Gas turbine pressurized cooling system
AssigneeAvco Corporation
InventorsAndrew Kozak, George Minkkinen
Life of this patent
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Abstract
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.
Claims14
A system for 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, turbine section and a first core of gas passing therethrough, the system comprising:
- coolant supply means comprising bleed means for bleeding pressurized gas from the first core of gas to thereby form a second core of coolant gas;
- second compressor means for additionally pressurizing the second core of coolant gas to thereby increase the pressure of the second core of coolant gas such that the pressure of the second core of coolant gas is greater than the pressure of the first core of gas, said second compressor comprising a gas compressor driven by an accessory drive shaft;
- and
- conduit means for delivering the increased pressure second core of coolant gas from said second compressor means to said turbine section whereby the second core of coolant gas has a higher pressure at said turbine assembly than the first core of gas.
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.
A system for cooling a turbine assembly in a gas turbine engine, the engine having a compressor section with a first gas compressor means, a combustor section, a turbine section, and a first gas conduit for passing a first core of gas through the engine, the system comprising:
- coolant supply means comprising bleed means for bleeding pressurized gas from the first core of gas to thereby form a second core of coolant gas;
- means for additionally pressurizing the second core of coolant gas to thereby increase the pressure of the second core of coolant gas such that the pressure of the second core of coolant gas is greater than the pressure of the first core of gas;
- means for delivering the increased pressure second core of coolant gas from said pressuring means to said turbine section;
- and
- means for independently controlling said pressurizing means relative to rotation of a main drive shaft of the engine to thereby independently control the pressure of gas flowing through said delivering means for predetermined conditions.
Dependencies are inferred from the claim text.