초록 ▼

A turbine system is provided including a plurality of gas turbine engines, each having a compressor section for producing compressed air, a combustor section, and a turbine section yielding hot exhaust gas. A single, common recuperator section is shared by and operatively associated with the plural

A turbine system is provided including a plurality of gas turbine engines, each having a compressor section for producing compressed air, a combustor section, and a turbine section yielding hot exhaust gas. A single, common recuperator section is shared by and operatively associated with the plurality of gas turbine engines. A first flow path within the single, common recuperator section is configured to receive compressed air produced by the compressor section of each gas turbine engine. A second flow path, separated from the first flow path and within the single, common recuperator section is configured to receive hot exhaust gases yielded by the turbine section of each gas turbine engine.

대표청구항 ▼

What is claimed is: 1. A turbine system comprising: a plurality of gas turbine engines, each having a compressor section for producing compressed air, a combustor section, and a turbine section yielding hot exhaust gases; a single, common recuperator section shared by and operatively associated wit

What is claimed is: 1. A turbine system comprising: a plurality of gas turbine engines, each having a compressor section for producing compressed air, a combustor section, and a turbine section yielding hot exhaust gases; a single, common recuperator section shared by and operatively associated with the plurality of gas turbine engines; a first flow path within the single, common recuperator section and configured to receive compressed air produced by the compressor section of each gas turbine engine; and a second flow path, separated from the first flow path, within the single, common recuperator section, and configured to receive hot exhaust gases yielded by the turbine section of each gas turbine engine. 2. The system of claim 1, wherein the plurality is three and the three gas turbine engines are arranged in a dense-pack configuration adjacent the single, common recuperator section. 3. The system of claim 1, wherein the plurality is four and the four gas turbine engines are arranged in a linear-pack configuration adjacent the single, common recuperator section. 4. The system of claim 1, wherein each of the plurality of gas turbine engines is configured to be selectively and individually activated and deactivated. 5. The system of claim 1, wherein each of the plurality of gas turbine engines includes: a third flow path configured to direct air to the compressor section; a fourth flow path configured to direct compressed air from the compressor section to the first flow path within the single, common recuperator section; a fifth flow path configured to direct compressed air from the first flow path within the single, common recuperator section to the combustor section; and a sixth flow path configured to direct exhaust gas from the turbine section to the second flow path within the single, common recuperator section. 6. The system of claim 5, wherein each of the plurality of gas turbine engines is configured to be selectively and individually activated and deactivated, and further including a first valve in each fourth flow path configured to direct compressed air from the compressor section to the first flow path within the single, common recuperator section, each first valve configured to be selectively actuated to close the fourth flow path when its respective gas turbine engine is deactivated, and each first valve configured to be selectively actuated to open the fourth flow path when its respective gas turbine engine is activated. 7. The system of claim 6, further including a second valve in each fifth flow path configured to direct compressed air from the first flow path within the single, common recuperator section to the combustor section, each second valve configured to be selectively actuated to close the fifth flow path when its respective gas turbine engine is deactivated, and each second valve configured to be selectively actuated to open the fifth flow path when its respective gas turbine engine is activated. 8. The system of claim 1, wherein the single, common recuperator section includes a multi-celled structure and the first and second flow paths include portions of the multi-celled structure. 9. A work machine, comprising: a chassis; a plurality of gas turbine engines mounted to the chassis and configured to drive at least one mechanism, each gas turbine engine including a compressor section for producing compressed air, a combustor section, and a turbine section yielding hot exhaust gases; a single, common recuperator section mounted on the chassis and shared by and operatively associated with the plurality of gas turbine engines; a first flow path for compressed air produced by the compressor sections, the first flow path being within the recuperator section and shared by each of the plurality of gas turbine engines; and a second flow path separated from the first flow path, for hot exhaust gases yielded by the turbine sections, the second flow path being within the recuperator section and shared by each of the plurality of gas turbine engines. 10. The work machine of claim 9, wherein the plurality off gas turbine engines includes at least three gas turbine engines arranged in a dense-pack configuration and each configured to be selectively and individually activated and deactivated. 11. The work machine of claim 10, including at least one valve associated with each gas turbine engine for inhibiting flow of compressed air from the recuperator section to a deactivated gas turbine engine. 12. The work machine of claim 9, wherein the plurality of gas turbine engines includes at least four gas turbine engines arranged in a linear-pack configuration and each configured to be selectively and individually activated and deactivated. 13. The work machine of claim 12, including at least one valve associated with each gas turbine engine for inhibiting flow of compressed air from the recuperator section to a deactivated gas turbine engine. 14. The work machine of claim 9, wherein the at least one mechanism includes at least one generator. 15. The work machine of claim 9, wherein the single, common recuperator section includes a multi-celled structure and the first and second flow paths include portions of the multi-celled structure.