# US 5,699,965 A · Infrared suppressor for a gas turbine engine

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- Number: US 5,699,965 A
- Document ID: US5699965A
- Status: Granted
- Kind: A
- Application number: 07/374,025
- Filed: 1989-06-30
- Granted: 1997-12-23
- Earliest claimed: 1989-06-30
- Assignees: Sikorsky Aircraft Corporation
- Inventors: Armand F. Amelio
- Web page: https://patentgrep.com/patent/US5699965A

## CPC

- F02K 1/825: {Infrared radiation suppressors}
- B64D 33/04: of exhaust outlets or jet pipes
- B64D 2033/045: {comprising infrared suppressors}
- Y02T 50/60: Efficient propulsion technologies, e.g. for 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)
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

An IR suppressor produces a thin "ribbon" exhaust plume using a tapered exhaust manifold which has a plurality of discrete exhaust nozzles that are longitudinally aligned with the exhaust manifold. Optionally, the nozzles extend within but are spaced apart from mixing ducts which are open to the ambient air at both ends. The mixing ducts mix ambient air with the exhaust plume. In another aspect of this invention, a single nozzle (which is longitudinally aligned with the manifold) is substituted for the plurality of discrete exhaust nozzles. In this aspect, the nozzle extends within but is spaced apart from a mixing duct which is open at both ends and has a curve sufficient to block a line of sight to the nozzle. A helicopter that has a rotatable IR suppressor so that the exhaust can be directed substantially parallel to the helicopter blades when the blades are not turning to protect them from exhaust heat is also disclosed.

## Claims

### Claim 1

In an infrared suppressor for the exhaust of a gas turbine engine, said suppressor comprising an elongated tapered exhaust manifold, said manifold having an inlet for receiving said exhaust and a plurality of spaced apart manifold nozzles in fluid communication with said manifold, said nozzles substantially aligned along the manifold for dispersing said exhaust, the improvement characterized by:
a) each nozzle having an elongated opening, each opening being longitudinally aligned with said manifold and each nozzle having a substantially unobstructed exhaust flowpath to the ambient air;
b) a plurality of mixing ducts, each mixing duct having sidewalls, an upstream orifice and a downstream orifice, said upstream and downstream orifices being open to the ambient air; and
c) said manifold nozzles extending within but spaced apart from said mixing ducts.

### Claim 2 (depends on 1)

The infrared suppressor as recited in claim 1 wherein said mixing duct blocks a line of sight to each nozzle from angles substantially perpendicular to said mixing duct sidewalls.

### Claim 3 (depends on 1)

The infrared suppressor as recited in claim 1 wherein said gas turbine engine provides power to helicopter blades and including means for rotating said infrared suppressor, such that said exhaust flowpath can be directed substantially parallel to the helicopter blades.

### Claim 4 (depends on 1)

The infrared suppressor as recited in claim 1 wherein said manifold has a decreasing cross-sectional area and the cross-sectional area of the manifold at any preselected point substantially equals the total area of the nozzles downstream of the preselected point.

### Claim 5

In an infrared suppressor for the exhaust of a gas turbine engine, said suppressor comprising an elongated tapered exhaust manifold, said manifold having an inlet for receiving said exhaust and a plurality of spaced apart manifold nozzles in fluid communication with said manifold, said nozzles substantially aligned along the manifold for dispersing said exhaust, the improvement characterized by each nozzle having an opening, each opening being elongated and longitudinally aligned with the manifold and each nozzle having a substantially unobstructed exhaust flowpath to the ambient air.

### Claim 6

In an infrared suppressor for the exhaust of a gas turbine engine, said suppressor comprising an elongated tapered exhaust manifold, said manifold having an inlet for receiving said exhaust and at least one nozzle in fluid communication with said manifold for dispersing said exhaust, the improvement characterized by:
each said nozzle having an elongated opening, said opening being longitudinally aligned with the manifold and said nozzle having a substantially unobstructed flow path to the ambient air;
a respective mixing duct for each said nozzle, each said mixing duct having an upstream orifice and a downstream orifice, said upstream and downstream orifices being open to the ambient air; and
each said manifold nozzle extending within but spaced apart from the respective said mixing duct.