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A gas turbine engine cooling system for providing cooling air to engine components includes a core engine and, in downstream serial flow relationship, a high pressure compressor, a combustor, and high pressure turbine. A first flowing system is used for flowing a portion of the pressurized air to a

A gas turbine engine cooling system for providing cooling air to engine components includes a core engine and, in downstream serial flow relationship, a high pressure compressor, a combustor, and high pressure turbine. A first flowing system is used for flowing a portion of the pressurized air to a heat exchanger to cool the pressurized air and provide the cooling air and a second flowing system is used for flowing a first portion of the cooling air to a compressor impeller operably connected to a compressor disk of the high pressure compressor for boosting pressure of the first portion of the cooling air. A second portion of the cooling air is supplied to turbine cooling. The heat exchanger may be a fuel to air heat exchanger for cooling the portion of the pressurized air from the first flowing means with fuel. Preferably, a first plurality of diffuser vanes extending radially across the core flowpath and each includes at one radial vane airflow passage for conveying the cooling air across the core flowpath to the compressor impeller and the turbine cooling apparatus.

대표청구항 ▼

A gas turbine engine cooling system for providing cooling air to engine components includes a core engine and, in downstream serial flow relationship, a high pressure compressor, a combustor, and high pressure turbine. A first flowing system is used for flowing a portion of the pressurized air to a

A gas turbine engine cooling system for providing cooling air to engine components includes a core engine and, in downstream serial flow relationship, a high pressure compressor, a combustor, and high pressure turbine. A first flowing system is used for flowing a portion of the pressurized air to a heat exchanger to cool the pressurized air and provide the cooling air and a second flowing system is used for flowing a first portion of the cooling air to a compressor impeller operably connected to a compressor disk of the high pressure compressor for boosting pressure of the first portion of the cooling air. A second portion of the cooling air is supplied to turbine cooling. The heat exchanger may be a fuel to air heat exchanger for cooling the portion of the pressurized air from the first flowing means with fuel. Preferably, a first plurality of diffuser vanes extending radially across the core flowpath and each includes at one radial vane airflow passage for conveying the cooling air across the core flowpath to the compressor impeller and the turbine cooling apparatus. t stream emerging at the outlet of the booster is smoothed with respect to pressure fluctuations. 6. The method as claimed in claim 2, wherein a pressure difference in the mass stream before subdivision and after combination is about 2 bar. 7. The method as claimed in claim 3, wherein a pressure difference in the mass stream before subdivision and after combination is about 2 bar. 8. The method of claim 1, wherein the gas includes air delivered in a power station. 9. The method as claimed in claim 2, wherein the relatively smaller part stream is about 20% of the mass stream of the delivered gas. 10. A device for increasing pressure of a gas from a compressor with a booster, comprising: a stream divider, via which a mass stream of the gas is adapted to be subdivided into a relatively smaller part stream and a relatively larger part stream; an ejector, to which the relatively smaller part stream is adapted to be delivered by the booster; and a bypass line, via which the relatively larger part stream is adapted to be delivered to a suction nipple of the ejector, wherein the relatively smaller part stream is adapted to be delivered to the booster via an air cooler. 11. The device as claimed in claim 10, wherein the relatively smaller part stream is about 20-40% of the mass stream of the delivered air. 12. The device as claimed in claim 10, wherein the booster is coupled to the ejector via a line, to which a buffer tank is coupled for smoothing of pressure fluctuations. 13. The device as claimed in claim 10, wherein the output of the ejector is coupled to at least one of a device for pressure-type fluidized-bed firing, an after burner and a coal gasifier. 14. A power station, including the device as claimed in claim 10. 15. The device of claim 11, wherein the booster is connected to the ejector via a line to which a buffer tank is connected for smoothing of pressure fluctuations. 16. The device as claimed in claim 11, wherein the relatively smaller part stream is about 20% of the mass stream of the delivered air. 17. The method as claimed in claim 11, wherein the relatively smaller part stream is about 20-40% of the mass stream of the delivered gas. 18. The device as claimed in claim 11, wherein the output of the ejector is coupled to at least one of a device for pressure-type fluidized-bed firing, an after burner and a coal gasifier. 19. The device as claimed in claim 12, wherein the output of the ejector is coupled to at least one of a device for pressure-type fluidized-bed firing, an after burner and a coal gasifier. 20. A power station, including the device as claimed in claim 10, and further including a device for pressure-type fluidized-bed firing and a coal gasifier.