Combustion chamber with a wall section and a brim element

Patent metadata

Field	Value
Publication number	US-9316398-B2
Application number	US-201213978948-A
Country	US
Kind code	B2
Filing date	Feb 1, 2012
Priority date	Feb 18, 2011
Publication date	Apr 19, 2016
Grant date	Apr 19, 2016

Abstract

A combustion chamber for a gas turbine is proposed. The combustion chamber has a wall section and a brim element. The wall section has an inlet aperture for injecting a cooling medium into the combustion chamber. The brim element is mounted to an inner face of the wall section. The brim element is formed in such a way that a projected area of the brim element onto the inner face along a direction of a normal of the inner face at least partially covers the inlet channel.

First claim

The invention claimed is:

1. A combustion chamber for a gas turbine, comprising:
a wall section comprising an inlet channel for injecting a cooling medium into the combustion chamber, and
a brim element mounted to an inner face of the wall section,
wherein the brim element is formed in such a way that a projected area of the brim element onto the inner face along a direction of a normal of the inner face at least partially covers the inlet channel,
wherein the wall section further comprises a fuel injection aperture through which fuel is injectable into the combustion chamber,
wherein the wall section further comprises a groove formed within the inner face,
wherein the groove forms a part of an end section of the inlet channel,
wherein the groove is formed such that the groove runs at least partially along a predefined direction configured to guide the cooling medium to stream through the inlet channel,
wherein the groove has a curved shape along a circumferential direction around a center axis of the fuel injection aperture,
wherein the inlet channel forms together with an edge of the brim element and the inner face, an inlet aperture through which the cooling medium is configured to stream inside the combustion chamber, and
wherein the brim element is configured to guide the cooling medium through the inlet aperture, partially along the circumferential direction around the center axis of the fuel injection aperture.

2. The combustion chamber according to claim 1 ,
wherein the wall section further comprises at least one further inlet channel for injecting the cooling medium into the combustion chamber,
wherein the combustion chamber further comprises at least one further brim element mounted to the inner face of the wall section,
wherein the at least one further brim element is formed in such a way that a further projected area of the at least one further brim element onto the inner face along a direction of the normal of the inner face at least partially covers the at least one further inlet channel.

3. The combustion chamber according to claim 1 ,
wherein in the combustion chamber, fuel droplets are injectable for streaming in a main fuel streaming direction,
wherein the main fuel streaming direction comprises a direction component which is parallel to the inner face, and
wherein the brim element is formed and adjusted to the wall section in such a way that the brim element is configured to generate the inlet aperture through which the injected cooling medium is guided from a lee side of the brim element along a downstream direction along the direction component of the main fuel streaming direction.

4. The combustion chamber according to claim 1 , wherein the inlet channel is formed within the wall section in such a way that the inlet channel comprises a section running in a helical way.

5. The combustion chamber according to claim 1 , wherein the inlet channel is formed within the wall section in such a way that the inlet channel comprises a section running parallel with respect to the normal of the inner face.

6. The combustion chamber according to claim 1 , wherein the wall section is surrounded by a spacer element.

7. The combustion chamber according to claim 6 , wherein the spacer element has a width of more than 1.5 times and less than 4 times that of the wall section.

8. The combustion chamber according to claim 6 , wherein the spacer element has a width of more than 2 times and less than 4 times that of the wall section.

9. The combustion chamber according to claim 6 , wherein the spacer element is a titanium alloy.

10. The combustion chamber according to claim 1 , wherein the inner face of the wall section and/or the brim element is a titanium alloy.

11. The combustion chamber according to claim 1 , further comprising a burner body with a receiving section into which the wall section is mounted in a detachable manner.

12. The combustion chamber according to claim 11 , wherein the burner body comprises a pilot tip mounted to an opening of the burner body, and wherein the pilot tip forms a mounting face to which the wall section is mounted.

13. A method for controlling a flow of a cooling medium inside a combustion chamber for a gas turbine, comprising:
injecting the cooling medium into the combustion chamber through at least one inlet channel of a wall section of the combustion chamber; and
controlling the flow of the cooling medium inside the combustion chamber by a brim element mounted to an inner face of the wall section,
wherein the brim element is formed in such a way that a projected area of the brim element onto the inner face along a direction of a normal of the inner face at least partially covers the inlet channel,
wherein the wall section further comprises a groove formed within the inner face,
wherein the groove forms a part of an end section of the inlet channel,
wherein the groove is formed such that the groove runs at least partially along a predefined direction for guiding the cooling medium streaming through the inlet channel,
wherein the groove has a curved shape along the circumferential direction around a center axis of the fuel injection aperture,
wherein the inlet channel forms together with an edge of the brim element and the inner face, an inlet aperture through which the cooling medium streams inside the combustion chamber,
wherein the wall section further comprises a fuel injection aperture through which fuel is injectable into the combustion chamber, and
wherein the brim element is formed in such a way that the cooling medium streaming through the inlet aperture is guided partially along a circumferential direction around a center axis of the fuel injection aperture.

Assignees

• Nilsson Ulf
• Siemens Ag

Inventors

• Nilsson Ulf

Classifications

• F23D2900/00016

  Preventing or reducing deposit build-up on burner parts, e.g. from carbon · CPC title

• F23R2900/00004

  Preventing formation of deposits on surfaces of gas turbine components, e.g. coke deposits · CPC title

• F23R2900/03043

  Convection cooled combustion chamber walls with means for guiding the cooling air flow · CPC title

• F23R3/04

  Air inlet arrangements · CPC title

• F23D2214/00

  Cooling · CPC title