Combustion chamber intermediate part for a gas turbine
View Patent ↗This invention relates to a gas turbine having a combustion chamber arrangement and a turbine chamber connected downstream of said combustion chamber arrangement, wherein the combustion chamber arrangement includes a plurality of individual combustion chambers formed by input areas and transition areas converging in an annular gap leading to the turbine chamber and wherein the longitudinal axes of the individual combustion chambers are placed at an angle relative to an engine axis that is defined by the axial extension of the turbine chamber. In order to improve said gas turbine by visibly reducing the thermal and mechanical loads of the individual combustion chambers in the transition area so that cooling requirements can be lowered in said area, the transition area of at least one individual combustion chamber into the turbine chamber is deflected in the direction of the engine axis and substantially in the input area of the turbine chamber.
1. A combustion chamber arrangement in a gas turbine comprising:
a combustion chamber comprising an upstream cylindrical input section and a downstream transition section, the transition section changing from a circular cross-section of the input section to a cross-section with an annular segment form at its downstream end and comprising an internal wall portion and an external wall portion; and
a turbine chamber comprising an input area comprising an internal fixed blade platform and an external fixed blade platform;
wherein the combustion chamber is disposed along a combustion chamber axis different from an engine axis, the turbine chamber being disposed along the engine axis, and
wherein the internal fixed blade platform and the external fixed blade platform each are curved in the direction of the combustion chamber, effective to relocate a thermal load due to hot gas deflection to the input area.
2. The combustion chamber arrangement of claim 1 , wherein the internal wall portion is flat.
3. The combustion chamber arrangement of claim 2 , wherein the external wall portion runs in a straight line and does not provide a contact surface for deflection of a hot gas flow through the transition section.
4. The combustion chamber arrangement of claim 1 , wherein the internal wall portion is flat and the external wall portion runs in a straight line and does not provide a contact surface for deflection of a hot gas flow through the transition section, effective to reduce thermal load related material stresses on the transition section.
5. The combustion chamber arrangement of claim 1 , wherein at least one of the internal fixed blade platform and the external fixed blade platform is extended in the direction of the transition section, effective to further move deflection of the hot gas flow in the direction of the turbine chamber.
6. The combustion chamber arrangement of claim 1 , wherein the transition section and the input area are embodied so that a hot gas flow running from the combustion chamber into the turbine chamber is deflected in the direction of the engine axis substantially in the input area of the turbine chamber.
7. A gas turbine comprising the combustion chamber arrangement of claim 1 .
8. A gas turbine comprising a plurality of combustion chamber arrangements of claim 1 , wherein the transition sections of all the individual combustion chambers and all corresponding input areas of the turbine chambers are embodied so that deflection of a hot gas flow from each individual combustion chamber to the respective turbine chamber in the direction of the engine axis takes place essentially in the input area of the respective turbine chamber.
9. A combustion chamber arrangement in a gas turbine comprising:
a combustion chamber comprising an upstream cylindrical input section and a downstream transition section, the transition section changing from a circular cross-section of the input section to a cross-section with an annular segment form at its downstream end and comprising an internal wall portion and an external wall portion; and
a turbine chamber comprising an input area comprising an internal fixed blade platform and an external fixed blade platform;
wherein the combustion chamber is disposed along a combustion chamber axis different from an engine axis, the turbine chamber being disposed along the engine axis, and
wherein at least one of the internal fixed blade platform and the external fixed blade platform is extended toward the combustion chamber, effective to relieve the combustion chamber in a critical area of hot gas deflection.
10. The combustion chamber arrangement of claim 9 , wherein the internal wall portion is flat.
11. The combustion chamber arrangement of claim 10 , wherein the external wall portion runs in a straight line and does not provide a contact surface for deflection of a hot gas flow through the transition section.
12. The combustion chamber arrangement of claim 9 , wherein the internal wall portion is flat and the external wall portion runs in a straight line and does not provide a contact surface for deflection of a hot gas flow through the transition section, effective to further reduce thermal load related material stresses on the transition section.
13. The combustion chamber arrangement of claim 9 , wherein the transition section and the input area are embodied so that a hot gas flow running from the combustion chamber into the turbine chamber is deflected in the direction of the engine axis substantially in the input area of the turbine chamber.
14. A gas turbine comprising the combustion chamber arrangement of claim 9 .
15. A gas turbine comprising a plurality of combustion chamber arrangements of claim 9 , wherein the transition sections of all the individual combustion chambers and all corresponding input areas of the turbine chambers are embodied so that deflection of a hot gas flow from each individual combustion chamber to the respective turbine chamber in the direction of the engine axis takes place essentially in the input area of the respective turbine chamber.