Combustion chamber assembly with specifically arranged mixing air holes on inner and outer combustion chamber wall

Patent metadata

Field	Value
Publication number	US-11754286-B2
Application number	US-202217965193-A
Country	US
Kind code	B2
Filing date	Oct 13, 2022
Priority date	Dec 16, 2021
Publication date	Sep 12, 2023
Grant date	Sep 12, 2023

Abstract

A combustion chamber for an engine includes inner and outer combustion chamber walls bounding a combustion space. Three mixing air holes with respective central points at corner points of a virtual first or second triangle are arranged on mutually opposite first and second wall segments of the inner and outer walls. The second triangle of the second wall segment of the outer wall is oriented rotated by 180° with respect to the first triangle of the first wall segment of the inner wall, and the mixing air holes arranged in rows on the first and second wall segments are arranged with respect to one another so the mixing air holes of the first and second wall segments that are arranged at the corner points of the first and second triangles do not lie opposite a mixing air hole of the second or first wall segment.

First claim

The invention claimed is:

1. A combustion chamber assembly, having a combustion chamber for an engine, comprising:
an inner combustion chamber wall and an outer combustion chamber wall for bounding a combustion space of the combustion chamber,
the combustion chamber extending along a central axis in an axial direction from a first axial end to a second axial end,
mixing air holes arranged in rows extending along a circumferential direction about the central axis, the rows including a first set of two rows extending through the inner combustion chamber wall and a second set of two rows extending through the outer combustion chamber wall, each of the first set of two rows and the second set of two rows respectively including a second row positioned aft of a first row in the axial direction, the mixing air holes being configured for conducting mixing air into the combustion space,
both the inner combustion chamber wall and the outer combustion chamber wall being divided in the circumferential direction into wall segments on which the mixing air holes are arranged in a predefined pattern, wherein:
three first mixing air holes of the first set of two rows are arranged with respective central points at corner points of a virtual first triangle on a first wall segment of the inner combustion chamber wall,
three second mixing air holes of the second set of two rows are arranged with respective central points at corner points of a virtual second triangle on a second wall segment of the outer combustion chamber wall, and
the virtual second triangle has an orientation rotated by 180° in the axial direction with respect to the virtual first triangle such that the three first mixing air holes are not directly opposite the three second mixing air holes, respectively,
a fuel nozzle including a nozzle head and configured for injecting fuel into the combustion chamber, the nozzle head extending along a nozzle axis,
a heat shield segment carrying the nozzle head of the fuel nozzle, wherein each of the first wall segment and the second wall segment has a width in the circumferential direction equal to a width of the heat shield segment,
a plane of symmetry, the plane of symmetry established by the nozzle axis and at least one point on the central axis between the first axial end and the second axial end,
wherein the virtual first triangle and the virtual second triangle are both isosceles triangles, wherein the virtual first triangle and the virtual second triangle are identical,
wherein a tip of the virtual first triangle and a tip of the virtual second triangle lie on the plane of symmetry, and, in a top view along a viewing direction running perpendicularly to the axial direction and perpendicularly to the circumferential direction, both the virtual first triangle and the virtual second triangle are symmetrical with respect to the plane of symmetry,
wherein the first set of two rows and the second set of two rows each respectively have a total of precisely five mixing air holes positioned on each of the first wall segment and the second wall segment, respectively, with each of the first wall segment and the second wall segment having two further mixing air holes, respectively, in addition to the three first mixing air holes and the three second mixing air holes.

2. The combustion chamber assembly according to claim 1 , wherein a first distance measured in the circumferential direction between each of the two further mixing air holes and the plane of symmetry on each of the first wall segment and the second wall segment is greater than a second distance between the each of the two further mixing air holes and mixing air holes arranged in further wall segments circumferentially adjacent the first and second wall segments.

3. The combustion chamber assembly according to claim 2 , wherein the first distance is twice the second distance.

4. The combustion chamber assembly according to claim 1 , wherein a first distance measured in the circumferential direction between each of the two further mixing air holes and the plane of symmetry on the first wall segment corresponds to a length of a base of the virtual first triangle.

5. The combustion chamber assembly according to claim 1 , wherein a first distance measured in the circumferential direction between each of the two further mixing air holes and the plane of symmetry on the second wall segment corresponds to a length of a base of the virtual second triangle.

6. The combustion chamber assembly according to claim 1 , wherein an axial distance between each row of the first set of two rows and the second set of two rows, respectively lies in a range of 0.05 d to 0.4 d, where d is a distance between the first and second wall segments.

7. A gas turbine engine having at least one of the combustion chamber assembly according to claim 1 .

8. The combustion chamber assembly according to claim 1 , wherein the precisely five mixing air holes positioned on each of the first wall segment and the second wall segment are both symmetrical with respect to the plane of symmetry.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Staufer Max

Classifications

• F23R3/50 Primary

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

• F23R3/06 Primary

  Arrangement of apertures along the flame tube · CPC title

• F23R3/002

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

• Y02T10/12

  Improving ICE efficiencies · CPC title