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U.S. Department of Energy
Office of Scientific and Technical Information

Aft entry cooling system and method for an aircraft engine

Patent ·
OSTI ID:7019971
This patent describes a gas turbine engine having a longitudinal axis and an air compressor, a combustor, and tandemly-arranged high and low pressure turbines disposed in a serial arrangement along the longitudinal axis. It comprises: stationary means disposed aft of the discharge end of the low pressure turbine and extending radially outwardly relative to the longitudinal axis; and an air flow circuit connected to the interstage portion of the air compressor and to the stationary means.
Assignee:
G.E. Co., Cincinnati, OH (United States)
Patent Number(s):
A; US 5134844
Application Number:
PPN: US 7-560538
OSTI ID:
7019971
Country of Publication:
United States
Language:
English