Conical-flat heat shield for gas turbine engine combustor dome

Patent metadata

Field	Value
Publication number	US-9869473-B2
Application number	US-201514750543-A
Country	US
Kind code	B2
Filing date	Jun 25, 2015
Priority date	Jun 26, 2014
Publication date	Jan 16, 2018
Grant date	Jan 16, 2018

Abstract

A gas turbine engine combustor conical-flat heat shield includes an annular conical section extending upstream from and being integral with a flat section with a flat downstream facing surface which may be generally perpendicular to or canted with respect to a centerline. The flat section includes radially outer and inner edges at least one of which is circular and circumscribed about a centerline and circumferentially spaced apart clockwise and counter-clockwise radial edges having an origin on the centerline. A gas turbine engine combustor includes conical-flat heat shields in one or more circular rows arranged in a non-symmetrical or asymmetrical pattern. Two or more groups (A, B, C) of the conical-flat heat shields in the circular rows may be mounted on a domeplate and one or more of the conical-flat heat shields is different in one or more of the groups (A, B, C).

First claim

What is claimed is:

1. A conical-flat heat shield for a combustor of a gas turbine engine, the conical-flat heat shield comprising:
a conical section extending upstream or forward from and being integral with a flat section of the conical-flat heat shield,
the flat section including radially outer and inner edges,
at least one of the radially outer and inner edges being circular and circumscribed about a centerline of the gas turbine engine,
the flat section including circumferentially spaced apart radial edges having an origin on the centerline;
film cooling means for cooling a downstream facing conical surface of the conical-flat heat shield upstream or forward of the flat section.

2. The conical-flat heat shield as claimed in claim 1 further comprising a flat downstream facing surface of the flat section perpendicular to or canted at a face angle with respect to the centerline.

3. The conical-flat heat shield as claimed in claim 2 further comprising a cylindrical section upstream from and integral with the conical section.

4. The conical-flat heat shield as claimed in claim 2 further comprising:
a cooling air plenum disposed between a cool wall and a hot wall of the conical-flat heat shield upstream or forward of the flat section,
cooling air supply holes extending through the cool wall to the cooling air plenum, and
upstream angled film cooling holes extending from the cooling air plenum through the hot wall to a downstream facing surface of the conical-flat heat shield upstream or forward of the flat section.

5. The conical-flat heat shield as claimed in claim 1 further comprising:
a transition section disposed between and integral with the conical section and a cylindrical section,
the cylindrical section extending upstream or forward from the conical section, and
a forward end of the transition section flush with the cylindrical section and an aft end of the transition section flush with the conical section.

6. The conical-flat heat shield as claimed in claim 1 further comprising the flat section having flat corners with flat flame stabilizing corner surfaces.

7. The conical-flat heat shield as claimed in claim 6 further comprising the flat flame stabilizing corner surfaces being at least part of a flat downstream facing surface of the flat section perpendicular to or canted at a face angle with respect to a centerline.

8. The conical-flat heat shield as claimed in claim 7 further comprising a cylindrical section upstream or forward from and integral with the conical section.

9. The conical-flat heat shield as claimed in claim 8 further comprising a transition section disposed between the cylindrical section and the conical section.

10. The conical-flat heat shield as claimed in claim 9 further comprising:
a cooling air plenum disposed between a cool wall and a hot wall of the conical-flat heat shield upstream or forward of the flat section,
cooling air supply holes extending through the cool wall to the cooling air plenum, and
upstream angled film cooling holes extending from the cooling air plenum through the hot wall to a downstream facing surface of the transition section upstream or forward of the flat section.

11. A gas turbine engine combustor comprising:
a domeplate coupled to combustor outer and inner liners,
one or more concentric circular rows of conical-flat heat shields mounted on or coupled to the domeplate,
each of the conical-flat heat shields including a conical section extending upstream or forward from and integral with a flat section of the conical-flat heat shield;
the flat section including radially outer and inner edges,
at least one of the outer and inner edges being circular and circumscribed about a centerline of a gas turbine engine,
the flat section including circumferentially spaced apart radial edges having an origin on the centerline; and
film cooling means for cooling a downstream facing conical surface of the conical-flat heat shield upstream or forward of the flat section.

12. The gas turbine engine combustor as claimed in claim 11 further comprising:
a flat downstream facing surface of the flat section perpendicular to or canted at a face angle with respect to the centerline.

13. The gas turbine engine combustor as claimed in claim 12 further comprising the flat section having flat corners with flat flame stabilizing corner surfaces and the flat flame stabilizing corner surfaces being at least part of the flat downstream facing surfaces.

14. The gas turbine engine combustor as claimed in claim 13 further comprising:
two or more groups of the conical-flat heat shields in the one or more circular rows of conical-flat heat shields,
each of the conical-flat heat shields having one or more design parameters, and
at least one of the conical-flat heat shields in a first one of the two or more groups having the one or more design parameters different than the one or more design parameters of the conical-flat heat shields in a second one of the two or more groups.

15. The gas turbine engine combustor as claimed in claim 14 further comprising the one or more design parameters chosen from a group consisting of:
total area (TA) of the flat downstream facing surfaces along the flat section of each of the conical-flat heat shields,
half cone angle of the conical section,
an axial offset (AX) of the flat section of the conical-flat heat shields from the domeplate, and
clockwise and/or counter-clockwise circumferential tilt angles (CL, CCL) of the flat downstream facing surfaces of the flat sections.

16. The gas turbine engine combustor as claimed in claim 15 further comprising:
cooling air plenums disposed between a cool wall and a hot wall of the conical-flat heat shields upstream or forward of the flat sections,
cooling air supply holes extending through the cool walls to the cooling air plenums, and
upstream angled film cooling holes extending from the cooling air plenums through the hot walls to downstream facing surfaces of transition sections upstream or forward of the flat sections.

17. The gas turbine engine combustor as claimed in claim 13 further comprising:
cylindrical sections upstream from and integral with the conical sections;
the conical-flat heat shields including transition sections disposed between and integral with the conical sections and the cylindrical sections,
the cylindrical sections extending upstream or forward from the conical sections,
forward ends of the transition sections flush with the cylindrical sections, and
aft ends of the transition sections flush with the conical sections.

18. The gas turbine engine combustor as claimed in claim 17 further comprising:
cooling air plenums disposed between cool walls and hot walls of the conical-flat heat shields upstream or forward of the flat sections,
cooling air supply holes extending through the cool walls to the cooling air plenums, and
upstream angled film cooling holes extending from the cooling air plenums through the hot walls to downstream facing surfaces of the transition sections upstream or forward of the flat sections.

19. A combustor of a gas turbine engine, the combustor comprising:
two or more concentric circular rows of conical-flat outer and inner heat shields coupled to or mounted on a domeplate of the combustor,
the two or more concentric circular rows including at least one pair of radially adjacent outer and inner circular rows of the conical-flat outer and inner heat shields,
the conical-flat outer and inner heat shields including out

Assignees

• Gen Electric

Inventors

• Elkady Ahmed Mostafa
• Danis Allen Michael
• Roberson Eric Matthew
• Mueller Mark Anthony
• Moertle George
• Li Shui-Chi

Classifications

• F23R3/002

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

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title

• F23R3/005 Primary

  Combined with pressure or heat exchangers · CPC title

• F23R3/50 Primary

  Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52) · CPC title