Combustion chamber with a wall section and a brim element
AssigneeSiemens Aktiengesellschaft
InventorUlf Nilsson
Life of this patent
Estimating the term…
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.
Claims13
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.
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.
Dependencies are inferred from the claim text.