초록 ▼

A gas turbine engine and method for operating a gas turbine engine includes compressing an air stream in a compressor and generating a post combustion gas by combusting a compressed air stream exiting from the compressor in a combustor. The post combustion gas is expanded in a first turbine. The exp

A gas turbine engine and method for operating a gas turbine engine includes compressing an air stream in a compressor and generating a post combustion gas by combusting a compressed air stream exiting from the compressor in a combustor. The post combustion gas is expanded in a first turbine. The expanded combustion gas exiting from the first turbine is split into a first stream, a second stream and a third stream. The first stream of the expanded combustion gas is combusted in a reheat combustor. An outer liner and flame stabilizer of the reheat combustor are cooled using the second stream of the expanded combustion gas. An inner liner of the reheat combustor is cooled using the third stream of the expanded combustion gas and a portion of the second stream of the expanded combustion gas passing through the one or more flame stabilizers.

대표청구항 ▼

1. A gas turbine engine, comprising: a compressor for compressing air;a combustor for generating a post combustion gas by combusting a compressed air exiting from the compressor;a first turbine for expanding the post combustion gas;a splitting zone for splitting an expanded combustion gas exiting fr

1. A gas turbine engine, comprising: a compressor for compressing air;a combustor for generating a post combustion gas by combusting a compressed air exiting from the compressor;a first turbine for expanding the post combustion gas;a splitting zone for splitting an expanded combustion gas exiting from the first turbine into a first stream, a second stream, and a third stream;a reheat combustor for combusting the first stream of the expanded combustion gas; anda radially outer liner at a radial exterior of the reheat combustor which the second stream is at least initially directed around;an inner liner at a radial interior of the reheat combustor which the third stream is at least initially directed around;a pressure loss device for developing a pressure differential between the second stream and the third stream; andone or more flame stabilizers traversing the reheat combustor and containing a fluid channel with an inlet at the outer liner and an outlet at the inner liner, the one or more flame stabilizers configured to convey a portion of the second stream into the flow of the third stream. 2. The gas turbine engine of claim 1, wherein the splitting zone is configured to split the expanded combustion gas in such a way that the second stream of the expanded combustion gas flows through a passage between a casing and the outer liner of the reheat combustor and the third stream of the expanded combustion gas flows through a passage between an engine centerline and the inner liner of the reheat combustor. 3. The gas turbine engine of claim 2, wherein the splitting zone is configured to maintain a balance of pressures of the first stream, the second stream and the third stream of expanded combustion gas to achieve sufficient flow through the reheat combustor and to provide for cooling of the reheat combustor. 4. The gas turbine engine of claim 1, wherein the pressure loss device comprises a device for developing a pressure differential between the second stream and the third stream so as to allow the portion of the second stream to be drawn through the one or more flame stabilizers and exit into the passage between the engine centerline and the inner liner of the reheat combustor and provide for cooling of the one or more flame stabilizers and the inner liner. 5. The gas turbine engine of claim 4, wherein the pressure loss device is one of an inlet metering device and a blocking structure. 6. The gas turbine engine of claim 1, further comprising a trapped vortex cavity, wherein at least the portion of the second stream of expanded combustion gases provides cooling to the trapped vortex cavity. 7. The gas turbine engine of claim 1, wherein the at least one of the inner liner and the outer liner of the reheat combustor comprises injection holes for at least a portion of one of the second stream and the third stream of the expanded combustion gas to enter the reheat combustor after cooling at least one of the inner liner and the outer liner of the reheat combustor and mix with a combusted first stream. 8. The gas turbine engine of claim 1, further comprising a second turbine for expanding a mixture of a combusted first stream of expanded combustion gas from the reheat combustor, the second stream of expanded combustion gas and the third stream of expanded combustion gas. 9. The gas turbine engine of claim 1, further comprising a second turbine for expanding a combusted first stream of expanded combustion gas from the reheat combustor and wherein at least one of a portion of the second stream of expanded combustion gas and a portion of the third stream of expanded combustion gas provide at least partial cooling for the second turbine. 