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Title: Turbine airfoil cooling system with cooling systems using high and low pressure cooling fluids

A turbine airfoil cooling system including a low pressure cooling system and a high pressure cooling system for a turbine airfoil of a gas turbine engine is disclosed. In at least one embodiment, the low pressure cooling system may be an ambient air cooling system, and the high pressure cooling system may be a compressor bleed air cooling system. In at least one embodiment, the compressor bleed air cooling system in communication with a high pressure subsystem that may be a snubber cooling system positioned within a snubber. A delivery system including a movable air supply tube may be used to separate the low and high pressure cooling subsystems. The delivery system may enable high pressure cooling air to be passed to the snubber cooling system separate from low pressure cooling fluid supplied by the low pressure cooling system to other portions of the turbine airfoil cooling system.
Inventors:
; ;
Issue Date:
OSTI Identifier:
1404936
Assignee:
SIEMENS ENERGY, INC. NETL
Patent Number(s):
9,797,259
Application Number:
14/200,168
Contract Number:
FC26-05NT42644
Resource Relation:
Patent File Date: 2014 Mar 07
Research Org:
SIEMENS ENERGY, INC. Orlando, FL (United States)
Sponsoring Org:
USDOE
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

Works referenced in this record:

Bicast Turbine Engine Components
patent-application, February 2014