Invention Grant
- Patent Title: Turbine cooling system using an enhanced compressor air flow
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Application No.: US14274874Application Date: 2014-05-12
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Publication No.: US09644542B2Publication Date: 2017-05-09
- Inventor: Alston Ilford Scipio , Julio Enrique Mestroni , Dale J. Davis , Sanji Ekanayake
- Applicant: General Electric Company
- Applicant Address: US NY Schenectady
- Assignee: General Electric Company
- Current Assignee: General Electric Company
- Current Assignee Address: US NY Schenectady
- Agency: Eversheds Sutherland (US) LLP
- Main IPC: F02C9/18
- IPC: F02C9/18 ; F02C3/13 ; F02C7/12
Abstract:
The present application provides a gas turbine engine for low turndown operations. The gas turbine engine may include a compressor with a compressor bleed air flow, a turbine, and a compressor bleed air flow manifold. The compressor bleed air manifold directs a variable portion of the compressor bleed air flow to the turbine.
Public/Granted literature
- US20150322865A1 Turbine Cooling System Using an Enhanced Compressor Air Flow Public/Granted day:2015-11-12
Information query
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