IP Library › Granted Patent US 6,966,745
Granted Patent B2
US 6,966,745 · App. 10/465,230 · Granted Nov 22, 2005

Method for intermediate cooling and gas turbine system with intermediate cooling

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Quick Facts
Patent No.
US 6,966,745
App. No.
10/465,230
Granted
Nov 22, 2005
Kind
B2
Abstract

In a method and a device for intermediate cooling during compression in a gas turbine system, the gas turbine system includes at least one first ( 1 ) and one second compressor ( 2 ), a combustion chamber ( 3 ), and a turbine ( 4 ). At least one intermediate cooler ( 9 ) is located between the first ( 1 ) and second compressor ( 2 ). The intermediate cooling takes place at least in part or for the most part isentropically.

Claims (18)

1. A method for intermediate cooling during compression of a gas turbine system, wherein the gas turbine system comprises at least one first and one second compressor, a combustion chamber, and a turbine, and wherein at least one intermediate cooler is located between the first and the second compressor, the method comprising:

at least in part isentropically intermediate cooling; and

wherein the cooling in the intermediate cooler takes place in an area where the medium to be cooled has a higher mach value than prior to the entrance into the intermediate cooler.

2. A method for intermediate cooling according to claim 1 , further comprising:

selecting an efficiency of the intermediate cooling η 1 greater than 0.5.

3. A method for intermediate cooling according to claim 1 , wherein at least in part isentropically intermediate cooling comprises mostly isentropically intermediate cooling.

4. A method for intermediate cooling according to claim 1 , further comprising:

reducing the mach value of the medium to be cooled prior to the entrance into the second compressor.

5. A method for intermediate cooling according to claim 1 , wherein the cooling comprises injecting water as a cooling medium.

6. A method for intermediate cooling during compression of a gas turbine system, wherein the gas turbine system comprises at least one first and one second compressor, a combustion chamber, and a turbine, and wherein at least one intermediate cooler is located between the first and the second compressor, the method comprising:

at least in part isentropically intermediate cooling; and

injecting a cooling medium in the intermediate cooler in an area where the medium to be cooled has a higher mach value than prior to the entrance into the intermediate cooler.

7. A method for intermediate cooling according to claim 6 , further comprising:

reducing the mach value of the medium to be cooled prior to the entrance into the second compressor.

8. A method for intermediate cooling according to claim 6 , wherein the injecting comprises injecting water as the cooling medium.

9. A method for intermediate cooling according to claim 6 , further comprising:

selecting an efficiency of the intermediate cooling η 1 greater than 0.5.

10. A method for intermediate cooling according to claim 6 , wherein at least in part isentropically intermediate cooling comprises mostly isentropically intermediate cooling.