10. A method of operating a gas turbine engine, the method comprising: compressing an air stream in a compressor;generating a post combustion gas by combusting a compressed air stream exiting from the compressor in a combustor;expanding the post combustion gas in a first turbine;splitting an expanded combustion gas exiting from the first turbine into a first stream, a second stream and a third stream;combusting the first stream of the expanded combustion gas in a reheat combustor, the reheat combustor including a radially outer liner at a radial exterior of the reheat combustor which the second stream is at least initially directed around, an inner liner at a radial interior of the reheat combustor which the third stream is at least initially directed around and one or more flame stabilizers traversing the reheat combustor and containing a fluid channel with an inlet at the outer liner and an outlet at the inner liner, the one or more flame stabilizers configured to convey a portion of the second stream into the flow of the third stream;creating a pressure differential between the second stream and the third stream using a pressure loss device;cooling the outer liner and the flame stabilizer of the reheat combustor using the second stream of the expanded combustion gas; andcooling the inner liner of the reheat combustor using the third stream of the expanded combustion gas and the portion of the second stream of the expanded combustion gas passing through the one or more flame stabilizers. 11. The method of claim 10, further comprising: mixing the second stream of the expanded combustion gas after cooling the outer liner and the one or more flame stabilizers of the reheat combustor with a combusted first stream of the expanded combustion gas of the reheat combustor; andmixing the third stream of the expanded combustion gas and a portion of the second stream of the expanded combustion gas passing through the one or more flame stabilizers after cooling the inner liner of the reheat combustor with the combusted first stream of the expanded combustion gas of the reheat combustor. 12. The method of claim 10, further comprising expanding the combusted first stream of the reheat combustor in a second turbine and at least partially cooling the second turbine with at least one of a portion of the second stream of the expanded combustion gas and a portion of the third stream of the expanded combustion gas. 13. The method of claim 10, wherein the second stream of the expanded combustion gas and the third stream of the expanded combustion gas, in combination are about 20% to about 45% by mass of the expanded combustion gas exiting from the first turbine. 14. The method of claim 10, wherein cooling the outer liner and the inner liner comprises, cooling through at least one of impingement cooling, effusion cooling, and film cooling. 15. The method of claim 10, further comprising mixing the second stream of the expanded combustion gas with a coolant before cooling the outer liner and the flame stabilizer of the reheat combustor. 16. The method of claim 15, wherein the coolant comprises air extracted from the compressor. 17. The method of claim 15, wherein the coolant comprises steam. 18. A method comprising: splitting a flow of an expanded post combustion gas from a first turbine into a first stream, a second stream and a third stream;combusting the first stream of the expanded post combustion gas in a reheat combustor, the reheat combustor including a radially outer liner at a radial exterior of the reheat combustor which the second stream is at least initially directed around, an inner liner at a radial interior of the reheat combustor which the third stream is at least initially directed around and one or more flame stabilizers traversing the reheat combustor and containing a fluid channel with an inlet at the outer liner and an outlet at the inner liner, the one or more flame stabilizers configured to convey a portion of the second stream into the flow of the third stream;creating a pressure differential between the second stream and the third stream using a pressure loss device;cooling the outer liner and the one or more flame stabilizers of the reheat combustor using the second stream of the post combustion gas; andcooling the inner liner of the reheat combustor using the third stream of the post combustion gas and the portion of the second stream of post combustion gas passing through the one or more flame stabilizers. 19. The method of claim 18, wherein splitting a flow of the expanded combustion gas includes maintaining a balance of pressures of the first stream, the second stream and the third stream to achieve sufficient flow through the reheat combustor and to provide for cooling of the reheat combustor. 20. The method of claim 18, further comprising metering a pressure differential between the second stream and the third stream with a pressure loss device to allow a portion of the second stream to be drawn through the one or more flame stabilizers and exit into a passage between the engine centerline and the inner liner of the reheat combustor and provide for cooling of the one or more flame stabilizers and the inner liner.