Sealed conical-flat dome for flight engine combustors

Patent metadata

Field	Value
Publication number	US-2017009986-A1
Application number	US-201514794016-A
Country	US
Kind code	A1
Filing date	Jul 8, 2015
Priority date	Jul 8, 2015
Publication date	Jan 12, 2017
Grant date	—

Abstract

A combustor assembly for a gas turbine engine defining an axial direction is provided. The combustor assembly generally includes a liner, an annular dome, and a deflector plate. The liner at least partially defines a combustion chamber. The annular dome defines a first cavity and has a plurality of impingement holes, and the deflector plate defines a conical surface and a flat surface, wherein a plurality of cooling holes are defined through the deflector plate. The annular dome and the deflector plate are positioned together to define a second cavity that is in fluid communication with the first cavity through the plurality of impingement holes. In addition, the second cavity is in fluid communication with the combustion chamber through the plurality of cooling holes.

First claim

What is claimed is:

1 . A combustor assembly for a gas turbine engine defining an axial direction, the combustor assembly comprising:
a liner at least partially defining a combustion chamber; an annular dome defining a first cavity and having a plurality of impingement holes; and a deflector plate defining a conical surface and a flat surface, wherein a plurality of cooling holes are defined through the deflector plate, wherein the annular dome and the deflector plate are positioned together to define a second cavity, the second cavity being in fluid communication with the first cavity through the plurality of impingement holes, and the second cavity being in fluid communication with the combustion chamber through the plurality of cooling holes.

2 . The combustor assembly of claim 1 , wherein a radially outer portion of the second cavity is sealed by a spline seal between the annular dome and the deflector plate.

3 . The combustor assembly of claim 2 , wherein the deflector plate further defines a recessed slot that extends around an end of the spline seal, thereby providing fluid communication between the second cavity and the combustion chamber.

4 . The combustor assembly of claim 1 , wherein a radially inner portion of the second cavity is sealed by a brazed joint between the annular dome and the deflector plate.

5 . The combustor assembly of claim 1 , such that a first portion of the conical surface has a first angle, and a second portion of the conical surface has a second angle different from the first angle.

6 . The combustor assembly of claim 5 , wherein the first angle and the second angle are in a range of about 15° to 75°.

7 . The combustor assembly of claim 1 , wherein an angle of the conical surface is in a range of about 15° to 75°.

8 . The combustor assembly of claim 1 , wherein the liner and the deflector plate are each comprised of a ceramic matrix composite material, and wherein the annular dome is comprised of a metal material.

9 . The combustor assembly of claim 1 , wherein the deflector plate comprises a thermal barrier coating.

10 . The combustor assembly of claim 1 , wherein the impingement holes extend perpendicularly relative to a surface of the annular dome.

11 . The combustor assembly of claim 1 , wherein the impingement holes extend at an angle between about 30° and 90° relative to a surface of the annular dome.

12 . The combustor assembly of claim 1 , wherein the cooling holes extend perpendicularly relative to a surface of the deflector plate.

13 . The combustor assembly of claim 1 , wherein the cooling holes extend at an angle between about 30° and 90° relative to a surface of the deflector plate.

14 . A gas turbine engine defining an axial direction, the gas turbine engine comprising:
a compressor section; a turbine section mechanically coupled to the compressor section through a shaft; and a combustor assembly disposed between the compressor section and the turbine section, the combustor assembly comprising:
a liner at least partially defining a combustion chamber;
an annular dome defining a first cavity and having a plurality of impingement holes; and
a deflector plate comprising a conical surface, a flat surface, and a plurality of cooling holes,
wherein the annular dome and the deflector plate define a second cavity, the second cavity being in fluid communication with the first cavity through the plurality of impingement holes, and the second cavity being in fluid communication with the combustion chamber through the plurality of cooling holes.

15 . The gas turbine engine of claim 14 , wherein a radially outer portion of the second cavity is sealed by placing a spline seal between the annular dome and the deflector plate.

16 . The gas turbine engine of claim 15 , wherein the deflector plate further defines a recessed slot that extends around an end of the spline seal, thereby providing fluid communication between the second cavity and the combustion chamber.

17 . The gas turbine engine of claim 14 , wherein a radially inner portion of the second cavity is sealed by brazing a joint between the annular dome and the deflector plate.

18 . The gas turbine engine of claim 14 , such that a first portion of the conical surface has a first angle, and a second portion of the conical surface has a second angle different from the first angle, and wherein the first angle and the second angle are in a range of about 15° to 75°.

19 . The gas turbine engine of claim 14 , wherein the impingement holes are angled at about 60° relative to the surface of the annular dome.

20 . The gas turbine engine of claim 14 , wherein the cooling holes are angled at about 60° relative to the surface of the deflector plate.

Assignees

• Gen Electric

Inventors

• Patel Nayan Vinodbhai
• Kim Kwanwoo
• Sutton Chad Holden
• Thomsen Duane Douglas
• Gonyou Craig Alan
• Abramson Harris Daniel
• Russo James A
• Stowers Robert Andrews
• Wang Shanwu
• Wang Anquan

Classifications

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F23R3/60

  Support structures; Attaching or mounting means · CPC title

• F23R3/00 Primary

  Continuous combustion chambers using liquid or gaseous fuel · CPC title