling channel through the receiving aperture.

5 . The gas turbine engine component assembly of claim 1 , wherein the first component is a heat shield of a combustor and the second component is a liner of the combustor.

6 . The gas turbine engine component assembly of claim 1 , wherein the threaded stud has a passage way providing fluid communication between an exterior surface of the threaded stud located above the nut and the cooling channel.

7 . The gas turbine engine component assembly of claim 6 , wherein the injection aperture of the washer is one of a plurality of injection apertures located between the peripheral portion of the nut and the peripheral portion of the washer.

8 . The gas turbine engine component assembly of claim 7 , wherein the first component is a heat shield of a combustor and the second component is a liner of the combustor.

9 . The gas turbine engine component assembly of claim 1 , wherein the threaded stud has a passage way providing fluid communication between a top of the threaded stud and opposite sides of the threaded stud located in the cooling channel.

10 . The gas turbine engine component assembly of claim 9 , wherein the first component is a heat shield of a combustor and the second component is a liner of the combustor.

11 . The gas turbine engine component assembly of claim 1 , wherein the injection aperture of the washer is one of a plurality of injection apertures located between the peripheral portion of the nut and the peripheral portion of the washer.

12 . The gas turbine engine component assembly of claim 1 , wherein the injection aperture extends directly from a radially outer surface of the washer to a radially inner surface of the washer.