Exhaust assembly for a high speed civil transport aircraft engine

Patent · Tue Oct 13 00:00:00 EDT 1992

OSTI ID:7141085

Giffin, R G; Wolf, J P; Hilse, M A

This patent describes an exhaust assembly for an aircraft gas turbine engine including a core engine having an outlet for discharging exhaust gases. It comprises: a casing having an inlet for receiving the exhaust gases from the core engine outlet; a variable area converging-diverging CD nozzle attached to the casing and including a first throat having a flow area A[sub 8] outlet having a flow area A[sub 9] for channeling the exhaust gases the CD nozzle further including: a plurality of spaced apart primary flaps defining therebetween a converging channel; a plurality of spaced apart secondary flaps defining therebetween a diverging channel; a plurality of space dapart retractable chutes; means for cahnneling air along aft facing surfaces of the chutes into siad CD nozzle; and wherein each of the chutes has a generally U-shaped trailing edge including first and second transversely spaced apart legs, a base extending between the legs at radially inner ends thereof, and a top opening extending between the legs at radially outer ends thereof.thereof.

• Assignee: General Electric Co., Cincinnati, OH (United States)
• Patent Number(s): US 5154052; A
• Application Number: PPN: US 7-520318
• OSTI ID: 7141085
• Resource Relation: Patent File Date: 7 May 1990
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
32 ENERGY CONSERVATION, CONSUMPTION, AND UTILIZATION
EXHAUST SYSTEMS
DESIGN
GAS TURBINE ENGINES
AIR FLOW
AIR POLLUTION CONTROL
EXHAUST GASES
NOZZLES
PROPULSION SYSTEMS
CONTROL
ENGINES
FLUID FLOW
FLUIDS
GAS FLOW
GASEOUS WASTES
GASES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
POLLUTION CONTROL
WASTES
330103* - Internal Combustion Engines- Turbine
330700 - Advanced Propulsion Systems- Emission Control
320201 - Energy Conservation
Consumption
& Utilization- Transportation- Air & Aerospace