Combustion chamber of a gas turbine

Patent metadata

Field	Value
Publication number	US-9447973-B2
Application number	US-201514641797-A
Country	US
Kind code	B2
Filing date	Mar 9, 2015
Priority date	Mar 11, 2014
Publication date	Sep 20, 2016
Grant date	Sep 20, 2016

Abstract

A combustion chamber of a gas turbine includes an external combustion chamber wall and at least one shingle that is mounted at the same, as well as a base plate and a combustion chamber head, characterized in that the shingle extends over the entire length of the combustion chamber and is held at its frontal end area, as it appears with respect to the flow direction of the combustion chamber, inside a groove of the base plate, and at its back end area inside a groove of the external combustion chamber wall.

First claim

The invention claimed is:

1. A combustion chamber of a gas turbine comprising:
an external combustion chamber wall including a rear end area with respect to a flow direction of the combustion chamber, the rear end area of the external combustion chamber including an axially extending groove;
at least one shingle mounted to the external combustion chamber wall;
a base plate including an axially extending groove;
a combustion chamber head,
wherein the at least one shingle extends over an entire length of the combustion chamber, the at least one shingle including a front end area and a rear end area with respect to the flow direction of the combustion chamber, the front end area of the at least one shingle positioned within the groove of the base plate to engage and be supported by the groove of the base plate to connect the at least one shingle to the base plate, the rear end area of the at least one shingle positioned within the groove of the external combustion chamber wall to engage and be supported by the groove of the external combustion chamber wall;
wherein at least a portion of the front end area of the at least one shingle is a spring, and the spring is positioned within the groove of the base plate to engage and be supported by the groove of the base plate to connect the at least one shingle to the base plate.

2. The combustion chamber according to claim 1 , wherein a front end area of the external combustion chamber wall is welded together with the base plate.

3. The combustion chamber according to claim 1 , wherein at least one of the grooves is formed as a circumferential groove.

4. The combustion chamber according to claim 1 , wherein at least one of the grooves is formed as a segmented groove.

5. The combustion chamber according to claim 1 , and further comprising cooling holes formed in an area of at least one of the grooves.

6. The combustion chamber according to claim 1 , wherein the at least one shingle is formed as a segmented part at a circumference of the combustion chamber.

7. The combustion chamber according to claim 6 , wherein the at least one shingle includes a plurality of shingles provided at the circumference of the combustion chamber.

8. The combustion chamber according to claim 1 , wherein the spring is formed as at least one chosen from a circumferential ring and in a segmented manner.

9. A combustion chamber of a gas turbine comprising:
an external combustion chamber wall including a rear end area with respect to a flow direction of the combustion chamber, the rear end area of the external combustion chamber including an axially extending groove;
at least one shingle mounted to the external combustion chamber wall;

a base plate including an axially extending groove;
a combustion chamber head,
wherein the at least one shingle extends over an entire length of the combustion chamber, the at least one shingle including a front end area and a rear end area with respect to the flow direction of the combustion chamber, the front end area of the at least one shingle positioned within the groove of the base plate to engage and be supported by the groove of the base plate to connect the at least one shingle to the base plate, the rear end area of the at least one shingle positioned within the groove of the external combustion chamber wall to engage and be supported by the groove of the external combustion chamber wall;
wherein at least a portion of the rear end area of the at least one shingle is a spring, and the spring is positioned within the groove of the external combustion chamber wall to engage and be supported by the groove of the external combustion chamber wall.

10. The combustion chamber according to claim 9 , wherein the spring is formed as at least one chosen from a circumferential ring and in a segmented manner.

11. The combustion chamber according to claim 1 , wherein at least a portion of the rear end area of the at least one shingle is a second spring, and the second spring is positioned within the groove of the external combustion chamber wall to engage and be supported by the groove of the external combustion chamber wall.

12. The combustion chamber according to claim 11 , wherein the second spring is formed as at least one chosen from a circumferential ring and in a segmented manner.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Clemen Carsten

Classifications

• F23R3/002 Primary

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

• F23R3/02 Primary

  characterised by the air-flow or gas-flow configuration (reverse- flow combustion chambers F23R3/54; cyclone or vortex type combustion chambers F23R3/58) · CPC title

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title

• F23R3/60

  Support structures; Attaching or mounting means · CPC title