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
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Related Subjects
32 ENERGY CONSERVATION, CONSUMPTION, AND UTILIZATION
320201 -- Energy Conservation
Consumption
& Utilization-- Transportation-- Air & Aerospace
33 ADVANCED PROPULSION SYSTEMS
330103* -- Internal Combustion Engines-- Turbine
330603 -- Vehicle Design Factors-- Engine System
42 ENGINEERING
420400 -- Engineering-- Heat Transfer & Fluid Flow
AIRCRAFT COMPONENTS
COOLING SYSTEMS
DESIGN
ENGINES
GAS TURBINE ENGINES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
320201 -- Energy Conservation
Consumption
& Utilization-- Transportation-- Air & Aerospace
33 ADVANCED PROPULSION SYSTEMS
330103* -- Internal Combustion Engines-- Turbine
330603 -- Vehicle Design Factors-- Engine System
42 ENGINEERING
420400 -- Engineering-- Heat Transfer & Fluid Flow
AIRCRAFT COMPONENTS
COOLING SYSTEMS
DESIGN
ENGINES
GAS TURBINE ENGINES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES