초록 ▼

A system for cooling a turbine assembly in a gas turbine engine. The system has a bleed means for bleeding a portion of a first core of gas exited from a compressor section of the engine to thereby form a second core of gas. The second core of gas is additionally pressurized by a second compressor m

A system for cooling a turbine assembly in a gas turbine engine. The system has a bleed means for bleeding a portion of a first core of gas exited from a compressor section of the engine to thereby form a second core of gas. The second core of gas is additionally pressurized by a second compressor means to increase the pressure of the second core of gas. The second core of gas is then delivered to the turbine section for cooling of the engine such that the second core of coolant gas has a higher pressure than the first core of gas exiting the combustor section.

대표청구항 ▼

A method of cooling a turbine assembly in a gas turbine engine, said gas turbine engine having a compressor section with a first gas compressor means, a combustor section, a turbine section and a first core of gas passing therethrough, the method comprising the steps of: bleeding pressurized gas fro

A method of cooling a turbine assembly in a gas turbine engine, said gas turbine engine having a compressor section with a first gas compressor means, a combustor section, a turbine section and a first core of gas passing therethrough, the method comprising the steps of: bleeding pressurized gas from the first core of gas at a point at least partially past said first compressor section to thereby form a second core of gas; compressing said second core of gas by means of a second compressor means to thereby increase the pressure of the bleed gas such that the pressure of the second core of gas is greater than the pressure of the first core of gas, said second compressor means being driven by an accessory drive shaft of the engine; and delivering the increased pressure bleed gas to said turbine section whereby the bleed gas has a higher pressure at said turbine section than the first core of gas.