# US 5,699,662 A · Infrared suppression exhaust duct system for a turboprop propulsion system for an aircraft

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- Number: US 5,699,662 A
- Document ID: US5699662A
- Status: Granted
- Kind: A
- Application number: 08/654,362
- Filed: 1996-05-28
- Granted: 1997-12-23
- Earliest claimed: 1996-05-28
- Assignees: Lockheed Martin Corporation
- Inventors: Gary A. Born; Thomas A. Roberts; Peter M. Boor
- Web page: https://patentgrep.com/patent/US5699662A

## CPC

- B64D 33/04: of exhaust outlets or jet pipes
- F02K 1/825: {Infrared radiation suppressors}
- B64D 2033/045: {comprising infrared suppressors}
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00)
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

The invention is an exhaust duct system for an aircraft, the aircraft having at least one turboprop propulsion system mounted on the wing within a nacelle, the propulsion system having a circular shaped exhaust port generally aligned with the longitudinal axis of the aircraft. In detail, the invention includes a generally shallow S shaped duct having a longitudinal axis aligned with the longitudinal axis of the exhaust port. A duct includes a circular shaped inlet section, a rectangular exhaust port section and a transition section therebetween. The inlet has a larger diameter than the exhaust port of the propulsion system and is positioned there about. The inlet includes a plurality of flexible finger like members extending inward such that they are in slidable engagable with the external surface of the exhaust port. A first pair of struts are pivotally connected at the center of the rectangular exhaust port section by their first ends and extend upward and outward from the longitudinal axis of the duct with their second ends pivotally connected to the underside of the wing. A second pair of struts are pivotally connected to the sides of the transition section by their first ends and extend upward and rearwards from the inlet slightly outward and having second ends pivotally coupled to the underside of the wing.

## Claims

### Claim 1

An exhaust duct system for an aircraft, the aircraft having at least one turboprop propulsion system mounted on the wing within a nacelle, the propulsion system having a circular shaped exhaust port generally aligned with the longitudinal axis of the aircraft, system comprising:
a generally shallow S shaped duct having a longitudinal axis aligned with the longitudinal axis of the exhaust port, a circular shaped inlet section, and a rectangular exhaust port section and a transition section therebetween; with the inlet having a larger diameter than the exhaust port of the propulsion system and positioned there about, said inlet portion having means to provide flexible engagement with an external surface of the exhaust port,
a first pair of struts having first ends pivotally connected at a central position of the rectangular exhaust port section, said first pair of struts extending upward and outward from the longitudinal axis of the duct and having second ends pivotally connected to the underside of the wing; and
a second pair of struts having first ends pivotally connected to the sides of said transition section, said second pair of struts extending upward and rearwards from the inlet and slightly outward and having second ends pivotally coupled to the underside of the wing.

### Claim 2 (depends on 1)

The system as set forth in claim 1 wherein means to provide flexible engagement with the external surface of the exhaust port comprises said inlet having a plurality of flexible finger like members extending inward such that said finger like member are in slidable engagement with the external surface of the exhaust port.

### Claim 3 (depends on 2)

The system as set forth in claim 2 wherein said first pair of struts are generally perpendicular to said longitudinal axis of said exhaust duct.

### Claim 4 (depends on 3)

The system as set forth in claim 3 wherein said exhaust duct is covered with a non-metallic shroud.