Global to push GA events into
skip to main content

Title: 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.
Inventors:
;
Issue Date:
OSTI Identifier:
1410287
Assignee:
SIEMENS ENERGY, INC. (Orlando, FL) NETL
Patent Number(s):
9,822,662
Application Number:
14/075,140
Contract Number:
FC26-05NT42644
Resource Relation:
Patent File Date: 2013 Nov 08
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: