Combustion chamber assembly with different curvatures for a combustion chamber wall and a combustion chamber shingle fixed thereto

Patent metadata

Field	Value
Publication number	US-11320144-B2
Application number	US-201916358353-A
Country	US
Kind code	B2
Filing date	Mar 19, 2019
Priority date	Mar 22, 2018
Publication date	May 3, 2022
Grant date	May 3, 2022

Abstract

A combustion chamber assembly group, and a mounting method therefor, includes a combustion chamber for an engine that includes a curved combustion chamber wall extending along two spatial directions, and a combustion chamber shingle affixed at an inner side of the combustion chamber wall and having a shingle edge defining the outer contour of the shingle. For an at least sectional abutment of the shingle edge at the combustion chamber wall with a minimum clamping force in an operational state of the engine, the shingle is mounted to the combustion chamber wall in a mounting state in which the shingle at least at one section of the shingle edge has a curvature with respect to at least one of the spatial directions that differs from the curvature of the combustion chamber wall with respect to this spatial direction.

First claim

The invention claimed is:

1. A combustion chamber assembly group, comprising:
a combustion chamber for an engine that comprises a curved combustion chamber wall extending along two spatial directions, and
a combustion chamber shingle that is affixed at an inner side of the combustion chamber wall and has a shingle edge that defines an outer contour of the combustion chamber shingle, the shingle edge including a central portion and end portions positioned on opposite sides of the central portion,
wherein for an at least sectional abutment of the shingle edge at the combustion chamber wall at a minimum clamping force in an operational state of the engine, the combustion chamber shingle has a curvature at a section of the shingle edge that differs with respect to at least one of the two spatial directions from a curvature of the combustion chamber wall with respect to the at least one of the two spatial directions, in a mounting state in which the combustion chamber shingle is mounted at the combustion chamber wall;
wherein the end portions of the shingle edge remain in contact with the combustion chamber wall from the mounting state to the operational state and the difference between the curvature of the section of the shingle edge and the combustion chamber wall changes between the mounting state and the operational state to provide the minimum clamping force in the operational state of the engine,
wherein with respect to one of the two spatial directions, the curvature of the shingle edge is smaller than the curvature of the combustion chamber wall, and
wherein with respect to the other of the two spatial directions, the curvature of the shingle edge is larger than the curvature of the combustion chamber wall between the end portions.

2. The combustion chamber assembly group according to claim 1 , wherein a ratio between the curvature of the combustion chamber wall and the smaller curvature at the section of the shingle edge is in a range from 1.03 to 1.4.

3. The combustion chamber assembly group according to claim 2 , wherein the ratio between the curvature radius of the combustion chamber wall and the curvature radius at the section of the shingle edge is in a range from 1.03 to 1.2.

4. The combustion chamber assembly group according to claim 1 , wherein a ratio between the curvature of the combustion chamber wall and the larger curvature at the section of the shingle edge is in a range from 0.7 to 0.98.

5. The combustion chamber assembly group according to claim 1 , wherein the section of the shingle edge includes a first section and a second section and a first curvature radius at the first section of the shingle edge is larger with respect to a first spatial direction of the two spatial directions along which the combustion chamber wall extends than the curvature radius of the combustion chamber wall with respect to the first spatial direction, and a second curvature radius at the second section of the shingle edge is smaller with respect to a second spatial direction of the two spatial directions than the curvature radius of the combustion chamber wall with respect to the second spatial direction.

6. The combustion chamber assembly group according to claim 1 , wherein the section of the shingle edge includes a first section and a second section and a first curvature radius at the first section of the shingle edge is larger with respect to a first spatial direction of the two spatial directions along which the combustion chamber wall extends than the curvature radius of the combustion chamber wall with respect to the first spatial direction, and a second curvature radius at the second section of the shingle edge is also larger with respect to a second spatial direction of the two spatial directions than the curvature radius of the combustion chamber wall with respect to the second spatial direction.

7. The combustion chamber assembly group according to claim 1 , wherein the combustion chamber wall extends along
an axial direction which is parallel to a flow direction through the combustion chamber, and
along a circumferential direction that extends along a circular path about the axial direction.

8. A gas turbine engine with a combustion chamber that comprises at least one combustion chamber assembly group according to claim 1 .

9. A method for producing a combustion chamber assembly group, comprising:
providing a combustion chamber for an engine that comprises:
a curved combustion chamber wall extending along two spatial directions, and
a combustion chamber shingle that is to be affixed at an inner side of the combustion chamber wall and has a shingle edge that defines the outer contour of the combustion chamber shingle, the shingle edge including a central portion and end portions positioned on opposite sides of the central portion,
wherein for a sectional abutment of the shingle edge at the combustion chamber wall with a minimum clamping force in an operational state of the engine, the combustion chamber shingle is mounted to the combustion chamber wall in a mounting state in which the combustion chamber shingle at a section of the shingle edge has a curvature with respect to at least one of the two spatial directions that differs by a predetermined measure from a curvature of the combustion chamber wall with respect to the at least one of the two spatial directions;
wherein the end portions of the shingle edge remain in contact with the combustion chamber wall from the mounting state to the operational state and the difference between the curvature of the section of the shingle edge and the combustion chamber wall changes between the mounting state and the operational state to provide the minimum clamping force in the operational state of the engine,

wherein with respect to one of the two spatial directions, the curvature of the shingle edge is smaller than the curvature of the combustion chamber wall, and
wherein with respect to the other of the two spatial directions, the curvature of the shingle edge is larger than the curvature of the combustion chamber wall between the end portions.

10. The method according to claim 9 , wherein the predetermined measure is determined depending on at least one chosen from a strength of the minimum clamping force, a natural frequency of the combustion chamber shingle, and on a temperature difference between the combustion chamber shingle and the combustion chamber wall in the operational state of the engine.

11. The method according to claim 9 , wherein the predetermined measure is chosen in such a manner that a vibration of the section of the combustion chamber shingle relative to the combustion chamber wall is prevented in the operational state of the engine.

12. The method according to claim 9 , wherein, the combustion chamber shingle is deformed and correspondingly curved to obtain the different curvature radii of the combustion chamber wall and the combustion chamber shingle.

13. The method according to claim 9 , wherein the curvature radii of the combustion chamber wall and the combustion chamber shingle are adjusted to each other in order to obtain the sectional abutment of the section of the shingle edge with the minimum clamping force.

14. A combustion chamber assembly group, comprising:
a combustion chamber for an engine that comprises a curved combustion chamber wall extending along two spatial directions, and
a combustion chamber shingle that is affixed at an inner side of the combustion chamber wall and has a shingle edge that defines an outer contour of the combustion chamber shingle, the shingle edge including a central portion and end portions positioned on opposite sides

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Heinze Kay
• Ebel Michael
• Sikorski Igor
• Baumgartner Manfred
• Szarvasy Ivo

Classifications

• F23M5/02

  characterised by the shape of the bricks or blocks used · CPC title

• F23R3/002 Primary

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

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title

• F23R2900/00005

  Preventing fatigue failures or reducing mechanical stress in gas turbine components · CPC title