Cooling system with compressor bleed and ambient air for gas turbine engine
A cooling system for a turbine engine for directing cooling fluids from a compressor to a turbine blade cooling fluid supply and from an ambient air source to the turbine blade cooling fluid supply to supply cooling fluids to one or more airfoils of a rotor assembly is disclosed. The cooling system may include a compressor bleed conduit extending from a compressor to the turbine blade cooling fluid supply that provides cooling fluid to at least one turbine blade. The compressor bleed conduit may include an upstream section and a downstream section whereby the upstream section exhausts compressed bleed air through an outlet into the downstream section through which ambient air passes. The outlet of the upstream section may be generally aligned with a flow of ambient air flowing in the downstream section. As such, the compressed air increases the flow of ambient air to the turbine blade cooling fluid supply.
- Research Organization:
- Siemens Energy, Inc., Orlando, FL (United States)
- Sponsoring Organization:
- USDOE
- DOE Contract Number:
- FC26-05NT42644
- Assignee:
- SIEMENS ENERGY, INC. (Orlando, FL)
- Patent Number(s):
- 9,822,662
- Application Number:
- 14/075,140
- OSTI ID:
- 1410287
- Resource Relation:
- Patent File Date: 2013 Nov 08
- Country of Publication:
- United States
- Language:
- English
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