초록

A combustion chamber of a gas turbine includes starter film cooling of a combustion chamber wall 4 and several circularly arranged burners 7 with local maxima and minima in the intensity of the starter film 3 being provided around the circumference of the combustion chamber wall 4.

대표청구항 ▼

What is claimed is: 1. A gas turbine combustion chamber including starter film cooling of a combustion chamber wall and several circularly arranged burners, wherein, the starter film cooling is provided by starter film holes positioned in a head of the combustion chamber upstream of any film coolin

What is claimed is: 1. A gas turbine combustion chamber including starter film cooling of a combustion chamber wall and several circularly arranged burners, wherein, the starter film cooling is provided by starter film holes positioned in a head of the combustion chamber upstream of any film cooling holes provided on a wall of the combustion chamber, the starter film holes being grouped into at least a first set of groups and a second set of groups, the first set of groups providing local starter film maxima with a greatest starter film air flow in certain sectors around a circumference of the combustion chamber where a thermal load is greater as compared to the second set of groups providing local starter film minima with a least starter film air flow in other sectors around the circumference of the combustion chamber where a thermal load is lesser to decrease a temperature gradient of the combustion chamber wall in a circumferential direction. 2. A gas turbine combustion chamber in accordance with claim 1, wherein, a number of at least one of the local starter film maxima and the local starter film minima, respectively, is equal to a number of the burners. 3. A gas turbine combustion chamber in accordance with claim 1, wherein, a number of at least one of the local starter film maxima and the local starter film minima, respectively, is an integer multiple of the burners. 4. A gas turbine combustion chamber in accordance with claim 1, wherein, the local starter film maxima and local starter film minima are produced by the air quantities passed through different groups of starter film holes, respectively. 5. A gas turbine combustion chamber in accordance with claim 4, wherein, at least certain of the starter film holes have different effective flow areas. 6. A gas turbine combustion chamber in accordance with claim 5, wherein, the starter film holes are equally distributed around the circumference of the combustion chamber. 7. A gas turbine combustion chamber in accordance with claim 5, wherein, at least certain of the starter film holes have a different hole spacing around the circumference of the combustion chamber. 8. A gas turbine combustion chamber in accordance with claim 4, wherein, effective areas of the starter film holes are equal and at least certain of the starter film holes have different spacing than other starter film holes around the circumference of the combustion chamber. 9. A gas turbine combustion chamber in accordance with claim 4, wherein the local starter film maxima and local starter film minima are produced by varying a number of the starter film holes positioned respective sectors of the circumference of the combustion chamber, with the starter film holes in certain of the sectors positioned on multiple different pitch circles of the combustion chamber. 10. A gas turbine combustion chamber in accordance with claim 4, wherein, at least certain of the starter film holes have different flow coefficients. 11. A gas turbine combustion chamber in accordance with claim 4, wherein, at least certain of the starter film holes have different inlet contours. 12. A gas turbine combustion chamber in accordance with claim 4, wherein, variation of the intensity of the starter film cooling is generally continuous. 13. A gas turbine combustion chamber in accordance with claim 4, wherein, variation of the intensity of the starter film cooling is in discrete states. 14. A gas turbine combustion chamber in accordance with claim 1, wherein, the respective local starter film maxima are aligned with radial projections of the burner axes. 15. A gas turbine combustion chamber in accordance with claim 1, wherein, the respective local starter film maxima are shifted circumferentially relative to radial projections of the burner axes. 16. A gas turbine combustion chamber, comprising: a plurality of burners positioned around a circumference of the combustion chamber; a plurality of starter film holes positioned around the circumference of a head of the combustion chamber upstream of any film cooling holes provided on a wall of the combustion chamber to provide starter film cooling of the combustion chamber, the starter film holes being arranged in at least a first set of groups to provide local starter film maxima with a greatest starter film air flow in certain sectors around a circumference of the combustion chamber where a thermal load is greater and a second set of groups to provide local starter film minima with a least starter film air flow in other sectors around the circumference of the combustion chamber where a thermal load is lesser to decrease a temperature gradient of the combustion chamber wall in a circumferential direction. 17. A gas turbine combustion chamber as in claim 16, wherein the greatest starter film air flows in the first set of groups are produced by a greater total flow area of the starter film holes in those groups as compared respectively to the second set of groups. 18. A gas turbine combustion chamber as in claim 17, wherein the greater total flow area is at least partially produced by starter film boles having respectively larger flow areas. 19. A gas turbine combustion chamber as in claim 18, wherein the greater total flow area is at least partially produced by decreased spacing between starter film boles. 20. A gas turbine combustion chamber as in claim 19, wherein the greater total flow area is at least partially produced by additional starter film holes positioned along at least one additional pitch circle of the combustion chamber. 21. A gas turbine combustion chamber as in claim 20, wherein the greatest starter film air flows are also produced by a greater flow coefficient of at least some of the starter film holes. 22. A gas turbine combustion chamber as in claim 21, wherein the greater flow coefficient is provided by contouring inlets of at least some of the starter film holes. 23. A gas turbine combustion chamber as in claim 17, wherein the greater total flow area is at least partially produced by decreased spacing between starter film holes. 24. A gas turbine combustion chamber as in claim 17, wherein the greater total flow area is at least partially produced by additional starter film holes positioned along at least one additional pitch circle of the combustion chamber. 25. A gas turbine combustion chamber as in claim 17, wherein the greatest starter film air flows are produced by a greater flow coefficient of at least some of the starter film holes. 26. A gas turbine combustion chamber as in claim 25, wherein the greater flow coefficient is provided by contouring inlets of at least some of the starter film holes. 27. A gas turbine combustion chamber as in claim 17, wherein, at least one of the local starter film minima is at least partially produced by a reduced number of starter film holes as compared to a number of starter film holes in the sectors having local starter film maxima.