Avco Corporation

Paul L Hoffman

Robert M Laughlin

John F Hurley

Joseph C Manente, Jr

John J Martin

An improved honeycomb seal is provided for turbine engines. The subject honeycomb structure comprises a plurality of identical rings. Each ring has a plurality of radially extending convolutions defining alternating ridges and valleys. The rings are fixedly arranged in abutting relationship to define a tubular honeycomb structure having an array of radially extending honeycomb cells. The resultant honeycomb structure is adaptable to both large and small diameter turbine engines. Furthermore, the individual cells of the honeycomb structure can be constructed to any width or depth.

Honeycomb seal for turbine engines

A heat exchange apparatus having a plurality of plates through which heat is exchanged from a first gas to a second gas is provided with a plurality of plates having first and second opposing patterns. Each of the opposing patterns is provided with a plurality of sinusoidally varying surface strips and a plurality of spacing ridges between the surface strips, whereby the second gas flows in a generally sinusoidal path in a first direction along a first side of the first and second patterns between the first and second plates and the first gas flows in a generally sinusoidal path in a direction opposite the first direction along the other side of the first and second plates. The plurality of spacing ridges on the second pattern are disposed relative to the spacing ridges on the first pattern such that the spacing ridges on the second pattern lie along a line substantially in the middle of the surface strips of the first pattern, and vice versa. The first and second patterns are provided with sealing ridges in abutting relationship, the sealing ridges so disposed to provide an inlet and outlet for the second gas when the plates are mounted in the heat exchange apparatus.

Primary surface for compact heat exchangers

A heat exchange apparatus is provided with a plurality of plates formed and stacked so at to provide heat transfer through the plates from a first gas to a second gas. The plates are of substantially identical configuration and size, each of the plates formed with a central opening and an alternating arrangement of first and second surface patterns, ports being provided between the first and second surface patterns. The plates are stacked such that adjacent plates are rotated 180.degree. about a diametrical axis relative to each other and so as to place the ports and patterns in alignment, surface patterns of the first type from any of the plates being adjacent to surface patterns of the second type on a plate adjacent thereto to form a plurality of opposing pattern pairs. Each of the first and second patterns in each pattern pair have a plurality of sinusoidally varying surface strips and a plurality of spacing ridges between the surface strips whereby the second gas flows in a generally sinusoidal path in a first direction between the first and second plates and the first gas flows in a generally sinusoidal path in a direction opposite the second gas along the other sides of the first and second plates.

Apparatus is disclosed for minimizing the infrared radiation emitted at the aft end of a bypass fan type turbine engine. Minimization is accomplished by ducting cool air from the secondary bypass airstream through an annulus to form a sheath of cooler air around the gas stream as it is discharged from the engine tailpipe. The sheath of air educted along the inside surface of the engine tailpipe minimizes infrared radiation in two ways. First it reduces the operating temperature of the tailpipe thus keeping radiation therefrom to a low level. Second, the cool outside air becomes entrained in the hot gas stream discharged from the turbine. This results in a reduction of the effective temperature of the gas plume and suppresses infrared radiation therefrom.

Integral infrared radiation suppressor for a turbofan engine

A heat suppressor for a gas turbine engine is mounted on an aircraft by means separate from the engine mounts. A sleeve apparatus is needed to connect the exhaust duct of the engine to the suppressor duct for continuous flow of turbine gases. The sleeve apparatus is in the form of a bellows to absorb bending forces created by flexing of the air frame. This invention provides a unique connecting assembly to connect the bellows to the engine. The assembly consists of an annular socket fixed to the bellows and constructed to receive a radially extending flange on a connecting shroud fixed to the engine. The flange and socket are slidably engaged to allow twisting movement between the bellows and the engine, while the bellows allows relative displacement of the axes of the connecting passages.

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Stratford, CT, United States of America

Paul L Hoffman