Compressor discharge bleed air circuit in gas turbine plants and related method

Patent · Tue Apr 08 00:00:00 EDT 2003

OSTI ID:921792

Anand, Ashok Kumar ^[1]; Berrahou, Philip Fadhel ^[2]; Jandrisevits, Michael ^[3]

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1. Niskayuna, NY
2. Latham, NY
3. Clifton Park, NY

A gas turbine system that includes a compressor, a turbine component and a load, wherein fuel and compressor discharge bleed air are supplied to a combustor and gaseous products of combustion are introduced into the turbine component and subsequently exhausted to atmosphere. A compressor discharge bleed air circuit removes bleed air from the compressor and supplies one portion of the bleed air to the combustor and another portion of the compressor discharge bleed air to an exhaust stack of the turbine component in a single cycle system, or to a heat recovery steam generator in a combined cycle system. In both systems, the bleed air diverted from the combustor may be expanded in an air expander to reduce pressure upstream of the exhaust stack or heat recovery steam generator.

• Research Organization: General Electric Co., Schenectady, NY (United States)
• Sponsoring Organization: USDOE
• DOE Contract Number: FC21-95MC31176
• Assignee: General Electric Company (Schenectady, NY)
• Patent Number(s): 6,543,234
• Application Number: 10/153,609
• OSTI ID: 921792
• Country of Publication: United States
• Language: English

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