Method for fabricating dilution holes in ceramic matrix composite combustor panels

Patent metadata

Field	Value
Publication number	US-11149684-B2
Application number	US-201816146818-A
Country	US
Kind code	B2
Filing date	Sep 28, 2018
Priority date	Sep 28, 2018
Publication date	Oct 19, 2021
Grant date	Oct 19, 2021

Abstract

A heat shield panel for use in a combustor of a gas turbine engine is disclosed. In various embodiments, the heat shield panel includes an inner base layer, an outer base layer, and a grommet having a flange disposed between the inner base layer and the outer base layer.

First claim

What is claimed is:

1. A heat shield panel for use in a combustor of a gas turbine engine, comprising:
an inner base layer;
an outer base layer; and
a grommet having a flange disposed between the inner base layer and the outer base layer,
wherein the grommet includes an orifice that defines a centerline and a boss portion disposed about the centerline,
wherein the flange extends outward of the centerline from an outer surface of the boss portion and
wherein the flange defines an outer face radial extent, wherein a first outer face surface normal is parallel to the centerline along a first outer face portion, from the outer surface of the boss portion to a transition portion, and a second outer face surface normal is divergent from being parallel to the centerline along a second outer face portion, from the transition portion to the outer face radial extent.

2. The heat shield panel of claim 1 , wherein the boss portion is disposed radially about the centerline and wherein the flange extends radially outward of the centerline from a radially outer surface of the boss portion.

3. The heat shield panel of claim 1 , wherein the flange includes an inner face configured for contact with the inner base layer and the outer face is configured for contact with the outer base layer.

4. The heat shield panel of claim 3 , wherein the inner base layer includes an inner base layer aperture configured to receive an inner boss wall of the boss portion.

5. The heat shield panel of claim 4 , wherein the outer base layer includes an outer base layer aperture configured to receive an outer boss wall of the boss portion.

6. The heat shield panel of claim 5 , wherein the flange defines an inner face radial extent and wherein an inner face surface normal is parallel to the centerline from the radially outer surface of the boss portion to the inner face radial extent.

7. A method for fabricating a heat shield panel for use in a gas turbine engine combustor, comprising:
forming an inner base layer from an inner composite matrix;
forming an outer base layer from an outer composite matrix;
positioning a flange of a grommet between the inner base layer and the outer base layer to form a composite matrix preform, the grommet including an orifice that defines a centerline and a boss portion disposed about the centerline, the flange extending outward of the centerline from an outer surface of the boss portion, wherein the flange defines an outer face radial extent, wherein a first outer face surface normal is parallel to the centerline along a first outer face portion, from the outer surface of the boss portion to a transition portion, and a second outer face surface normal is divergent from being parallel to the centerline along a second outer face portion, from the transition portion to the outer face radial extent; and
curing the composite matrix preform to form the heat shield panel.

8. The method of claim 7 , wherein forming the inner base layer from the inner composite matrix includes forming an inner base layer aperture in the inner base layer configured to receive an inner boss wall of the grommet.

9. The method of claim 8 , wherein forming the outer base layer from the outer composite matrix includes forming an outer base layer aperture in the outer base layer configured to receive an outer boss wall of the grommet.

10. The method of claim 9 , wherein the flange includes an inner face configured for contact with the inner base layer and the outer face is configured for contact with the outer base layer.

11. The method of claim 10 , wherein the flange defines an inner face normal parallel to the centerline.

12. The method of claim 7 , further comprising positioning the inner base layer against an inner base layer mold and positioning the outer base layer against an outer base layer mold to form a mold cavity.

13. The method of claim 12 , wherein curing the composite matrix preform to form the heat shield panel comprises chemical vapor infiltration.

14. The method of claim 7 , wherein positioning the flange of the grommet between the inner base layer and the outer base layer to form the composite matrix preform further includes forming the grommet from a grommet composite matrix.

15. The method of claim 14 , wherein at least one of the inner composite matrix, the outer composite matrix and the grommet composite matrix are constructed of a ceramic composite material.

16. A gas turbine engine, comprising:
a combustor; and
a heat shield panel for use in the combustor, comprising:
an inner base layer;
an outer base layer; and

a grommet having a flange disposed between the inner base layer and the outer base layer,
wherein the grommet includes an orifice that defines a centerline and a boss portion disposed about the centerline,
wherein the flange extends outward of the centerline from an outer surface of the boss portion and
wherein the flange defines an outer face radial extent, wherein a first outer face surface normal is parallel to the centerline along a first outer face portion, from the outer surface of the boss portion to a transition portion, and a second outer face surface normal is divergent from being parallel to the centerline along a second outer face portion, from the transition portion to the outer face radial extent.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Dillard Gary J

Classifications

• F23R2900/00018

  Manufacturing combustion chamber liners or subparts · CPC title

• F23R3/06

  Arrangement of apertures along the flame tube · CPC title

• F02G3/00

  Combustion-product positive-displacement engine plants · CPC title

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F23R3/007

  constructed mainly of ceramic components · CPC title